Frank, Joseph L.
This report presents ram-recovery and mass-flow ratios for NACA submerged inlets at four positions on the fuselage of a model of a hypothetical fighter airplane. Ram-recovery and mass-flow contours in the inlet and plots of the pressuredistribution over the ramp and in the inelt entrance are shown for the rearmost inlet position. The Mach number range was from 0.30 to 0.875, and the angle-of-attack range was from -2 degrees to 12 degrees.
An Adobe Acrobat (PDF) file of the entire report: