WING HAYING AN AEROFOIL SECTION DESIGNED FOR SUBCRITICAL FLOW AT A MACH NUMBER OF 1.2 PART I: 9% THICK SECTION WITH "TRIANGULAR" PRESSURE DISTRIBUTION bY
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RCWAL ^Inr,•e,,:'r ze.i,:,g~ >-.~,M.-~ MINISTRY OF AVIATION
This note describes further tests made during 1954 in the Royal Aircraft Establishment 10 ft x 7 ft High Speed Tunnel, as part of a research programme to improve the subsonic longitudinal stability characteristics of a 50 deg swept wing of aspect ratio 3" 1 by means such as nose-droop, chord extensions, fences, change of aerofoil section, etc. Lift, drag, pitching-moment and root bending moment...
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