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Consider the Supermarine Spitfire, a British World War II fighter that has an elliptical wing planform, in steady level flight. Its wing span is b =...
1. Consider the Supermarine Spitfire, a British World War II fighter that has an elliptical wing planform, in steady level flight. Its wing span is b = 11.23 m, wing aspect ratio is 5.61, mass is m = 3,000 kg, and speed is V∞ = 85 m/s at an altitude of 1,000 m (where the air density is r = 1.1117 kg/m3 ). Assume the Spitfire's wing has no geometric or aerodynamic twist.
(a) Ensure that it is acceptable to assume incompressible flow (use a Mach number threshold of 0.3).
(b) What is the circulation at the wing root, G0?
(c) What is the lift per unit span, L', at a spanwise position of y = b/4?
(d) Find the induced angle of attack, ai, in degrees.
(e) What is the ratio of the induced drag to the lift, Di / L ? Give your answer as a percentage.
(f) What is the lift coefficient, CL?
(g) What is the chord length at the wing root, c0?
