Data was obtained by tracking rocket-propelled bodies carrying wings of various plan forms. Results showed that for investigations in Mach number range of 1.05 - 1.35, an increasing swept-back angle and decreasing aspect ratio reduced the value of wing drag coefficient. Decreasing the aspect ratio always decreased the wing drag coefficient; although, this effect was observed to become very small at higher swept-back angles.
Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Aspect Ratios of 1.5 and 2.7 as determined by Flight Tests at Supersonic Speeds
1947
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English