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Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control

A Comparison of Several Systems of Boundary-Layer Removal Ahead of a Typical Conical External-Compression Side Inlet at Mach Numbers of 1.88 and 2.93

Experimental investigation of methods of improving diffuser-exit total-pressure profiles for side-inlet model at Mach number 3.05

Preliminary investigation of shield to improve angle-of-attack performance of nacelle-type inlet

Published Year

• 1950-1959 (4) *

Subject

• Airplanes--Motors--Cowlings (1)
• Airplanes--Nacelles (1)
• Angle of attack (Aerodynamics) (1)
• Charts, diagrams, etc (1)
• Diffusers (1)
• Jet engines--Air intakes (1)

Author

• Piercy, Thomas G. (4) *
• Beheim, Milton A. (1)

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