1 engine

LVG C-V

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Used for reconnaissance and bombing, a small number of L.V.G.s were in the German air force at the outbreak of war in 1914. Like their British counterparts, they were unarmed and suffered heavy losses. This resulted in the much improved C.V, armed with machine¬guns, which proved a formidable adversary, in spite of the pilot’s exceptionally poor view forward.

A two-bay biplane, the two spar wooden wings were fabric covered. Plywood covered the wooden fuselage, with integral upper and lower tail fins. Fabric covered wooden tailplane. All control surfaces were welded steel-tube construction, with fabric covering. Ailerons were on the top wing only.

About 500 C.V’s and C.VI’s were in frontline service in the summer of 1918.

Engine: One 200 h.p. Benz Bz.IV
Wing span 42.75 ft (13.02 m.)
Wing area: 459.6 sq.ft
Length 26.5 ft (8.07 m.)
Height: 10 ft 6 in
Weight empty 1,860 lb. (843 kg.)
MTOW: 3141 lb
Fuel capacity: 52.5 Imp.Gal
Max speed: 102 m.p.h. (164 km.p.h.) at 6000 ft
Service ceiling: 16,500 ft. (5,000 m.) fully loaded
Endurance: 3.5 hours
Seats: 1 pilot and 1 observer
Armament One fixed Spandau machine gun firing forward, one Parabellum mg rear cockpit

LVG C-1 / C-II

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A reconnaissance biplane of WW 1.

C.I

The C.II was developed from the LVG C.I, with the pilot and observer positions reversed, adding a ring-mounted machine gun to the rear. The increase in weight required a larger engine, the Benz Bz.III. Few C.I’s were built before the C.II was introduced. It incorporated structural improvements and a more powerful engine.

C.II

C.I
Engine: Mercedes, 130 hp
Top speed: 97 mph

C.II
Engine: Mercedes D.III, 119 kW (160 hp)
Wingspan: 12.85 m (42 ft 2 in)
Wing area: 37.60 m2 (404.74 sq ft)
Length: 8.10 m (26 ft 7 in)
Height: 2.93 m (9 ft 7.25 in)
Empty weight: 845 kg (1,863 lb)
Gross weight: 1,405 kg (3,097 lb)
Wing loading: 37 kg/m2 (7.6 lb/sq ft)
Maximum speed: 130 km/h (81 mph, 70 kn)
Range: 385 km (240 mi, 210 nmi)
Endurance: 4 hours
Service ceiling: 4,000 m (13,125 ft)
Crew: 2
Armament
1 × flexible 7.92 mm (.312 in) Parabellum MG14 machine gun
1 × fixed, forward-firing 7.92 mm (.312 in) LMG 08/15 machine gun (later production aircraft)
Bomb load: 60 kg (130 lb)

C.II

Luttrell 1909 biplane

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Samuel Luttrell, a local automobile enthusiast of Rockville, Maryland (or Washington DC), built this tailless tractor biplane in 1909. He tested it with a 50-horsepower engine, driving the four-bladed canvas propeller at about 650 revolutions per minute. The propeller was set on a universal joint and intended to control the vertical and lateral movement of the machine. The strong engine crumpled up the flimsy-looking propeller on the first test, after which a 30 horsepower unit was installed.

Luton LA5 Major / Phoenix Aircraft Ltd LA5 Major

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Following the pre-war success of the Luton Minor, Mr. Latimer-Needham designed the two seater Major which first flew on 4 March 1939.

Accommodation is for two per¬sons seated in tandem in an enclosed cabin with a door in the starboard side. Dual controls are fitted. An 11 Imp. gallon fuel tank is fitted behind the firewall. Alternative engines include 62 h.p. Walter Mikron 11, 83 h.p. Agusta GA-70, 55 h.p. Lycoming and 85 h.p. Continental.

A hangar fire at the Phoenix Works in 1943 destroyed the single example of the LA5 Major, a two-seat cabin type, and also spelt the end for the company. C. H. Latimer-Needham founded a new company at Cranleigh, Surrey, in March 1958, appropriately named Phoenix Aircraft Ltd, which acquired the rights for the Minor and Major. Both designs were improved, the first as the LA4A Minor, and built in the UK and in several countries across the world.

The Luton Major was the only British designed two seater aircraft available to amateurs for home building.

LA.5 Major HB-YAH. Built in Italy, registered and flown in Switzerland

Phoenix Aircraft Ltd. undertook the revision of the Major drawings for amateur construction and the aircraft has since been re-stressed to to permit engine power to 85 hp and gross weight to 1400 lbs and it has been restressed to British Airworthiness Require¬ments. The wing chord is the same as the Luton Minor and the wings fold back for ease of storage and transport.

Engine: Walter Mikron 11, 62 h.p.
Span: 35’ 2”.
Length: 23’ 9”.
Wing Area: 163 sq.ft.
Empty Weight: 600 lb.
Loaded Weight: 1100 lb.
Wing Loading: 6.7 lb/sq. ft.
Max. Speed: 105 mph.
Cruise Speed: 95 mph.
Stall Speed: 40 mph.
Initial Climb: 700 fpm.
Takeoff run 250 ft.
Landing roll 150 ft.
Range: 300 miles.
Fuel capacity 11 Imp.Gal..
Width (wings folded): 11’ 8”.
Seats: 2.

Luton LA3 / LA4 Minor / Phoenix Aircraft Ltd LA4A Minor / Ord-Hume OH-7 Coupe / Parker CA.4

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The tandem-wing LA2 never flew, but its fuselage and other components were incorporated into the LA3. The LA3 (also G-AEPD cn LA.3) was built at Barton-in-the-Clay in 1937. It was powered by an Anzani engine. It survived the War in store in Scotland but was destroyed in the 1950s.

The LA3 itself was redesigned for home-assembly as the LA4 Minor. Designed by Mr. C. H. Latimer-Needham, the first was built at the company’s Phoenix Works at Gerrards Cross, Buckinghamshire, and fitted with a 40hp ABC Scorpion, but subsequent models were home-built from drawings and fitted with many different engines.

The Minor is a single seat aircraft with a two piece wooden two spar wing of 5’ 3” chord, attached to a tubular steel pylon on the fuselage. The wings are divided for ease of building, transport and storage. The wing section is RAF 48. The leading edge is plywood covered, the remainder of the wing being fabric covered. The fuselage is a rectangular all wood structure; the sides and bottom being plywood covered, while the top decking behind the cockpit is fabric covered. The under¬carriage incorporates rubber disc shock absorbers for the main legs and optional brakes. The tailwheel is fully castoring.

The first Luton Minor flew in England in 1936 and in 1960 the design was restressed enabling engines up to 55 hp to be fitted. The Minor was designed for the 37 h.p. Aeronca JAP engine, although the 55 hp Lycoming and converted Volkswagen engines may be installed. A 6.5 Imp. gallon fuel tank is located behind the firewall.

A.W.J.G.Ord-Hume designed a modified Luton LA.4 Minor with a totally enclosed cockpit, designated Ord-Hume OH-7 Coupe (previously known as the Luton LA.4C). Construction of the prototype (c/n OH-7, PAL.1401 G-ARIF) was started at Sandown in 1965 and it was nearing competition in early 1975.

Luton Minor G-AFIU built by C.F.Parker was designated Parker CA.4. It was started in 1938 but not finished. It was stored at Peel Green, Manchester.

The design of the Luton Minor was brought up to date by Phoenix Aircraft Ltd., successors to Luton Aircraft Ltd. In 1959-60 the Minor was accredited as one of the finest single seater amateur aircraft in Europe, and the easiest to build.

Gallery

Engine: Aeronca JAP, 37 h.p.
Span: 25’ 0”.
Length: 20’ 9”.
Wing Area: 125 sq. ft.
Empty Weight: 450 lb.
Loaded Weight: 750 lb.
Wing Loading: 6.0 lb. sq. ft.
Max. Speed: 85 mph.
Cruise Speed: 75 mph.
Stall Speed: 37mph.
Initial Climb: 450 fpm.
Range: 180 miles.
Fuel capacity 6.5 Imp.Gal.
Takeoff run: 250 ft.
Landing roll 120 ft.
Seats: 1.

Luscombe Aircraft Vitality

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Single engined high wing mono¬plane with conventional three axis control. Wing has swept back leading and trailing edges and tapering chord; no tail, canard wing. Pitch control by fully flying canard; yaw control by under wing rudders at half span; roll control by differential canard. Wing braced from below by struts; wing profile; 100% double surface. Undercarriage has three wheels in tricycle formation; no suspension on any wheels. Push right go right nosewheel steering. No brakes. Fuselage, totally enclosed. Engine mounted below wing driving pusher propeller.
The Vitality was first announced in mid 1982, using differential canard for roll control and under¬wing rudders at half span for yaw control. In August 1982 Flightlline magazine was told that three Vitalitys had been built and 36 ordered, that production would be concentrated on the two seat version, and that an all new three cylinder 1000 cc radial four stroke was being developed for the aircraft.
A few weeks later came the announcement that Luscombe Aircraft was to move into a new factory in November and that the company hoped to have an aircraft produced by the end of February 1983. These aircraft never materialised, however, as the company announced later in 1982 that it had shelved the design, at least until the UK microlight airworthiness regulations were finalised.
Although that happened in March 1983, the design rights of Vitality were for sale, along with three prototypes one two seater and two single seaters. The design was first conceived some 11 years before and dusted off in response to the microlight boom.

Engine: Robin EC44, 60 hp.
Power per unit area 0.47 hp/sq.ft, 5.0hp/sq.m.
Empty weight 236 lb, 107 kg.
Length overall 11.7 ft, 3.56 m.
Height overall 4.8ft, 1.47m.
Wing span 34.0ft, 10.36m.
Mean main wing chord 3.8 ft, 1.15 m.
Canard span 14.0ft, 4.27m.
Mean canard chord 0.95ft, 0.29m.
Total wing area 141 sq.ft, 13.1 sq.m.
Main wing area 128sq.ft, 11.9sq.m.
Canard area 13 sq.ft, 1.2 sq.m.
Wing aspect ratio 9.0/1.

Luscombe Colt

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Luscombe Gullwing 1960 N54082

The Colt 190 design rights and fuselage, wing alignment, and gear jigs were purchased by Spibec Corp for $30,000, according to Carroll S Bechtel, one of Spibec’s three owners. By 1958 the prototype had been flown more than 350 hours. Engineering data necessary for FAA approval, with the exception of static wing-loading tests, had been completed. Although with no firm orders, Bechtel production schedule called for 50 Colts the first year (1960) and another 50 the second year at one of several airports in the Philadelphia area, with subsequent output depending on demand for the plane. The projected base price $7,995

Ray Weatherley acquired plans of the Colt 4-seater NX54082 from Luscombe Airplane Corporation in 1942. A high wing cabin monoplane, designed by Fred Knack and completed post-war, the aircraft was still active into the ’90s.

Engine: 190hp Lycoming O-435 or 215hp Franklin
Wingspan: 36’3″
Length: 23’11”
Useful load: 685 lb
Max speed: 160 mph
Cruise speed: 140 mph
Stall: 52 mph
Range: 750 mi

Luscombe 11 Sedan / Spartan / Alpha Aviation Co Alpha 11D

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11A Sedan

Alpha Aviation Co was established early 1970s to manufacture a re-engined and updated version of the Luscombe 11A Sedan under the designation Alpha 11D. Primary changes were the introduction of a fixed tricycle landing gear and provision of a 180 hp engine.
The Alpha Aviation prototype use a variable pitch prop, although a fixed-pitch, two-blade prop will be fitted to production aircraft.

2002 Luscombe Model 11E

1998 Luscombe Spartan 185 IIE
Price: $138,500
Engine: Continental IO-360-ES4, 185 hp @ 2550rpm@SL
TBO: 1800 hr
Fuel type: 100/100LL
Propeller: Three-blade CS
Landing gear type: Fixed/Tri
Max ramp weight: 2286 lb
Gross weight: 2286 lb
Max landing weight: 2286 lb
Empty weight, std: 1350 lb
Payload, full std. fuel: 696 lb
Usable fuel: 39 USgal
Oil capacity: 8 qt
Wingspan: 38 ft. 6 in.
Overall length: 24 ft.
Height: 8 ft. 10 in.
Wing area:167 sq. ft
Wing loading: 13.7 lb/sq. ft
Power loading: 12.3 lb/hp
Wheel track: 7 ft. 4 in.
Wheel size: 6.00 x 6 in
Seating capacity: 4
Cabin doors: 2
Cabin width: 45.5 in
Cabin height: 51.3 in
Baggage capacity: 100 lb
Cruise speed 75% power: 126 kt
Cruise speed 65% power: 121 kt
Cruise speed 55% power: 110 kt
Max range (w/ reserve) 75% power: 375 nm
Max range (w/ reserve) 65% power: 420 nm
Max range (w/ reserve) 55% power: 440 nm
Fuel consumption 75% power: 11.5 US gph
Fuel consumption 65% power: 9.8 US gph
Fuel consumption 55% power: 8.2 US gph
Stall speed (flaps up): 47 kt
Stall speed (flaps down): 43 kt
Best rate of climb: 1050 fpm
Best rate of climb at 8000 ft: 800 fpm
Service ceiling: 18,000 ft
Takeoff ground roll: 670 ft
Takeoff over 50-ft. obstacle:1140 ft
Landing ground roll: 500 ft
Landing over 50-ft. obstacle: 800 ft

2002 Luscombe Model 11E
Base price (incl. basic avionics):$158,900
Engine: Continental. IO-360-ES4, 185 hp
Fuel type: 100/100LL
Propeller type: FP
Landing gear type: Tri/Fixed
Gross weight: 2280 lb
Landing weight: 2280 lb
Empty weight, std: 1450 lb
Useful load, std: 830 lb
Payload – full std. fuel: 590 lb
Useable fuel, std: 40 USgal
Height: 8 ft. 10 in.
Overall length: 24 ft.
Wingspan: 38 ft. 6 in.
Power loading: 12.3 lb/hp
Seating capacity: 4
Cabin doors: 2
Cabin width: 45.5 in
Cabin height: 51.3 in
Baggage capacity: 100 lb
Cruise speed @ 7,500 ft 70% power: 117 kt
Cruise speed @ 7,500 ft 60% power: 110 kt
Fuel consumption 70% power: 7.4 USgph
Fuel consumption 60% power: 7.0 USgph
Vs: 47 kt
Vso: 49 kt
Best rate of climb: 876 fpm
Best rate of climb, 8000 ft: 800 fpm
Service ceiling (ft.): 16,000
Takeoff ground roll: 900 ft
Takeoff over 50-ft. obstacle: 1375 ft
Landing ground roll: 800 ft
Landing over 50-ft. obstacle:1901 ft

Alpha 11D
Engine: 180hp Lycoming O-360
Wingspan: 38’0″
Length: 25’0″
Useful load: 990 lb
Max speed: 150 mph
Cruise: 135 mph
Seats: 4