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Aspect ratio (aeronautics) An ASH 31 glider with very high aspect ratio (AR=33.5) and lift-to-drag ratio (L/D=56) In aeronautics, the aspect ratio of a wing is the ratio of its span to its mean chord. It is equal to the square of the wingspan divided by the wing area. Thus, a long, narrow wing has a high aspect ratio, whereas a short, wide wing ...
Wing configuration. The Spitfire wing may be classified as: "a conventional low-wing cantilever monoplane with unswept elliptical wings of moderate aspect ratio and slight dihedral". The wing configuration of a fixed-wing aircraft (including both gliders and powered aeroplanes) is its arrangement of lifting and related surfaces.
Data from Sport Aviation General characteristics Length: 17 ft (5.2 m) Wingspan: 19 ft (5.8 m) Wing area: 211 sq ft (19.6 m 2) Airfoil: NACA M6 Empty weight: 780 lb (354 kg) Powerplant: 1 × Continental A-40, 36 hp (27 kW) Performance Maximum speed: 84 kn (97 mph, 156 km/h) Stall speed: 20 kn (23 mph, 37 km/h) See also Lifting body Related development Arup S-1 Arup S-3 Arup S-4 Aircraft of ...
The aircraft was also to test the feasibility of low-aspect-ratio wings, and the large-scale use of titanium in aircraft structures. The design of the Douglas X-3 Stiletto is the subject of U.S. Design Patent #172,588 granted on July 13, 1954, to Frank N. Fleming and Harold T. Luskin and assigned to the Douglas Aircraft Company, Inc.
Their design team, which was influenced by design information obtained from Nazi Germany [citation needed], opted for a tailless configuration paired with low aspect ratio swept wings, which was regarded as a radical departure from traditional aircraft design for the era. Vought's submission was favoured by Navy officials and was declared the ...
Data from Sailplane Directory, Soaring and FAA Type Certificate G51EU General characteristics Crew: one Capacity: one passenger Wingspan: 16.0 m (52 ft 6 in) Wing area: 15.24 m 2 (164.0 sq ft) Aspect ratio: 16.8:1 Airfoil: Wortmann FX 63-137 Empty weight: 497 kg (1,096 lb) Gross weight: 770 kg (1,698 lb) Fuel capacity: 80 liters (18 imp gal ; 21 U.S. gal) Propellers: 2-bladed Hoffmann HO-V 62 ...
A tall, fixed main undercarriage combined with a small tailwheel gave the aircraft a 22° "nose-high" angle. [4] Ground testing of the V-173. The disc wing design featured a low aspect ratio that overcame the built-in disadvantages of induced drag created at the wingtips with the large propellers actively canceling the drag-causing tip vortices ...
Design and development. The Tomahawk is a single-engined low-wing cantilever monoplane with a T-tail and an enclosed cabin for two. It has a fixed tricycle landing gear and is powered by a Lycoming O-235 four-cylinder piston engine with a twin-bladed tractor propeller. The Tomahawk has two front-hinged doors for access to the cabin.