Pressure Measurements on Four Cone-Cylinder-Flare Configurations at Supersonic Speeds

摘要

Pressure distribution data are presented for four cone-cylinder-flare configurations at Mach numbers of 1.75 to 4.5. The angle of attack range was from -4 to +12 degrees. Roll angles ranged from 0 to 180 degrees. The Reynolds number remained constant at approximately 450,000 per inch. The boundary layer was made turbulent with a grit ban. The basic pressure data are presented in tabular form with the test conditions printed on each table. (Author)