Convair 880

In 1955 Convair went ahead with the Model 22 Skylark, seating 80-108 passengers over sectors up to about 2,500 miles. It was announced in September 1956. During construction the aircraft was renamed Golden Arrow, and it was proposed to anodise the external skins gold. Then, because it was to cruise at 600 mph, the type became the Convair 600, and finally this was changed to Convair 880, because 600 mph is 880ft per second. The aircraft grew slightly in weight, the 880M weighing 193,000lb with 11,650-lb thrust CJ805-3B engines. Designed at the request of Howard Hughes, the owner of TWA, the first 880 made its maiden flight on January 27, 1959 and was technically a very advanced aircraft. Powered by four 49.8kN (11,2001b) st CJ 805 3s it had a boldly swept (35 degrees) wing and was a very fast aircraft indeed, justifying the much hyped claim that it was ‘the fastest airliner in the world’.

Convair 880 Article

At the time of the first flight, 78 Convair 880 variants were on order.

The second aircraft off the line flew on 31 March 1959.

The FAA certified the 880 for airline use on 1 May 1960, and 15 days later Delta Airlines put the liner into commercial service.

It was built in two versions: the 880 Model 22 basic model with 49.8kN General Electric CJ-805-3 turbojet engines, flown for the first time on 27 January 1959; and the 880 Model 22-M with 51.8kN CJ-805-3B turbojets, power-boosted rudder and four leading-edge slats. The first 880 Model 22-M flew on 3 October 1960.
The first aircraft completed to full airline standards (number 7) actually broke a transcontinental speed record on delivery from San Diego to Miami. TWAs aircraft were stored while the airline’s ownership was hotly disputed and Delta gained the honour of initiating the first services on 16 May 1960.

TWA became the largest operator of the type, with deliveries beginning two days after Howard Hughes relinquished control of the airline, on December 30, 1960. Subsequently, Convair 880s were also delivered to Northeast Airlines, though a massive, once nearly firm order from United, was lost to Boeing.

TWA was taking delivery of 20 Convair 990 during 1960 and 1961.

Some 17 Convair 880Ms were built, these having four leading edge slats on each wing, a larger fin and powered rudder, a retractable tailskid, provision for pre loaded baggage containers and a 7,094 lit (1,560 Imp gal) centre section tank. The aircraft also had a strengthened undercarriage and CJ 805 313 engines.

The oil crisis of the early 1970s made the Convair 880 particularly uneconomical to operate and Delta retired its aircraft at the end of 1973, followed by TWA in June 1974. New operators included LANICA in Nicaragua, a number of travel clubs and even Elvis Presley, whose aircraft, named Lisa Marie after his daughter, and callsign Hound Dog One is now part of the Graceland museum. Airtrust Singapore operated three Convair 880Ms until 1979, latterly operating services for Air Malta. Another aircraft was sold to the Ciskei Government.

A number of Convair 880s were briefly used as freighters. Monarch Aviation converted about seven with a cargo door and more without the door. American Jet Industries (later part of Gulfstream American) worked closely with Convair to convert some 20 Model 880s as Airlifters, but the company completed only two aircraft and the remainder were stored at Mojave, many with unused cargo doors installed. Attempts to market the aircraft in the mid 1980s foundered because they were not hush kitted. General Air Services converted one more Convair as a freighter. The last freighter flying was probably retired (in about 1986) in Haiti.

The last aircraft in regular service was the US Navy’s sole UC 880, ‘Old Smokey’, equipped as a tanker, and for missile test control and telemetry. This was retired at the NATC, Patuxent River, in September 1993 and in 1995 was used for ground based tests simulating high-altitude bomb explosions. Some 15 aircraft remained in storage at Mojave in 1998.
Total sales were 65.

Gallery

880 Model 22
Engines: 4 x General Electric CJ805-3 turbojet, 5080 kg / 49.8kN / 11,200 lb thrust.
Max level speed: 615 mph (990 kph).
Cruising speed 482kts (895km/h) at 35,000ft (10,668m).
Range 6,518km (3,513nm).
Weight empty 42,185kg (93,000 lb).
Gross weight 87,772kg (193,500 lb).
Span 36.5m (120ft 0m).
Length 39.4 m (129ft 4in).
Height: 36 ft 0 in (10.97 m).
Wing area 185.8sq.m (2,000 sq.ft).

880 Model 22-M
Engines: 4 x General Electric CJ805-3B turbojet, 5285 kg / 51.8kN / 11,650-lb thrust.
MTOW: 87410 kg / 184,500 lb.
Empty wt. 88,615 lb
Top speed 615 mph.
Cruise 501 mph.
Stall 121 mph.
Initial climb rate 3,565 fpm.
Range 3,995 miles.
Ceiling 41,000 ft.
Takeoff run 8,050 ft.
Landing roll 6,150 ft.
Pax cap: 110.
Crew: 5.
Max fuel cap: 47445 lt / 12,534 USG

Convair XFY-1 Pogo

From 1949 the US Navy actively pursued a policy of VTOL research. The results were two prototypes, the Lockheed XFV-1 and the Convair XFY-1 Pogo. Both aircraft were of the ‘tail-sitter’ concept and powered by the 5500-shp (4101-kW) Allison T40-A-6 turboprop driving large contra-rotating propeller units. These provided more thrust than the weight of the aircraft, making possible VTOL operation.

The XFY-1 was a swept delta design with large dorsal and ventral fins, all four surfaces of this cruciform arrangement carrying castoring wheels to support the aeroplane vertically on the ground. This arrangement of flying surfaces made it impossible to fit the XFY-1 with the same type of conventional landing gear as the XFV-1, so Convair received the only example of the T40 turboprop cleared for VTOL operation.

The pilot is seated in a gimbal-mounted seat which tilts forward 45 degrees when the aircraft is in the vertical position, returning to normal when horizontal flight is attained.

The Pogo made its first free VTOL flight on 1 August 1954 and in October made its first transition from free vertical to horizontal flight and back. The flight test programme was very successful in overall terms, but like that of the XFV-1 confirmed that exceptional piloting was necessary for such a tail-sitter type.

The aircraft had little castoring wheels on their fins on which they stood, towering nearly 12.2 m (40 ft) above the ground, and wingtip weapon pods.

The Pogo was equipped with a custom fitted clamshell ‘hangar’ which locked around tile aircraft and made it independent of airfield facilities so that it could be stationed anywhere.

Extensive tethered tests from a special rig were followed by a first vertical take-off and landing on 1 August 1954. Testing continued with a series of similar vertical flights before the first complete transition from vertical to horizontal flight and vice versa was accomplished on 2 November 1954. Although some 40 flight hours were accumulated by two prototypes of this experimental fighter, its development was abandoned.
The aircraft did not get beyond preliminary testing.

Gallery

Engine: 1 x Allison YT40-A-6 turboprop, 4362kW / 5500 shp
Wingspan: 8.43 m / 27 ft 8 in
Length: 10.66 m / 34 ft 12 in
Height horizontal: 30 ft 9in
Wing area: 32.98 sq.m / 354.99 sq ft
Max take-off weight: 7371 kg / 16250 lb
Empty weight: 5345 kg / 11784 lb
Loaded weight: 10,000-11,000 lb
Max. speed: 982 km/h / 610 mph
Ceiling: 13320 m / 43700 ft
Armament: 4 x 20mm cannon (proposed) or 46 x 70mm rockets

Convair 8-24 / F-106 Delta Dart

F-106A

The Convair F-106 Delta Dart began its production life as a direct successor to the interim F-102 Delta Dagger, as the F-102B, built around the advanced Hughes-produced MA-1 fire control system. The F-106 retained many design elements of the F-102 including a small internal bomb bay. Nuclear capability with twin Genie nuclear-tipped missiles was a standard design initiative. An internal 20mm cannon would not be fitted to the system until 1973, when it was found throughout engagements in the Vietnam conflict that close-range fighting was still involved.

The F-106 has mid-set delta wings, with 60 degrees sweepback, no tailplane, and square-top fin and rudder.
Engine air intakes are on each side of the fuselage just forward of the wing leading edges.

The tricycle undercarriage has a single wheel on each main unit and twin nose-wheels. The nosewheels retract forward.

Convair F-106 Article

While development of the earlier fighter was delayed by various teething troubles in 1955-6, progress with the later machine became possible with the development of the Hughes MA-1 integrated fire-control system. In November 1955, the USAF placed an order for 17 F-102Bs and in December, a mock-up of the proposed cockpit with radically new equipment and pilot displays was completed. On 17 June 1956, the F-102B was redesignated F-106.

The first of two YF-106A service-test aircraft (56-451/452) flew on 26 December 1956 at Edwards AFB, California. Like most new fighter types in the ‘century series’, the F-106 was initially a disappointment. Maximum speed, rate of climb and overall acceleration were significantly below Air Defense Command expectations with the Pratt & Whitney J57-P-9 turbojet employed in the initial machines and the Wright J67, licence-built Olympus, being contemplated. When the latter powerplant failed to materialise, the USAF reduced its requirement from 1,000 to 360 of the new interceptors.

The first flight of the F-106B two-seat trainer was made in April 1958.

F-106B

An F-106A held the world speed record of 1525.05 mph from 15 December 1959 until the autumn of 1961.

Performance was improved with the installation of the 7800kg thrust Pratt & Whitney J75-P-17 turbojet which could provide 11100kg thrust with afterburning.

F-106A

The F-106A attained its initial operating capability with the 498th Fighter-Interceptor Squadron at Geiger AFB, Washington, in October 1959 and subsequently served with 15 ADC and eight Air National Guard squadrons. Except for brief deployments to Europe and to Korea in 1968, the type served exclusively in North America. Totals of 277 F-106A single-seat interceptors served in company with 63 F-106B two-seat combat trainers, 340 machines actually being completed, and the types remained on active duty until 1982.

Gallery

Convair F-106A Delta Dart
Engine: 1 x Pratt & Whitney J75-P-17 turbojet, 17,500 lb / 24,500 lb with afterburner.
Length: 70 ft 10 in (21.55m)
Wingspan: 38 ft 5 in (11.67m)
Wing area: 64.8 sq.m / 697.50 sq ft
Wing load: 55.76 lb/sq.ft / 272.00 kg/sq.m
Height: 20 ft 4 in (6.18m)
Wheel track: 15 ft 5.5 in
Wheelbase: 24 ft 1.5 in
Empty Weight: 24,859lbs (11,276kg)
Maximum Take-Off Weight: 41,831lbs (18,974kg)
Maximum Speed: 1,487mph (2,393kmh; 1,292kts)
Cruising speed: 529 kts / 980 km/h
Cruising altitude: 41011 ft / 12500 m
Maximum Range: 1,950miles (3,138km)
Rate-of-Climb: 30,000ft/min (9,144m/min)
Service Ceiling: 58,005ft (17,680m; 11.0miles)
Armament: 1 x 20mm cannon
Hardpoints: 4 for:
2 x AIR-2A Genie Nuclear Rockets or
4 x AIM-4 Falcon Air-to-Air Missiles
Accommodation: 1

Convair 8 / F-102 Delta Dagger

The Convair F-102 Delta Dagger resulted from a 1950 USAF design competition for an integral all-weather interceptor weapon system. Combining the Hughes Falcon air-to-air missile, the 60 degree sweep delta wing platform first flown on the XF-92A, and the 4944kg thrust Pratt & Whitney J57-P-11 turbojet, the first of 10 YF-102s (52-7994/7995 and 53-1779/1786) flew at Edwards AFB, California, on 24 October 1953, piloted by Dick Johnson. The prototype was lost in a mishap nine days later.

YF-102 (nearest), F-102 (rear)

The YF-102 was not a success, proving unable to maintan supersonic speeds in level flight. The fuselage was completely redesigned into a ‘coke bottle’ shape using the area rule concept, and a more powerful engine installed. The indented fuselage or ‘area rule’ configuration was developed by NACA’s Richard Whitcomb was introduced in the much-altered YF-102A, which was assembled in 117 days.

The first of four YF-102As (53-1787/1790) flew at Edwards AFB on 20 December 1954, again piloted by Dick Johnson, not merely with ‘area rule’ but with cambered wing, new canopy (except on 53-1788) and 5443kg thrust Pratt & Whitney J57-P-23. The new design was supersonic and met USAF expectations.

Development included the introduction pf a larger fin from the 23rd production aircraft.

Convair F-102 Delta Dagger Article

The primary weapon was the Hughes AIM-4 Falcon air-to-air missile, coupled with the Hughes MG-10 fire control system. Introduced later was the AIM-26, some nuclear tipped.

YF-102

The production F-102A began to reach Air Defense Command squadrons in June 1955. The first two-seat TF-102A combat proficiency trainer (54-1351) flew at Edwards AFB 8 November 1955 and operated alongside F-102As in ADC service.

Service entry began with the first examples delivered in April 1956 to the 327th Fighter Interceptor Squadron (FIS) at George, California.
The F-102B designation was briefly assigned to a new aircraft completed as the F-106. The little-known YF-102C (53-1806), a converted F-102A model, tested change in the internal fire control system, but these were not adopted.

The F-102A eventually served with 32 ADC and 21 States ANG squadrons. Air Defense Command machines went through several modernisation programmes before being relegated to the ANG, the internal provision for rockets being eventually omitted. A few F-102As went to Greece (20 F-102A and 4 TF-102A) and Turkey (40 F-102A and 9 TF-102A).

1964 on arrival at Saigon, Vietnam

A few camouflaged F-102As were deployed to South East Asia in 1964-6, and to Korea in 1968 but, while they flew a few missions over North Vietnam, they are not thought to have actually been in combat. No air-to-air kills were achieved but one F-102A was shot down by a MiG-21 on 5 February 1968.

F-102A

Most F-102A squadrons had converted to other types by the end of 1971. The last US operational user was the Hawaii Air National Guard’s 199th FIS which received its first F-4C Phantom replacement in October 1975.
Greece retired their F-102As in 1979, with Turkey withdrawing its last 13 fighters and five trainers on 5 June 1979.
In March 1973, the USAF awarded Sperry a contract to convert an initial 6 F-102As as a fully manoeuvrable manned or unmanned target drones under the Pave Deuce programme as PQM-102As. Over 200 were eventually converted, operating until 1986.
Numerous F-102A airframes have been saved, the 199th Fighter Interceptor Squadron of the Hawaii Air National Guard having retained no fewer than four non-flyable F-102As for display purposes after transitioning to the F-4C Phantom.

Total Delta Dagger production was exactly 1000 airplanes built at San Diego’s Lindbergh Field, comprising 10 YF-102, 4 YF-102A, 875 F-102A and 111 TF-102A trainers.

Gallery

Convair F-102A Delta Dagger
Engines: 1 x Pratt & Whitney J57-P-23 turbojet, 17,200 lb (5307/7802kp) thrust.
Length: 68 ft 4.5 in (20.84m)
Wingspan: 38 ft 1.5 in (11.62m)
Wing area: 695.031 sqft / 64.57 sq.m
Wing loading: 45.31 lb/sq.ft / 221.0 kg/sq.m
Height: 21 ft 2.5 in (6.46m)
Empty Weight: 19,026lbs (8,630kg)
Maximum Take-Off Weight: 31,500lbs (14,288kg)
Maximum Speed: 825mph (1,328kmh; 717kts) at 36,000 ft
Cruising speed: 469 kts / 869 km/h
Cruising altitude: 34449 ft / 10500 m
Maximum Range: 1,350miles (2,173km)
Rate-of-Climb: 17,400ft/min (5,304m/min)
Service Ceiling: 54,003ft (16,460m)
Armament:
6 x AIM-4A / AIM-4C Falcon Air-to-Air Missiles
2 x 2.75″ Rocket Pods (24-shot, unguided rockets)
Nuclear Capable munitions as needed.
Accommodation: 1
Hardpoints: 6

Convair F-102A Delta Dagger
Engine: 1 x Pratt & Whitney J57-P-35 turbojet, 10,900 dry, 17,000 lb afterburner
Wingspan: 38 ft 1.5 in (11.62m)
Wing area: 661.5 sq.ft
Length: 68 ft 4.5 in (20.84m)
Height: 21 ft 2.5 in (6.46m)
Wheel track: 14 ft 2.25 in
Wheelbase: 22 ft 4.5 in
Maximum Take-Off Weight: 27,000 lbs
Maximum Speed: 825 mph (1,328kmh; 717kts, M1.25) at 36,000 ft
Service Ceiling: 54,000 ft (16,460m)
Armament:
6 x AIM-4A / AIM-4C Falcon Air-to-Air Missiles
2 x 2.75″ Rocket Pods (24-shot, unguided rockets)
Nuclear Capable munitions as needed.
Accommodation: 1
Hardpoints: 6

Convair 7 / XF-92A

The Convair Model 7 submission was ordered in prototype form as the XF-92 to be powered by a 1600-lb (726-kg) thrust Westinghouse 130 turbojet supplemented for take-off and combat by a 6000-lb (2722-kg) thrust Reaction Motors LR-11 liquid-propellant rocket. This was a tailless delta type with mixed powerplant, and its wing was designed with the aid of Dr Alexander Lippisch. This would have been a very fast point-defence interceptor with exceedingly limited range and duration.

Validation of the basic design’s 60 degree swept delta wing (complete with full-span elevons for pitch and roll control) was entrusted to a smaller-scale aeroplane, the Model 7-002, which used components from five other aircraft and was powered by an Allison J33-A-23 turbojet. The Model 7-002 was generally successful, and development of the XF-92 proceeded without undue problems. In June 1949 the XF-92 was cancelled, but the Model 7-002 was kept in development as the XF-92A high-speed research aeroplane. Re-engined with the 6800-lb (3084-kg) J33-A-29 afterburning turbojet, the XF-92A eventually reached a speed of Mach 0.95 at 40,000-ft (12,190-rn). Meanwhile the LTSAF was completing the competition for the fire-control system originally specified for the XF-92, and this was later installed in the modestly supersonic F-102 Delta Dagger interceptor that was evolved as the Convair Model 8 on the aerodynamic basis of the XF-92A with the advanced Pratt & Whitney J57 afterburning turbojet.

The Convair made its first flight on 8 June 1948. This was a simple airplane with latticed canopy cover, nose air inlet, and through-flow arrangement for its 2358kg thrust Allison J33-A-23 turbojet. Its delta wing was swept 60 degrees. When the fully-fledged rocket-powered XF-92 design was cancelled because of its obviously limited military application, the model 7002 was redesignated XF-92A.

The XF-92A originally flew without afterburning. During continuing tests at Edwards AFB it was re-engined and its fuselage lengthened to provide reheat for the new 3402kg afterburning thrust Allison J33-A-29. At the same time, the natural-metal XF-92A was painted gloss white.

Always a research aircraft rather than a fighter, the XF-92A was turned over to NACA for tests before its flight career ended in 1953.

Since it had been intended only as a flying mock-up for the cancelled machine, the XF-92A was never a candidate for a production order, though it performed valuable, if unintended, service as a testbed for the company’s F-102 interceptor.

XF-92A
Engine: 1 x 3402kg afterburning thrust Allison J33-A-29 turbojet
Max take-off weight: 6800 kg / 14992 lb
Wingspan: 9.5 m / 31 ft 2 in
Length: 12.9 m / 42 ft 4 in
Wing area: 39.0 sq.m / 419.79 sq ft
Max. speed: 1000 km/h / 621 mph
Crew: 1

Convair 600 / 640

The prototype Convair 600 (a converted 240D) was powered by Rolls-Royce Dart R.Da 10 turboprops, and first flew on 12 May 1965.

N74850 1948 Convair 240-0 converted to 600 with RR Dart 542-4

About 240 aircraft were modified from Convair 240 (Convair 600) and Convair 340 / Convair 440 (Convair 640) with the Rolls-Royce turbo-props installed.

Engines: Rolls Royce Dart 10 Mk 542 4 turboprops, 2,750 shp.
Length: 74 ft 8 in.
Wingspan: 91 ft 9 in.
Speed: 309 mph.
Ceiling: 24,600 ft.
Range: 1,230 mls.

Convair 640
Engines: 2 x Rolls-Royce RDa. 10/1 Dart turbo-prop, 2256kW
Max take-off weight: 25855 kg / 57001 lb
Empty weight: 13733 kg / 30276 lb
Wingspan: 32.11 m / 105 ft 4 in
Length: 24.84 m / 81 ft 6 in
Height: 8.59 m / 28 ft 2 in
Wing area: 85.47 sq.m / 919.99 sq ft
Cruise speed: 465 km/h / 289 mph
Ceiling: 6000 m / 19700 ft
Range w/max.fuel: 3138 km / 1950 miles
Range w/max.payload: 1979 km / 1230 miles
Crew: 2-3
Passengers: 49-56

Convair 580 / CV5800

The Convair 580 is a turbine powered development of the Convair 340/440. Standard Pratt and Whitney R2800 piston engine (2,000hp) Convairs were converted to take a pair of Allison 501-D turboprop engines developing 2796kW (3750ehp) and driving four-bladed propellers. Development work was carried out by PacAero Engineering Corp, the extra power allowed a gross weight increase to 53,200 lb. for take off following some structural modification including an enlarged horizontal and vertical tailplane. The conversion line was opened at Pacific Airmotive Corp. Burbank, California, following certification in 1960. The last 580 was delivered in July 1969 after 170 aircraft had been converted. In all-passenger configuration it could carry 39 passengers.

Kelowna Flightcraft R&D Ltd., Allison Gas Turbine and General Dynamics teamed to launch the Convair 5800 Program. The Convair Model 340, 440, and 580 Airplanes were converted with a fourteen foot, three inch stretch to provide increased capacity. The 5800 is powered by the Allison 501-D22G (Series III) Propjet Engine, de-rated to 4300 TSHP.

CV5800

The CV5800 featured a reconditioned airframe with a projected life in excess of 100,000 hours, modern, all new lightweight electrical wiring, all new flight control system cables, dual point underwing pressure refuelling, roller floor system, and passenger, cargo, or Combi models with approved Class E cabin.

All have Honeywell EFIS Flight Decks. The passenger model 5800 has 78 seats, and wide body interior with overhead bins. The cargo versions have a 120 inch cargo door and pallets and containers are compatible with DC-9 and B-727 aircraft. There is a 9-G Tie-down system.

Convair CV5800 ex/C-131F, cn277

Gallery

CV580
Engines: 2 x Allison 501-D turboprop, 2796kW (3750ehp).
MAUW: 53,200 lb.

CV5800
Engines: 2 x Allison 501-D22G
Propellers: Hamilton Standard 54H60-164
Cruise speed: 325 mph
Range with 21,000 lb payload: 750 statute miles
Range with20,000 lb payload: 900 statute miles

Convair 106 Skycoach / Stinson 106 Skycoach

The Convair Model 106 Skycoach was an experimental four-seat light aircraft, designed and built by the Stinson Division of Convair. The Model 106 was a four seat cabin aircraft with a pusher engine, fixed spatted tricycle undercarriage and twin tail booms flanking the propeller. The three passengers and pilot sat in a cabin in the fuselage nacelle, which also housed the pusher 230 hp (170 kW) Franklin 6A8-225-B8 six-cylinder horizontally-opposed piston engine, driving a cooling fan and pusher propeller.

First flown in April 1946 (pilot: Bill Martin), flight testing was carried out at San Diego, but performance was found to be unexceptional. With a maximum speed of only 142 mph (123 kn; 229 km/h) the Model 106 was outclassed and Convair abandoned development, scrapping the sole prototype, (regn. NX40004, msn. 1), in 1947.

Model 106 Skycoach
Engine: 1 × Franklin 6A8-225-B8, 230 hp (170 kW)
Maximum speed: 142 mph (229 km/h; 123 kn)
Crew: 1
Capacity: 3 passengers

Convair R3Y Tradewind

Shortly after Reuben Fleet sold his interest in Consolidated Aircraft Corporation in March 1943 and the company was reorganised as Consolidated Vultee (Convair), the US Navy expressed interest in a new long-range multi-role flying-boat.

Convair’s proposal was for an aircraft powered by four turboprop engines, was the subject of a contract for two prototypes, awarded on 27 May 1946. Designated XP5Y-1, the new aircraft featured a slim fuselage for an aircraft of this class with a length-to-beam ratio of 10 to 1. it was powered by four Allison T40-A4 turboprops, each driving two contra-rotating, reversable propellers through a common gearbox. The type’s main role was anti-submarine warfare, and it was to have been fitted with advanced radar, ECM and MAD equipment in addition to carrying a heavy load of bombs, mines, rockets and torpedoes. The first aircraft was flown from San Diego on 18 April 1950, and in August the type set a turboprop endurance record of 8 hours 6 minutes. August was an eventful month for the XP5Y-1 as the US Navy decided to discontinue its development for maritime patrol, but to persevere with the basic design for use as a passenger and cargo aircraft.

Convair R3Y-1 Tradewind

Work continued, despite the loss of an XP5Y-1 in a non-fatal crash off San Diego in 15 July 1953 and the first R3Y-1 Tradewind flew on 25 February 1954. Major changes included the deletion of all armament and of tailplane dihedral, the addition of a 3.05m wide port-side cargo hatch aft of the wing and the provision of redesigned engine nacelles to accept the improved T40-A-10 engines. Cabin sound-proofing and air-conditioning were installed and pressurised accommodation provided for up to 103 passengers or, in medevac configuration, for 72 stretcher cases and 12 attendants; cargo payload was 24.4 tonnes (24 tons).
The R3Y-1 was a straight transport version, the R3Y-2 was the assault transport version with the hinged nose. It could also refuel jets in flight using two or four wing pods. The R3Y-2 had a nose loading door and integral hydraulic ramps. The opening door blocked the pilots’ forward view during beach operations.
The R3Y-1 ‘s performance was demonstrated on 24 February 1955 when one of the five aircraft built flew coast-to-coast at an average speed of 649km/h on delivery to the Navy Test Center at Patuxent River, Maryland. Similarly, on 18 October a 6 hour 45 minute record flight at an average 579km/h was accomplished between Honolulu and NAS Alameda, California. US Navy transport squadron VR-2 received the first of its mixed fleet of R3Y-1 and R3Y-2 flying-boats on 31 March 1956, but financial considerations and continuing problems with the engine/propeller combination, culminating in two in-flight separations of propellers and gearbox from an engine (on 10 May 1957 and on 2 January 1958), led to a curtailment of Tradewind operations. Squadron strength was first cut to two R3Y-1s and two R3Y-2s and the unit was finally disbanded on 16 April 1958.

R3Y-2

R3Y
Engines: 4 x Allison T40-A-10 turboprops, 4362kW, 5500 shp
Max take-off weight: 74843-79379 kg / 165001 – 175002 lb
Payload: 21750kg / 47951 lb
Wingspan: 44.42 m / 145 ft 9 in
Length: 42.57 m / 139 ft 8 in
Height: 13.67 m / 44 ft 10 in
Max. speed: 580 km/h / 360 mph
Cruise speed: 480 km/h / 298 mph
Range w/max.fuel: 6437 km / 4000 miles
Crew: 5
Passenger Capacity: 80 or 24 ton.

R3Y-1
Engines: 4x 5,500 h.p. Allison T40-A-4 coupled turboprops.
Wingspan: 145 ft
Length: 142 ft. 6 in
Loaded weight: 160,000 lb
Max. speed: 392 mph
Range: 4,500 miles at 300 mph
Accommodation: 103 troops, 92 stretchers and 12 attendants or 24 tons of cargo.

Convair XF2Y Sea Dart

Convair was selected to produce a waterplane interceptor, and the result was XF2Y Sea Dart. The company was instructed to investigate the ‘blended hull’ concept, in which the hull rode so low in the water that the wings provided part of the required buoyancy until the aeroplane had accelerated sufficiently to rise onto a planing bottom, while the National Advisory Committee for Aeronautics (from 1958 the National Aeronautics and Space Administration) investigated the hydro-ski concept. When extended, the hydro-skis lifted the accelerating aeroplane onto the surface of the water, where the skis planed and so allowed the aeroplane to reach take-off speed; and when retracted they formed the lower surface of the fuselage without creating any drag.

Convair XF2Y Sea Dart Article

The inlets for its two 3400-lb (1542-kg) thrust Westinghouse J34-WF-32 turbojets located in the dorsal position where they would be shielded from spray.

YF2Y-1

The concept embodied in the Convair Model 2-2 proposal was sufficiently interesting for the US Navy to award a contract for a prototype XF2Y-1 on 19 January 1951, followed by an order for 12 production F2Y-1 fighters on 28 August 1952; to this was added subsequently four YF2Y-1 pre-production aircraft.

First flown on 9 April 1953, the prototype offered performance much below expectations and this factor, coupled with serious vibration problems with the hydro-skis, led to the XF2Y-1 and the production F2Y-1s being cancelled.

During test runs there was considerable vibration and pounding from the two hydro-skis and these were replaced by a single V-shaped ski. More power was needed than the 1542kg thrust provided by each of the Westinghouse J34-WE-32 turbojets installed in the prototype and the first YF2Y-1. This latter aircraft was re-engined with two J46-WE-2s, the rear fuselage being modified to accommodate the engine afterburners and the same powerplant was installed in the remaining three YF2Y-1s. On 3 August 1954 the YF2Y-1 exceeded a speed of Mach 1 in a shallow dive, the first seaplane to become supersonic, but only two of these aircraft were used in a limited test programme that was terminated finally during 1956.

Gallery

YF2Y Sea Dart
Engines: 2 x Westinghouse J46-WE-32, 2722kg
Wingspan: 10.26 m / 33 ft 8 in
Length: 16.03 m / 52 ft 7 in
Height: 6.32 m / 20 ft 9 in
Wing area: 52.30 sq.m / 562.95 sq ft
Max take-off weight: 7495 kg / 16524 lb
Empty weight: 5739 kg / 12652 lb
Max. speed: 1118 km/h / 695 mph
Ceiling: 16705 m / 54800 ft
Range: 826 km / 513 miles
Crew: 1

YF2Y-1
Engines: 2 x Westinghouse J46-WE-8 turbojets, 4,800 lb. thrust
Wingspan: 30 ft. 6 in
Length: 41 ft. 2 in
Loaded weight: approx. 22,000 lb.
Armament: 4×20 mm. cannon
Crew: 1.