Wind tunnel tests at Mach numbers between 0.6 and 1.4 of a 60 [degrees] swept wing having an aerofoil section designed for subcritical flow at a Mach number of 1.2 / Aeronautical Research Council ; Pt. 1: 9% thick section with "triangular" pressure distribution
1962
35 p.
33 cm
40 plates
Buch
Englisch
DDC: | 629.13432 |