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Experimental Investigation of Hypersonic Air Data Attitude Equations for a Hemispherical Pressure Probe.
CORNELL AERONAUTICAL LAB INC BUFFALO NY
Pressure data obtained from hypersonic shock tunnel tests of a hemispherical air data probe were used to evaluate the validity and range of applicability of attitude equations derived from an assumed pressure distribution. Various forms of attitude angle equations determined analytically from this distribution were compared with the experimental results. Data were obtained on a six-inch diameter hemispherical probe with interchangable cylindrical and 15 deg half angle conical afterbodies at zero attitude, at Mach numbers of 7 to 8.2. Data were also obtained at angles of attack ranging from 0 to 85 deg and angles of yaw from 0 to 15 deg at a Mach number of 7. this angle of attack range. The data also confirm an expected independence of angle of attack measurement on angle of yaw. Author
Final rept. Nov 68-Sep 69,