Wind-tunnel Investigation of Effects of Ground Proximity and of Split Flaps on the Lateral Stability Derivatives of a 60 Degree Delta-wing Model Oscillating in Yaw
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A delta wing and a tapered sweptback wing of aspect ratios 1.56 and 2.00, respectively, both of which were cambered and twisted so as to provide a uniform load distribution for a supersonic flight condition, were tested in combination with a fuselage at Reynolds numbers between 384,000 and 1,550,000 in order to determine the low-speed lift-drag and static stability characteristics of such wings.
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