Abstract
An advanced rotation-balance apparatus has been developed for the Ames 12-ft Pressure Wind Tunnel to study the effects of spin rate, angles of attack and sideslip, and, particularly, Reynolds number on the aerodynamics of fighter and general aviation aircraft in a steady spin. Angles of attack to 100 deg and angles of sideslip to 30 deg are possible with spin rates to 42 rad/s (400 rpm) and Reynolds numbers to 30x 106/m on fighter models with wing spans that are typically 0.7 m. A complete description of the new rotation-balance apparatus, the sting/balance/model assembly, and the operational capabilities is given. Nomenclature A = body reference area, ird214 b = wing span (0.457 m for Figs. 3-6) Cy = body side force/qA d = diameter of centerbody (0.0762 m for Figs. 3-6) M = freestream Mach number q — freestream dynamic pressure Rd — Reynolds number based on d V — freestream velocity as — sting angle (Figs. 11 and 12) a =angle of attack /3 = angle of sideslip a = angle between freestream velocity vector and body longitudinal axis
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