An investigation has been conducted in the Langley low-turbulence pressure tunnel to determine the aerodynamic characteristics of a proposed flight-research vehicle with a delta planform and a high hypersonic lift-drag ratio. The tests were conducted at a Mach number of about 0.25, angles of attack from about -9 deg. to 31 deg., angles of sideslip from about -7 deg. to 12 deg., and Reynolds numbers based on body length from 4.5 x 10(exp 6) to 43.2 X 10(exp 6).
Low Subsonic Aerodynamic Characteristics of a Reentry Spacecraft Shape with a High Hypersonic Lift-Drag Ratio
1971
38 pages
Report
No indication
English
HYPERSONIC AERODYNAMIC CONFIGURATIONS WITH MAXIMUM LIFT-TO-DRAG RATIO
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