Transonic and supersonic wind tunnel tests investigated the loads on one wing panel and one control panel at different positions on schematic body-wing, body-tail, and body-wing-tail cruciform missile configurations for 0 and 45 deg roll position. The Mach number range was 0.7 to 3.0 and the angle of attack varied between minus 3 degrees and plus 24 degrees. The tail controls were tested at different angles from 0 deg to -20 deg with 5 deg steps. The result is given in diagram and tables. Interference coefficients and downwash figures were evaluated.
Wind Tunnel Investigation of Wing and Control Panel Loads at Transonic and Supersonic Speeds on Some Schematic Cruciform Missile Configurations
1987
207 pages
Report
Keine Angabe
Englisch
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