A thin flat-plate wing is set at angle of attack in a uniform supersonic stream at
PHYSICS · Multi-part · Fermi University Physics · Fluids & Continuum Physics · Waves, acoustics and compressible flow · Waves, acoustics and compressible flow
Signal Speeds in Fluids, Ch Steady compressible flow: energy, stagnation and the Mach number
Problem
A thin flat-plate wing is set at angle of attack α=3∘ in a uniform supersonic stream at M∞=1.8. Using supersonic thin-aerofoil (Ackeret) theory, find
((a)) the lift coefficient CL;
((b)) the wave-drag coefficient CD;
((c)) the inviscid lift-to-drag ratio.