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For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.
The position of a swept wing along the fuselage has to be such that the lift from the wing root, well forward of the aircraft center of gravity (c.g.), must be balanced by the wing tip, well aft of the c.g. [68] If the tip stalls first the balance of the aircraft is upset causing dangerous nose pitch up. Swept wings have to incorporate features ...
In fluid dynamics, angle of attack (AOA, α, or ) is the angle between a reference line on a body (often the chord line of an airfoil) and the vector representing the relative motion between the body and the fluid through which it is moving. [1] Angle of attack is the angle between the body's reference line and the oncoming flow.
Data from Jane's All the World's Aircraft 2013–14, pp. 672–3 General characteristics Capacity: Two Length: 6.96 m (22 ft 10 in) Wingspan: 7.92 m (26 ft 0 in) Height: 2.08 m (6 ft 10 in) Wing area: 11.4 m 2 (123 sq ft) Airfoil: NACA 23012, with washout to NACA 2412 outboard Empty weight: 680 kg (1,499 lb) Max takeoff weight: 1,111 kg (2,449 lb) ; 907 kg (2,000 lb) for aerobatic flight Fuel ...
The WGPLNF, HTPLNF and VTPLNF Namelists define the wing, horizontal tail and vertical tail, respectively. The basic parameters such as root chord, tip chord, half-span, twist, dihedral and sweep are input. Digital DATCOM also accepts wing planforms which change geometry along the span such as the F4 Phantom II which had 15 degrees of outboard ...
The Gurney flap (or wickerbill) is a small tab projecting from the trailing edge of a wing. Typically it is set at a right angle to the pressure-side surface of the airfoil [2] and projects 1% to 2% of the wing chord. [3] This trailing edge device can improve the performance of a simple airfoil to nearly the same level as a complex high ...
X body axis is aligned along the vehicle body and is usually positive toward the normal direction of motion. Y body axis is at a right angle to the x body axis and is oriented along the wings of the vehicle. If there are no wings (as with a missile), a "horizontal" direction is defined in a way that is useful.
Supercritical airfoils feature four main benefits: they have a higher drag-divergence Mach number, [21] they develop shock waves farther aft than traditional airfoils, [22] they greatly reduce shock-induced boundary layer separation, and their geometry allows more efficient wing design (e.g., a thicker wing and/or reduced wing sweep, each of which may allow a lighter wing).