Abstract:
Four models of an aircraft configuration with a 55 degree swept wing were flown at Mach numbers between 0.9 end 1.4, at Reynolds numbers up to 10 million and lift coefficients between zero and 0.5. Measurements of the manoeuvre margin and the derivatives ... were obtained. The results are compared with those obtained from one of the same models in a transonic wind tunnel and from a related M-wing model in flight. They are also corrected for aeroelastic effects.
