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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 part 1 9 percent thick section with "triangular" pressure distribution

E. F. Lawlor (1962)

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- E. F. Lawlor (1)
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- 1962 (1)