Effects of internal corner fillets on pressure recovery : mass flow characteristics of scoop-type conical supersonic inlets

Alfred S. Valerino
Dec 1952

An investigation was conducted in the NACA Lewis 8- by 6-foot supersonic tunnel at free-stream Mach numbers of 1.49 to 1.97 at zero angle of attack to determine the effects of internal corner fillets on the pressure recovery characteristics of twin-scoop conical-type inlets utilizing boundary-layer removal and mounted on the RM-10 body. The inlet size was relatively small, with a cowl lip radius of 1.33 inches.

An Adobe Acrobat (PDF) file of the entire report: