Monoplane

Davis D-1

24/01/202424/01/2024TerryLeave a comment

Walter C. Davis was a former WWI pilot who had been working in his family’s business, the Davis Automobile Company of Richmond, Indiana, when it was sold in 1928. Redirecting his talents back to flying, he purchased the production rights to the Vulcan V-3 and began work on the first Davis aircraft in March 1929. He hired Vulcan test pilot, Pat Love, and engineer Dwight Huntington and opened his factory in Richmond, Indiana.

Huntington’s slight re-design of the aircraft included adding the gently curved leading edge to the vertical stabilizer. Davis then set up dealers in California, Dayton, Boston, Seattle, Salt Lake City and Pittsburgh. Air racing success continued in 1929 and all seemed well. The advent of the Great Depression ultimately led to the demise of Davis Aircraft, but the company struggled on.

In December 1929, two new models were engineered with different engines, the D-1 with a 65 hp LeBlond and the D-1K with the 100 hp Kinner K-5. Both models were certificated, but sales lagged. Davis countered by aggressively pursuing direct sales to buyers and attended trade shows in St. Louis, Detroit and New York. He added the D-1-66 (later D-1-85) with an 85 hp LeBlond engine and cut prices, but then lost the entire finished inventory of planes to a fire.

The D-1 is a parasol-winged aircraft of mixed construction with a two-spar wing and a rectangular welded steel-tube fuselage, the whole being covered by fabric. There are tandem open cockpits and it is fitted with a fixed tailwheel undercarriage which is attached by struts to the fuselage top and bottom. The wing is braced by struts from the lower fuselage. Various engines of between 60 to 125 hp (45 to 93 kW) have been fitted.

Produced 1929-1930, the D-1 was used by sporting pilots and by private pilot owners for leisure flying. Davis Aircraft Corp. produced three models of the D4 series. The first two models were the D-1-85 with an 85 hp Le Blond engine and the D-1-K with a 100 hp Kinner engine. The third model, the D1-W was equipped with a 125 hp Warner Scarab seven-cylinder radial air-cooled engine. The Dl-W features complete dual controls for its tandem seats.

In September 1930, Art Chester bought a Davis D-1-85 parasol, and flew it to victory in the 25 mile event at the September 1930 National Air Races. A late model D-1W “The Whistler II” was built in 1933 for Davis with a canopy. It was raced in the 1934 Miami air race by Art Davis winning the category at 133.478 mph. NC150Y which was destroyed in a crash at the 1932 Nationals. It was later owned by movie star Richard Arlen, and restored to become a Grand Champion antique.

Unfortunately, the commercial market for airplanes just wasn’t there and in 1932 Davis turned to the production of lawn mowers. A few additional planes left the factory in 1933 but they were apparently made up from existing parts inventory or airframes returned to the factory for various reasons. They received new serial and registration numbers. Most Davis aircraft were sold ($2,965 with a 60hp LeBlond in 1929) in the United States but at least one went to Argentina. Fourteen examples remained in 2001 in various states of airworthiness and several were still airworthy in 2011.

Gallery

Variants:

D-1
23 built
Engine: 60 hp (45 kW) LeBlond 5D
Span: 30 ft 2 in
Length (overall): 19 ft 10 in
Gross Weight: 1,334 lb
Useful Load: 495 lb
Baggage: 20 lb
Fuel: 20 gal
Oil: 2 gal
High Speed: 101 mph
Cruise Speed: 85 mph
Landing Speed: 38 mph
Range: 350 sm
Type Data: ATC 256
Year of Introduction: 1929
Price (1929): $3,285
Price (1930): $2,995

D-1
Engine: LeBlond 70 5DE, 70 hp
Span: 30 ft 2 in
Length (overall): 19 ft 10 in
Gross Weight: 1,334 lb
Useful Load: 495 lb
Baggage: 20 lb
Fuel: 20 gal
Oil: 2 gal
High Speed: 101 mph
Cruise Speed: 85 mph
Landing Speed: 38 mph
Range: 350 sm
Type Data: ATC 256
Year of Introduction: 1929
Price (1929): $3,285
Price (1930): $2,995

D-1
Engine: LeBlond 70 DE, 70 hp
Span: 30 ft 2 in
Length (overall): 19 ft 10 in
Gross Weight: 1,334 lb
Useful Load: 495 lb
Baggage: 20 lb
Fuel: 20 gal
Oil: 2 gal
High Speed: 101 mph
Cruise Speed: 85 mph
Landing Speed: 38 mph
Range: 350 sm
Type Data: ATC 256
Year of Introduction: 1929
Price (1929): $3,285
Price (1930): $2,995

D-1-66
4 built
Engine: 85 hp (63 kW) LeBlond 5DF
Span: 30 ft 3 in
Length (overall): 21 ft 6 in
Gross Weight: 1,380 lb
Useful Load: 526 lb
Baggage: 47 lb
Fuel: 20 USgal
Oil: 2-1/2 USgal
High Speed: 112 mph
Cruise Speed: 97 mph
Landing Speed: 40 mph
Range: 360 sm
Type Data: ATC 317
Year of Introduction: 1930
Total Production: 4
Price (1930): $3,395
Price (1931): $2,795

D-1-85
Engine: 1 × LeBlond, 85 hp

D-1-K
11 built
Engine: 100 hp (75 kW) Kinner K-5
Span: 30 ft 3 in
Length (overall): 19 ft 10 in
Gross Weight: 1,461 lb
Useful Load: 536 lb
Baggage: 27 lb
Fuel: 25 USgal
Oil: 2-1/2 USgal
High Speed: 130 mph
Cruise Speed: 100 mph
Landing Speed: 40 mph
Range: 400 sm
Type Data: ATC 272
Year of Introduction: 1930
Total Production: 11
Price (1930): $3,995 to $4,185
Price (1932): $2,295

D-1-L
prototype of the D-1-166 (1 built)
Engine: 90 hp (67 kW) Lambert R-266

D-1-W
(8 converted from D-1-K)
Engine: Warner Scarab, 125 hp (93 kW)
Length: 20 ft 4 in (6.20 m)
Wingspan: 30 ft 2 in (9.19 m)
Height: 7 ft 3 in (2.21 m)
Empty weight: 925 lb (420 kg)
Gross weight: 1,461 lb (663 kg)
Maximum speed: 142 mph (229 km/h; 123 kn)
Cruise speed: 122 mph (106 kn; 196 km/h)
Stall speed: 46 mph (40 kn; 74 km/h)
Initial climb rate 1,360 fpm.
Range: 480 mi (417 nmi; 772 km)
Service ceiling: 14,800 ft (4,511 m)
Crew: one
Capacity: one passenger

D-1-W
Engine: Warner Super Scarab SS-50A, 145 hp
Propeller: Sensenich Model 86CA-69
Wing span: 30 ft. 3 in
Wing area: 145 sq. ft
Airfoil: Goettigen 387 modified
Length: 21 ft. 6 in
Height: 7 ft. 3 in
Empty weight: 1134 lb
Weight loaded: 1471 lb
Baggage: None
Fuel: 30 USgal
Oil: 3 USgal
Maximum speed: 142 mph
Cruising speed: 123 mph
Landing speed: 46 mph
Initial rate of climb: 1,270 fpm
Service ceiling: 19,000 ft
Normal range: 480 mi
Starter: Eclipse Y-150
Type Data: Memo 2-394

Davis Aircraft V-3 / Vulcan Aircraft V-3

24/01/2024TerryLeave a comment

Vulcan Aircraft updated the engine of the American Moth from a 60 hp Detroit Air-Cat to a Warner radial and the aircraft became the Vulcan V-3. It finished second in the National Air Races “A” Division, New York to Los Angeles Derby. Later it took first in the Los Angeles to Cincinnati race at 90.3 mph. Shortly after these achievements, William Burke died leaving the company’s future in doubt.

Dassy DA 1 / DA 2

24/01/2024TerryLeave a comment

In 1929 Georges Dassy built a low wing monoplane designed by Glymes who also worked
at SABCA (Belgian Public Limited Company of Aeronautical Constructions). G. Dassy, like many
other Belgian manufacturers, made their prototype in the context of the so-called “subsidy” program to encourage a national aeronautical industry.

This prototype – the Dassy DA 1 – performed its first flight in August 1930 registered OO-ALN.

The Dassy DA1 was powered with a Renard engine and entirely made of spruce wood coated with plywood

OO-ALN was sold to the pilot builder and director of the national aviation school, Jef Guldentops, in September 1930, which used it either at Haren or at its Leefdaal aerodrome (Tervuren) until 1940.

The registration was cancelled in April 1946, because presumed destroyed during the war.

The DA 1 allowed the development of the Dassy DA 2 two-seater tandem monoplane, adaptable
easily into a three-seater.

Dassy DA 1
Engine: Renard 5-cyl, 120 hp at 1580 rpm
Engine weight: 130 kg
Wingspan: 11.50 m
Wing area: 14 m²
Length: 6.40 m
Height: 2.30 m
Empty weight: 420 kg
Maximum weight: 725 k
Maximum speed: 194 km / h
Cruising speed (80% of power): 175 km / h
ROC: 250 m / min
Ceiling: 7,000 m
Range: 1,000 km

Dassault-Breguet / Dornier Alpha Jet

24/01/202431/08/2025TerryLeave a comment

On 10 July 1969 a project called Alpha Jet was started by the governments of Germany and France to cooperatively create a light aircraft for advanced jet training and for the tactical support role. The contenders were the following: Dassault-Brequet joined up with Dornier with the TA-501, Aérospatiale with MBB with the E-650 Eurotrainer and VFW with their own T-291 project. On 23 July 1970, the TA-501 project from Dassault-Dornier was selected, a tandem seat twin-engined jet trainer and light attack aircraft.

Dassault-Breguet / Dornier Alpha Jet Article

Dassault-Brequet was responsible for building the front fuselage and assembly of the trainer variant as well as the export orders. Dornier in Germany produced the rear fuselage, the tail, wings and assembled the attack variants. The Alpha Jet is power by two Larzac jet engines, which were designed by Turbomecca, SNECMA, MTU and KHD. On 30 November 1972 the first mock up was accepted by both governments and a contract for the production of four prototypes.
On 26 October 1973 prototype 01 made the first flight, sixth months ahead of the contract scheduled date. The official presentation flight was flown on 23 November in 1973 at Isres, France.
On 9 January 1974, the second prototype made its maiden flight, followed by prototype 03 on 4 May and prototype 04 on October 11th. Alpha Jet E entered production in 1977. The first production Alpha Jet E 1 was flown at Istres, France, on 4 November 1977. The aircraft features a DEFA 30mm cannon.

The German Alpha Jet A entered production a year later. Production aircraft were delivered starting in 1978, with French aircraft operating as pure trainer aircraft, while German aircraft were employed as light attack aircraft. The two types can be distinguished visually by the rounded nose of the French aircraft compared with the pointed nose of German aircraft. The aircraft feature a simple but sophisticated design, utilizing fixed leading edges and air intakes, and an area ruled fuselage to minimize transonic drag. The Alpha Jet was also designed to be turned between sorties quickly, and features single-point refueling, and no required ground-support equipment. Alpha Jet A was the light attack variant for the Luftwaffe designed to replace the Fiat G.91R/3s in the light attack and close air support role. The A is therefor equipped with a more advanced nav/attack system including HUD, Doppler navigation radar and twin-gyro INS. The German versions were equipped with a 27mm Mauser cannon, replacing the French DEFA. Alternatively a Super Cyclone recce pod could be carried on the centeline station.

Principal customers were the air arms of the partner countries, the French Air Force taking 176 between 1978 and 1985, and the Luftwaffe 175 between 1979 and 1983.

The Alpha Jet E was produced for the French Air Force and several export customers, including Egypt, where it is known as the MS1.

The Arab Organisation for Industrialisation’s Helwan factory assembled 37 Alpha Jets from CKD kits between 1982 and 1985, and also produced some components under licence. The Egyptian Air Force also received eight aircraft assembled in France.
The close-support version (Alpha Jet A) was built for the West German Air Force; while the alternative close support version, with a new navigation/attack system, was sold to the Cameroon and Egypt as the M52. The Alpha Jet Nouvelle Generation pur l’Ecole et l’Appui (NGEA), now known as the Alpha Jet 2, incorporates the navigation/attack system of the M52 together with uprated Larzac 04-C20 engines and Magic 2 AAMs. No NGEA sales have been achieved, but Egyptian M52s are to be upgraded to NGEA standard. The fifth version, announced in 1985, is the Alpha Jet Lancier. Derived from the NGEA, the Lancier is intended for day/night ground attack, anti-shipping strikes, and anti-helicopter duties. In addition to the NGEA systems it has a Flir, Thomson-CSF Agave multimode radar, active and passive ECM, anti-shipping missiles, and laser guided bombs. No orders for the Lancier have been achieved to date. The Alpha Jet 3 is an advanced training version for use with FLIR, laser and ECM systems.

Under an independent programme, the Luftwaffe is retrofitting more powerful Larzac 04-C20 engines to boost performance. A limited armament and avionics upgrade had been approved for the Luftwaffe’s Alpha jet fleet for service from 1992.
By early 1986 more than 480 Alpha Jets had been delivered, against orders for 501 for ten customers.
The German Luftwaffe was the sole operator of the Alpha Jet A light attack version until the 1990s. The first production aircraft flew in 1979 and three years later Dornier closed the production line. The 175 Luftwaffe Alpha Jets replaced the Fiat/Aeritalia G.91R, of which 300 were operated in the tactical support and light attack role. In the 1990s the Alpha Jet was slowly withdrawn from service, the last example being officially retired on 31 December 1998. A large number of aircraft was sold to other nations and about 40 aircraft were put into storage at Fürstenfeldbruck. Two examples have been bought and restored for flying with the Flying Bulls, a display team sponsored by Red Bull.

The Alpha Jet E trainer version for France entered service with the Armée de l’Air replacing the Fouga Magister, Lockheed T-33 and the Dassault Mystère IVA.

The Belgian Air Force needed an advanced trainer and was interested in the development of the Alpha Jet since the start of the project. Belgium operated 28 aircraft, which have been upgraded prolonging their service life until at least 2015. The upgrade was carrier out by SABCA (Société Anonyme Belge de Constructions Aéronautiques), the first upgraded example being delivered back to the air force on 21 April in 2000. The upgrade features a new flightstick, advanced HUD, GPS, ILS and a multi function display in the rear cockpit.
In 1994 50 ex-Luftwaffe Alpha Jets were sold to the Portuguese Air Force. In service with Squadrons 103 Caracóis (Snails) for complementary flying training and operational conversion training and with Squadron 301 Jaguares (Jaguars) on the offensive air support role, both squadrons operated from Beja airbase.

Operators: Belgium, Cameroon, Egypt, France, Ivory Coast, Marocco, Nigeria, Portugal, Qatar, Thailand, Togo.

In 2017 Alpha Jets were still in service with the militaries of France, Belgium, Egypt, Portugal, Thailand, and are operated by EPNER and Empire Test Pilot School.

Gallery

Breguet Alpha Jet
Engines: 2 x SNECMA / Turboméca Larzac 04-C5, 13244 N
Length: 40.322 ft / 12.29 m
Height: 13.747 ft / 4.19 m
Wingspan: 29.888 ft / 9.11 m
Wing area: 188.37 sqft / 17.5 sqm
Max take off weight: 13230.0 lb / 6000.0 kg
Weight empty: 6945.8 lb/ 3150.0 kg
Max. speed: 535 kts / 991 km/h
Initial climb rate: 11614.17 ft/min / 59.00 m/s
Service ceiling: 44948 ft / 13700 m
Wing load: 70.32 lb/sq.ft / 343.00 kg/sq.m
Range: 680 nm / 1260 km
Range (max. weight): 432 nm / 800 km
Crew: 2
Armament: 1x MK 30mm, 2500kg ext.

Alpha Jet
Engine: 2 x Snecma/Turbomeca Larzac 04-C6.
Installed thrust: 26.5 kN.
Span: 9.1 m.
Length: 12.3 m.
Wing area: 17.5 sq.m.
Empty wt: 3855 kg.
MTOW: 7940 kg.
Warload: 2720 kg.
Max speed: 1000 kph.
Initial ROC: 3420 m / min.
Ceiling: 14,600+ m.
T/O run: 410 m.
Ldg run: 610 m.
Fuel internal: 1900 lt.
Range/Endurance: 1230 km / 3.5 hr.
Combat radius: 350-1075 km.
Armament: 1 x 27/30 mm, 2 x AAM.
Hardpoints: 4/5.

Alpha Jet
Max Speed: 550 KIAS / .95 M
Ceiling: 47,000 ft
G-Limits: +8 / -5
Payload: 1,360 lb on each inner pylon, 635 lb on each outer pylon
EW: Wired for ALQ-167 and ALQ-188
Endurance: 2.5+ hr with 2 drop tanks
Empty Weight: 7,850 lb
Useful load: 8,600 lb

Alpha Jet E
Engines: two 13.24 kN (2,976 lb st) SNECMA/Turbomecca Larzac 04-C6 non-afterburning turbofan
Wing span 9.11 m (29 ft 10¼ in)
Wing area: 188,4 sq,ft / 17,50 sq m
Length 11.75m (38 ft 6½ in)
Height 4.19m (13 ft 9 in)
Empty weight 3345 kg (7,374 lb)
Max Take-Off Weight 8.000 kg (17,637 lb)
Max level speed at sea level 1000 km/h (621 mph)
Service ceiling 14,630m (48,000 ft)
Climb to 30,000ft/9145m: 7 min 0 sec
Radius: 764 mi / 1230 km
Armament: one Mauser 27mm or DEFA 30mm ventral cannon pod with 125 rpg
Ordnance: 2500 kg (5,511 lb)
Hardpoints: 4

Dassault Rafale

24/01/202401/09/2025TerryLeave a comment

France originally was part of the EFA (European Fighter Aircraft) project, which would result in the Eurofighter. In 1985 France left the project and started its own development of a fighter, which led to the ACX or Rafale A.

Dassault Rafale Article

The Rafale (‘Squall’) was originally conceived to demonstrate technologies applicable to a French air force Jaguar replacement (ACT= Avions Combat Tactique) and a French navy Crusader and Super Etendard replacement (ACM= Avion de Combat Marine).
It is a single-seat aircraft with a compound-sweep delta wing, an all-moving canard, a single fin, and semi-vented intakes. It incorporates digital fly-by-wire, relaxed stability, a reclined pilot’s seat, a wide-angle headup display, and composite components are used extensively in the airframe. Provision has been made for the introduction of fibre-optics, voice command, and voice warning systems.
Equipped with the multi-mode RBE2 radar which has full air-to-air and air-to-ground capability, it can carry a wide range of weapons, including the APACHE stand-off munitions dispenser and the ASMP nuclear missile.
The Rafale A technology demonstrator, A 01, powered by two General Electric F404 turbofans, was rolled out of the Saint-Cloud factory on 14 December 1985,
First flying on 4 July 1986, Mach 1.3 was exceeded during the flight.
In May 1987 the Rafale A prototype successfully completed a series of approaches to the carrier Clemenceau to establish the feasibility of carrier operations.
In April 1989 the aircraft was laid-up for the substitution of a SNECMA M88-2 augmented turbofan in the port engine bay and flew in this configuration on 27 February 1990. The M88 is the selected engine for production versions of the Rafale.
Developed from the Rafale A was the single seat Rafale C that first flew on 19 May 1991.

The two-seat Rafale B was designed as a dual control conversion trainer for the single seat Rafale C. But the Rafale B has developed as a fully operational variant with full combat capability. Either an instructor, a second pilot or a WSO can assist the pilot from the rear seat. The Rafale B and C aircraft were planned to enter Armée de l’Air (French Air Force) service from 2002 onwards to replace its older Mirage variants and Jaguars. The first production aircraft Rafale B1 flew for the first time on 4 December 1998 and was delivered to the French Air Force.
On April 20, 2001, a Rafale B fitted with conformal fuel tanks made its first flight.

Designed especially for the Aeronavale (French Navy Air Arm) is the carrier capable Rafale M. A fully navilised version first flying on 12 December 1991. The Rafale M has for 80% the same structural design and for 95% the same systems as the Rafale C. It has strengthened main undercarriage, extended nosewheel suitable for catapult launch, hydraulically operated arrester hook, but has no folding wings. The centreline pylon has to be removed because of the longer nosewheel undercarriage. The first production Rafale M aircraft replaced the remaining F-8E(FN) Crusaders in the fighter role. Subsequent deliveries were to replace the Super Etendard and Etendard IVP in the attack and recconnaissance roles.

A fourth variant developed for the French Navy, is the two-seat Rafale N to enter service in 2008. The Rafale will become the only combat aircraft in the French Navy when all aircraft are delivered.
The original plan was to order a total of 94 Cs, 78 Ms and 140 Bs.
On December 1, 2001, the French carrier Charles de Gaulle departed to support the war on terrorism with on board seven Rafale M fighters. Although the aircraft did not take part in the large-scale air combat operation over Afghanistan, they flew combat air patrols and were able to practise and test out new tactics.

Gallery

Prototype
Engines: 2 x Snecma M88-2, 16,870 lb thrust
MTOW: 43,000 lb

Rafale A
Engine: 2 x General Electric GE F404-GE-100, 69847 N
Length : 51.837 ft / 15.8 m
Height: 17.06 ft / 5.2 m
Wingspan: 36.745 ft / 11.2 m
Wing area: 505.908 sq.ft. / 47.0 sq.m
Max take off weight: 44100.0 lb / 20000.0 kg
Weight empty: 20947.5 lb / 9500.0 kg
Max. weight carried: 23152.5 lb / 10500.0 kg
Max. speed: 1147 kt / 2124 km/h
Landing speed: 120 kt / 223 km/h
Wing load: 87.33 lb/sq.ft / 426.0 kg/sq.m
Fuel capacity: 1123 gal / 4250 lt
Crew: 1
Armament: 1x MK 30mm DEFA 554, max 12x AIM.

Rafale C
Engines: 2 x SNECMA M88-2 turbofans, 7500kg, 16,500 lb
Max take-off weight: 19500 kg / 42990 lb
Empty weight: 9060 kg / 19974 lb
Wingspan: 10.9 m / 35 ft 9 in
Length: 15.3 m / 50 ft 2 in
Height: 5.34 m / 17 ft 6 in
Max. speed: 2070 km/h / 1286 mph
Armament: 1 x 30mm cannon
Hardpoints: 14

Rafale M
Engines: 2 x SNECMA M88-3 afterburning turbofans, 86.98 kN (19,555 lb st)
Length 15.30m (50 ft 2½ in)
Height 5.34m (17 ft 6¼ in)
Wing span (over AAMs) 10.90m (35 ft 9¼ in)
Empty weight equipped 9670 kg (21,319 lb)
Max Take-Off Weight 21.500 kg (47,399 lb)
Max level speed at 11.000m (36,069 ft) Mach 2.0 or 2125 km/h (1,321 mph)
Service ceiling 16,460m (54,000 ft)
Armament: one DEFA 791 B 30mm cannon; up to 6000 kg (13,228 lb) ordnance
Hardpoints: 13

Dassault Mirage 4000

24/01/202414/09/2025TerryLeave a comment

Intended as a multi¬role fighter, the private venture Mirage 4000 prototype was originally known as the Super Mirage 4000.
Powered initially by two SNECMA M53-2 turbofans with afterburning thrust of 8500kg, the Mirage 4000 introduced extensive use of boron and carbonfibre composites for structures, and computer-derived aerodynamics and a fly-by-wire active control system making possible a rearward CG. Built-in armament consisted of two 30mm cannon and external ordnance loads in excess of 8000kg could be distributed between 11 external stations.

First flown on 9 March 1979, the Mirage 4000 achieved Mach=1.6 during its first flight and Mach=2.2 five weeks later, on 11 April, during its sixth flight.
The single prototype was re-engined with M53-5 turbofans with afterburning thrust of 8790kg during the course of its flight test programme. No production contract was placed for the Mirage 4000, but in 1986, the prototype was re-engined with M53-P2 engines and participated in the Rafale programme.

Mirage 4000
Engine: 2 x SNECMA M53 turbofans, 10000kg
Wingspan: 12.0 m / 39 ft 4.5 in
Length: 18.7 m / 61 ft 4 in
Wing area: 73.0 sq.m / 785.76 sq ft
Max. speed: 2333 km/h / 1450 mph
Ceiling: 20000 m / 65600 ft
Range w/max.fuel: 3700 km / 2299 miles
Armament: 2 x 30mm cannons
Hardpoints: ten

Dassault Mirage F.1

24/01/202414/06/2025TerryLeave a comment

In the 1960s Dassault designed the Mirage F1 as a successor for the Mirage III family. Loss of energy in low-level manoeuvring flight of the delta-winged Mirage III led to development of a traditional layout for the wing.
Evolved in parallel with the Mirage F2 as a scale-down, multi-role single-seat fighter employing a SNECMA Atar turbojet, the Mirage F1 was the subject of a government contract awarded in 1964. Possessing a conventional sweptback wing equipped with high-lift devices, and conventional swept tail surfaces, the private venture prototype F1 flew on 23 December 1966.

On 23 December 1966 the first prototype made its maiden flight. Three pre-series aircraft were ordered in September 1967, the first of these flying on 20 March 1969.

Dassault Mirage F.1 Article

The initial production model for France’s Armee de l’Air was designated F1C, placed emphasis on the intercept mission, was powered by an Atar 9K-50 turbojet affording 7200kg with afterburning, and had an armament of two 30mm cannon, two Matra 550 Magic and two Matra R 530 or Super 530 AAMs. An initial order for the F1C for the Armee de l’Air was placed in 1969, 162 being procured by that service (plus 64 recce F1CRs and 20 two-seat F1B trainers), initial operational capability being achieved in 1974. Many of the Armee de l’Air aircraft were delivered in, or retroactively modified to, F1C-200 standard with an 8cm fuselage plug to accommodate a removable flight refuelling probe.

The Mirage F.1C entered service with France’s air defence command (CAF-DA) in 1973, equipped with Thomson-CSF Cyrano IV all-sector fire-control radar. This type has also met with considerable success on the export market, customers including Ecuador, Greece, Iraq, Jordan, Kuwait, Libya, Morocco. South Africa and Spain. Production of 81 of this variant was followed by 89 Mirage F.1C-200 fighters fitted with a fixed inflight-refuelling probe at the base of the windscreen. The F.1-CR-200 became operational in July 1983, and carries cameras and infrared sensors internally with additional sensors in an under-fuselage pod. Improved navigation systems, radar, and a flight refuelling probe fitted as standard.

The Armée de l’Air (French Air Force) operated the F1C as its main interceptor fighter until the service entree of the Mirage 2000 in 1984.

The first flight was made by the Dassault Mirage F.1B two seat dual role trainer/tactical aircraft on 26 May 1976. Twenty Mirage F.1B conversion trainers (based on the Mirage F.1C but lacking its internal cannon) have also been received. It proved attractive to overseas customers, initial orders being received from Ecuador, Iraq, Jordan, Kuwait, Libya, Morocco and Spain.

Single-seat aircraft, including the F.1A with its slightly increased fuel tankage, have a notional maximum weapon-carrying capacity of 13,889 lb (6 300 kg), excluding the fitted cannon. This total is made up of 4,630 lb (2 100 kg) on the centreline; 220 lb (100 kg) of chaff/flare dispensers on the fuselage shoulder; 2,866 lb (1 300 kg) at the inner wing; 1,213 lb (550 kg) on the outer wing pylons, and 331 lb (150kg) on the wing-tip AAM positions. Maximum FIC/E internal fuel capacity is 946 Imp gal (4 300 1) or 7,568 lb (3 433 kg) of Jet A-1 /Avtur whilst three external tanks can hold a further 1,012 Imp gal (4 600 1) or 8,096 lb (3 672 kg). Fuel and weaponry must be traded-off between the confines of a 16,314 lb (7 400 kg) empty weight and 35,715 lb (16 200 kg) max take¬off weight.

French Air Force F.1-Cs were delivered as or converted to F.1-C-200s by the installation of detachable flight refuelling probe.

The Mirage F1E was a dedicated strike and attack aircraft which incorperated upgraded systems, including radar. Dassault also designed a two-seat version of the F1E for training, designated F1D.

A simplified version, lacking certain avionics such as the Cyrano radar, was produced for South Africa (F1AZ and F1CZ for the interceptor variant) and Libya for the clear-weather attack role with ranging radar as the Mirage F.1A, with Aida radar in a slimmer nose filled with much of the electronics previously located behind the cockpit, where more fuel could now be stored. Other additions were Doppler navigation, an inertial platform. and a laser rangefinder. Libya, together with Iraq, Jordan, Morocco, Qatar and Spain, also bought the multi-role Mirage F.1E. An export model, the Mirage F.1E, is based on the F.lC with upgraded Cyrano IVM radar offering terrain-avoidance, air-to-surface ranging, and look-down capability. The model also has an inertial platform, digital computer, and improved head-up display. The Mirage F.1E entered service in 1976, and offered multi-role capability, including anti¬ship attack with the AM.39 Exocet missile.

According to Dassault data the Mirage F1E’s LO-LO combat radius with one centreline Exocet, two Magics, two ECM pods and two 264 Imp gal (1 200 1) external tanks is 435 mls (700 km), including the missile’s range of 37-43 mls (60-70 km). This is achieved at a cruising speed of 400 kts (742 km/h), apart from the first 59 mls (95 km) of the homeward flight, which are flown at 550 kts (1 019 km/h). Radius can be increased to 559 mls (900 km) with one “buddy” refuelling. A larger, 484 Imp gal (2 200 lt), tank is also available, but can be fitted only singly on the centreline pylon and has hitherto been employed mainly for ferrying. With one large and two small tanks and a H1-LO-HI mission profile, the Mirage F.IE’s radius may be increased to 870 mls (1 400 km), but only if the Magics and ECM pods are left at home and the weapon load reduced to just two 250-kg (55l-lb) bombs.
Production of the AM.39 Exocet armed Mirage F.1-EQ6 for the Iraqi Air FoU continued until late 1988. The French Air Force has received the last of its Mirage F.1-CR-200 reconnaissance fighters.
The specialized reconnaissance model is the Mirage F.1CR (based on the Mirage F.1C-200 and with a secondary attack capability) and this replaced the 50 or so Mirage IIIR/RD aircraft which equiped the 33e Escadre at Strasbourg, the French air force’s sole tactical reconnaissance unit. Selected in February 1979, two Mirage F.ICR prototypes were produced for test duties, the first making its maiden flight on 20 November 1981. These two machines being followed by 62 production examples. Mission-related equipment includes OMERA cameras carried internally together with an infra-red sensor, while additional electromagnetic or optical sensors can be housed in an external pod fitted beneath the aircraft’s belly. Air-to-air missiles can also be carried for defensive purposes, while inflight-refuelling gear is also fitted as standard.

First flown on 22 December 1974, and built as an engine test bed under official contract, the Mirage F1.M53 was also envisaged as the basis for a contender in the contest to find a successor for the Lockheed F-104G in service with Belgium, Denmark, the Netherlands and Norway. Evolved from the basic Atar 9K-50 turbojet-powered Mirage F1C, the Mirage F1.M53 – referred to for a brief period as the “F1E”, the suffix letter signifying Exportation and the designation subsequently being reassigned – was powered by the SNECMA M53 turbofan rated at 5550kg dry and 8500kg with maximum afterburning. M53 installation involved significant fuselage structural redesign, and to provide suitability for ground attack and long-range interdiction tasks in addition to that of interception, provision was made for multi-role avionics. By comparison with the F1C, the F1.M53 had increased fuel capacity, enlarged engine air intakes and strengthened undercarriage. The nose profile was revised to provide for the introduction of a retractable flight refuelling probe. The installed armament remained two 30mm cannon and it was proposed to distribute up to 4000kg of ordnance between seven external stations. The other contenders for the multi-national fighter contract were the Saab 37 Viggen and the General Dynamics F-16. With choice of the F-16 as winner of the competition, plans to produce a second prototype F1.M53 for testing and integration of systems were discarded.

Variants of the basic aircraft offered for export, in addition to the F1C, were the F1A with simplified avionics for operation under VFR conditions and the F1E multi-role air superiority/ground attack/reconnaissance version. Export customers were Ecuador (16 F1AJs), Greece (40 F1CGs), Iraq (113 F1EQs), Jordan (17 F1CJs and 17 F1EJs), Kuwait (27 F1CKS), Libya (16 F1ADs and 16 F1EDs), Morocco (30 F1CHs and 20 F1EHs), Qatar (12 F1EDAs), South Africa (32 F1AZs and 16 F1CZs) and Spain (45 F1CEs and 22 F1EEs). Production of the Mirage F1 was completed in 1990 with 731 built (including F1B and F1D two-seat trainers and F1CR reconnaissance aircraft). In 1991, work began on the adaptation of 30 F1C-200S as F1CT ground attack fighters.

In the 1991 Gulf War, the Mirage F1 was operated on both sides. In the 1980s Dassault sold a large number of Mirage F1E and some F1B aircraft to Iraq (designated F1EQ and F1BQ respectively). When coalition forces struck numerous hardened aircraft shelters to neutralize the Iraqi Air Force in support of operation Desert Storm, many of these aircraft were destroyed. Taking part in the coalition was France, supporting air operations with F1CR and F1CT aircraft.

The last French F1 Mirage was retired from active service in June 2014, and stored at Châteaudun air base, near Paris, while waiting for a buyer. Replaced in the French Armée de l’air by the Dassault Mirage 2000 and Dassault Rafale, it was still in use in five air forces around the world. Draken International was after the retired French planes. Instead, in December 2017, it acquired 22 Mirage F1 fighter jets from the Spanish Air Force.

Gallery

Mirage F1C
Powerplant: one 70.21 kN (15,873 lb st) SNECMA Atar 9K-50 turbojet
Length 15.23m (49 ft 11½ in)
Height 4.50m (14 ft 9 in)
Wing span (over tip missiles) 9.32m (30 ft 10 in)
Wing area: 25 sq.m / 269.10 sq ft
Empty weight: 7400 kg / 16314 lb
Max Take-Off Weight 16.200 kg (35,714 lb)
Max level speed at 12,000m (39,370 ft) Mach 2.2 or 2350 km/h (1,460 mph)
Landing speed: 124 kts / 230 km/h
Cruising speed: 478 kts / 885 km/h
Initial climb rate: 41338.58 ft/min / 210.0 m/s
Service ceiling 20,000m (65,615 ft)
Range w/max.payload: 900 km / 559 miles
Armament: two DEFA 553 30mm cannons (135 rounds/gun), up to 4000 kg (8,818 lb) ordnance
Hardpoints: 7
T/O run: 670 m.
Ldg run: 610 m.
Combat radius lo-lo-lo: 740 km.
Fuel internal: 4300 lt.
Air refuel: Yes.
Crew: 1

Mirage F.1CR
Powerplant: one SNECMA Atar 9K-50 turbojet rated at 7200-kg (15,873-lb) afterburning thrust.
Maximum speed at sea level 1475 km/h (917 mph) or Mach 1.2
Maximum. speed at altitude 2335 km/h (1450 mph) or Mach 2.2
Ferry range 300 km (2,050 miles)
Empty weight 7400 kg (16,314 lb)
Maximurn take-off 16200 kg (35,715 lb)
Wingspan 8.40 m (27 ft 6¾ in)
Length 15.00 m (49 ft 2½ in)
Height 4.50 m (14 ft 9 in)
Wing area 25.00 sq.m (269.1 sq.ft)

Mirage F.1E
Engine: one 15,873-lb (7,200-kg) reheated thrust SNECMA Atar 9K-50 turbojet.
mximum speed, clean Mach 2.2 speed (1,321 mph / 2,125 km/h) at 36,090 ft (11,000 m)
Initial climb rate 39,370 ft (12,000 m) per minute
Service ceiling 20000 m (65,615 ft)
Endurance 3 hours 45 minutes
Radius 265 miles (425 km) on a hi-lo-hi mission with a 7.716-lb (3,500-kg) warload.
Empty weight 7400 kg (16,314 lb)
Maximum take-off 16200 kg (35,714 lb)
Wingspan 8.40 m (27 ft 6 ¾ in)
Length 15.00 m (49 ft 2 ½ in)
Height 4,50 m (14 ft 9 in)
Wing area 25.00sq.m (269.1 sq ft).
Armament: two 30-min DEFA 553 cannon (125 rpg) up to 4000 kg (8,818 lb) ordnance

F1.M53
Max take-off weight: 15200 kg / 33510 lb
Empty weight: 8024 kg / 17690 lb
Wingspan: 8.45 m / 27 ft 9 in
Length: 15.53 m / 50 ft 11 in
Height: 4.56 m / 14 ft 12 in
Wing area: 25.00 sq.m / 269.10 sq ft
Max. speed: 2335 km/h / 1451 mph
Range: 1200 km / 746 miles

Dassault Mirage F.2

24/01/2024TerryLeave a comment

In 1964 Dassault received a contract to develop a successor to the Mirage III for the low-altitude penetration role, and an order followed for a single prototype of a tandem two-seat aircraft. The intended powerplant was a SNECMA (Pratt & Whitney) TF-306 turbofan. The new fighter featured a high-mounted swept wing with horizontal tail surfaces, and was assigned the designation Mirage F2. It was first flown on 12 June 1966 with a Pratt & Whitney TF30 turbofan rated at 8400kg with afterburning. After being re-engined with a TF-306 of 9000kg, it attained M=2.0 on its second flight, on 29 December 1966.
Work had begun on a single-seat version, the Mirage F3 with a 10350kg TF-306E engine, but changes in Armee de l’Air requirements saw interest transferred to a simpler version of the basic Mirage F1. Development of which had been pursued in parallel by Dassault, and further development of the Mirage F2 was discontinued.

Engine: 1 x Pratt & Whitney TF30 turbofan, 9000kg
Take-off weight: 18000 kg / 39683 lb
Empty weight: 9500 kg / 20944 lb
Wingspan: 10.5 m / 34 ft 5 in
Length: 17.6 m / 57 ft 9 in
Height: 5.8 m / 19 ft 0 in
Max. speed: 2333 km/h / 1450 mph
Ceiling: 20000 m / 65600 ft

Dassault Mirage 2000

24/01/202426/05/2025TerryLeave a comment

The Mirage 2000 high-performance fighter delta wing used a design with relaxed stability, a variable-camber (produced by two-section leading-edge slats and trailing-edge elevons) and a “fly-by-wire” computerized control system in an airframe that makes extensive use of composite materials.
Developed initially as a single-seat interceptor and air superiority aircraft designated 2000C, the first of four prototypes was flown on 10 March 1978. A company-funded fifth prototype, in tandem two-seat trainer 2000B form, flew on 11 October 1980.
The Mirage 2000 was chosen on 18 December 1975 to become the next primary combat aircraft of the Armee de l’Air, to replace the Mirage III is the interceptor role.

Dassault Mirage 2000 Article

The first production Mirage 2000C flew on 20 November 1982 with a SNECMA M53-5 rated at 5547kg dry and 8790kg with afterburning, this being replaced from the 38th Armee de l’Air Mirage 2000C by the M53-P2 turbofan producing 6557kg dry and 9687kg with afterburning. Armament consisted of two 30mm cannon with a typical intercept weapons mix comprising two Matra 530D or 530F AAMs inboard and two Matra 550 Magic missiles outboard under the wings. For an attack mission, up to 6300kg of ordnance could be distributed between nine external stations.
Deliveries of the initial 37 Mirage 2000C to the first of four Escadres de Chasse began in the summer 1983, this attaining operational capability on 2 July 1984.

The dedicated air-defense Mirage 2000C with an advanced electronic countermeasures system, a “look-down/shoot-down” radar, and a mix of air-to-air missiles with infra-red or semi-active radar guidance, with an active radar-guided type to follow, can also be used in the attack role. The 2000C was also produced in a number of differently suffixed sub-variants for export.
Mirage 2000C aircraft have flown CAP missions during the Gulf War alongside other coalition fighters. The Mirage 2000 also saw action over Bosnia and Kosova in support of NATO.
In 1987, the Dassault company offered a private venture two-phase Mirage 2000 update programme. The first phase, the Mirage 2000-3 with Rafale-type cockpit multifunction displays, flew on 10 March 1988, and the addition of a new central processing unit, an updated head-up display and Thomson- CSF RDY multi-mode radar resulted in the second phase Mirage 2000-5, flown on 24 October 1990.

In 1990 a major upgrade of the 37 Mirage 2000C design resulted in the multi-role Mirage 2000-5F which was first flown on 24 October 1990 and was also ordered by Taiwan. The 2000-5 is a multi-role variant capable of using the Super 530D or Sky Flash air-to-air missiles.

In 1979 Dassault was contracted to build two prototypes designated Mirage 2000P, later Mirage 2000N. The 2000P was being developed for the low-altitude tactical nuclear strike mission to replace the fleet of nuclear-armed Mirage IVPs. The Mirage 2000N made its first flight on 3 February 1983.
Based on the Mirage 2000B two-seat trainer variant, the 2000P has a revised avionics suite and strengthened fuselage for the low-altitude role and the Antilope 5 nose radar optimised for terrain following, ground mapping and navigation and has additional air-to-air and air-to-sea modes. The rear seat is occupied by a WSO which has twin inertial platform navigation systems, a radar altimeter, ECM, a vertical camera, and an additional moving map. The aircraft configured with only the ASMP missile and 2 Magic AAMs is designated 2000N-K1, while the K2 configuration can also carry alternative loads.

Lessening tensions in Europe in the late 1980s reduced the need for nuclear capable aircraft and the orders for the Mirage 2000N were reduced to 75 aircraft. Delays with the Rafale program resulted in a need for additional aircraft with a capability for conventional weapons. This resulted in the Mirage 2000D originally known as Mirage 2000N’ (or N Prime). Developed from the 2000N-K2 is the Mirage 2000D, equipped with GPS it is developed for the use of laser guided weapons, but is not capable of carrying the ASMP missile. The 2000D-R1N1L is equipped with laser guided weapons and Magic AAMs only, while the R1 configuration can be equipped with the full range of conventional weapons. The R2 configuration is upgraded with a fully integrated self-defence suite and is compatible with the Apache stand-off weapons dispenser.

The first Mirage 2000D was flown on 19 February 1991 and the first of 86 aircraft ordered entered service in April, 1993.
Mirage 2000D aircraft flew combat missions over Afghanistan equipped with laser targeting pods and laser guided bombs or free fall 250kg bombs.
The export model of the Mirage 2000D is designated 2000S, where the S stands for Strike.
Mirage 2000-9 is the designation for the upgraded version of the Mirage 2000 export models of the United Arab Emirates.
Dassault marketed the Mirage 2000-5 Mk.2 either as a new aircraft or retrofitted from currently operated Mirage 2000Cs or 2000Es. It features an integrated mission system with a glass cockpit, digital modular avionics and enhanced communications.

A cockpit development aircraft was designated BX1.
To 1990, more than 260 have been delivered, including the two-seat B and N variants, and more than 160 export Mirage 2000s had been ordered by six nations.
The Mirage 2000 single-seat fighter export customers included Abu Dhabi (22 2000EADs), Egypt (16 2000EMs), Greece (36 2000EGs), India (42 2000Hs), and Peru (10 2000Ps).
At the beginning of 1993, planned Armee de l’Air procurement of the Mirage 2000 totalled 323 aircraft, including 136 single-seat Mirage 2000Cs.

Gallery

Variants:
2000A (prototype)
2000B
2000C
2000-5
2000-5F
2000E
2000ED
2000ER
2000P
2000N
2000D
2000S
2000-9
2000 BX1

Specifications:

Dassault Mirage 2000
Engine: SNECMA M53-5, 88290 N / 9000 kp
Length: 50.295 ft / 15.33 m
Wingspan: 29.528 ft / 9.0 m
Wing area: 430.56 sq.ft / 40.0 sq.m
Max take off weight: 33075.0 lb / 15000.0 kg
Max. speed: 1320 kts / 2445 km/h
Wing load: 76.88 lb/sq.ft / 375.0 kg/sq.m
Range: 378 nm / 700 km
Crew: 1
Armament: 5000 kg. ext. 9 Pods.

Mirage 2000
Engine: 1 x Snecma M53-P2.
Installed thrust (dry / reheat): 64.5 / 95 kN.
Span: 9 m.
Length: 14.4 m.
Wing span: 29.5ft (9m).
Wing area: 41 sq.m.
Empty wt: 7500 kg.
MTOW: 17,000 kg.
Warload: 6300+ kg.
Max speed: 2.2 Mach.
Initial ROC: 18,000 m / min.
Ceiling: 18,000 m.
T/O run: 430 m.
Combat radius: 740+ km.
Fuel internal: 3800 lt.
Air refuel: Yes.
Armament: 2 x 30 mm, 4 x AAM
Hard points: 9

Mirage 2000C
Engine: one SNECMA M53-P2 turbofan, 21,385-lb (9,700-kg) reheated thrust.
Maximum speed 1,453+ mph(2,338+ km/h) or Mach 2.2+ at 36,090 ft (11,000 m)
Initial climb rate 56,000 ft (17,060 m) per minute
Service ceiling 59,055 ft (18,000 m)
Range 920 miles (1,480 km)
Range w/max.fuel: 3335 km / 2072 miles
Empty weight 16,534 lb (7,500 kg)
Maximum take-off 37,480 lb (17,000 kg)
Wingspan 29 ft 11.5 in (9.13 m)
Length 47 ft 1.25 in (14.36 m)
Height 17 ft 0.75 in (5.20 m)
Wing area 441.3 sq ft (41.00 sq.m)
Armament: two DEFA 554 30-mm cannon (125 rounds/gun), up to 13,890 lb (6,300 kg) of disposable stores.
Hardpoints: 9

Mirage 2000N-K2
Engine: one SNECMA M53-P2 turbofan 95.1 kN (21,385 lb st) afterburning
Length 14.55m (47 ft 9 in)
Height 5.15m (16 ft 10¼ in)
Wing span 9.13m (29 ft 11½ in)
Empty weight 7600 kg (16,755 lb)
Max Take-Off Weight 17.000 kg (37,480 lb)
Max level speed at 11.000m (36,069 ft) Mach 2.2 or 2338 km/h (1,453 mph)
Service ceiling 16,460m (54,000 ft)
Armament: one 900kg (1,984lb) ASMP tactical nuclear missile; up tp 6300 kg (13,889 lb) of ordnance
Hardpoints: 9

Dassault Mirage IV

24/01/202424/01/2024TerryLeave a comment

In 1954 the French Government elected to create their own nuclear deterrent force. Development of a launch platform for the weapons was headed by Dassault with a requirement for a long-range high-speed mission to be met. Basically a scaled-up Mirage III, the project redesign considered many changes in size and powerplant, but the solution was found with inflight-refuelling.

Dassault Mirage IV Article

The first Dassault Mirage IVA prototype flew on 17 June 1959, then powered by two 13,225 lb / 6000kg SNECMA Atar 09 augmented turbojets. On its 14th test flight during July1959 it reached Mach 1.9, and attained Mach 2 on its 33rd flight. The prototype set up an international speed record of 1132 mph over a 620 mile circuit in 1960.

Three pre-production prototypes followed, the first of which flew on 12 October 1961. Powered by a pair of 6400kg Atar 9Cs, this aircraft was larger and more representative of the production Mirage IVA, incorporating a large circular radome under the centre fuselage forward of the semi-recessed nuclear free-fall bomb.

The first of these pre-production aircraft was used for bombing trials and development at Colomb-Bechar; the second similar aircraft was used to develop the navigation and inflight-refuelling systems; and the third, a completely operational model with Atar 9Ks, full equipment including nose-probe for refuelling and armament, flew on 23 January 1963.

The French air force ordered 50 production aircraft for delivery in 1964-5, with a repeat order for a further 12 placed later for the French Air Force’s Force de Frappe.

The useful radius of 1,000 miles (1,610 km) can be extended by in flight refuelling. By 1967 all had entered French Air Force service, each carrying a free fall nuclear bomb under the fuselage.

By 1985, about 50 IV As remain operational. Most deployed as tactical bombers with strategic capability, carrying either a nuclear weapon or 1,000 lb of bombs, although a very small number have been mod strategic reconnaissance aircraft.

The IV A has received in-service modifications permitting it to be used for low level as well as high level bombing missions.

Dassault is converting 18 Mirage IVAs to carry the medium-range air-to-surface (ASMP) nuclear missile as Mirage IVPs. An avionics upgrade, including the fitting of a Thomson-CSF Arcana pulse-¬Doppler radar and dual inertial systems, improved navigation and attack capabilities. The Mirage IVP will also have an improved elec¬tronic warfare system with upgraded jamming pods and chaff dispensers carried on the outer wing pylons.
The last of nine Mirage IVA strategic bomber units disbanded in July 1988 with passing of the French nuclear deterrent to silo-based S-3 strategic missiles. However, two units still operate remaining Mirage IVPs (P= Penetration) of 18 upgraded between May 1983 and December 1987 to carry the ASMP medium-range nuclear-tipped air-to-surface missile. Mirage IVPs have Arcana pulse doppler radar, dual inertial navigation systems, a Thomson-CSF Barem self protection jamming pod, a BOZ-100 chaff/flare pod and Thomson-CSF Serval radar warning receivers. Eighteen unconverted Mirage IVAs remained in store.

Production totaled 62 aircraft plus four prototypes.

The Mirage IV was retired from operational service in 2005.

Engine: 2 x SNECMA Atar 09K-50 afterburning turbo¬jet, 15400 lb (7000kg) thrust.
Wing span: 38 ft 10.5 in (11.85 m).
Length: 77 ft 1 in (23.50 m).
Wing area: 840 sq ft (78.0 sq.m).
Height: 5.4 m / 17 ft 9 in
Empty weight: 14500 kg / 31967 lb
Gross weight: 69,665 lb (31,600 kg).
Max speed: 1,450 mph (2,335 km/h) at 36000 ft (11 000 m).
Cruise speed: 1966 km/h / 1222 mph
Ceiling: 20000 m / 65600 ft
Range: 2480 km / 1541 miles
Range w/max.fuel: 4000 km / 2486 miles
Armament: 1 x 60kt nuclear bomb or 7260kg of weapons
Crew: 2.

All Aero

A large aeronautical archive.

Davis D-1

Davis Aircraft V-3 / Vulcan Aircraft V-3

Dassy DA 1 / DA 2

Dassault-Breguet / Dornier Alpha Jet

Dassault Rafale

Dassault Mirage 4000

Dassault Mirage F.1

Dassault Mirage F.2

Dassault Mirage 2000

Dassault Mirage IV