Pressure distribution data are provided for a supersonic rectangular inlet at subsonic speeds. Variations in cowl and ramp geometry as well as sideplate sweep were investigated. Tests were made in the Langley 16-foot transonic tunnel and the Langley high speed 7- by 10-foot tunnel for Mach numbers of 0.6, 0.7, and 0.8. Angles of attack investigated were 0 deg, 4 deg, and 8 deg for a range of mass flow ratios.
Pressure distributions for a rectangular supersonic inlet at subsonic speeds
01.02.1976
Report
Keine Angabe
Englisch
Estimation of inlet lip forces at subsonic and supersonic speeds
TIBKAT | 1955
|Estimation of inlet lip forces at subsonic and supersonic speeds
Engineering Index Backfile | 1955
|