Total-pressure recovery of a circular underslung inlet with three different nose shapes at a Mach number of 1.42

Charles F. Merlet, Howard S. Carter
Feb 1952

A circular underslung inlet located well forward on a body of revolution - modified by drooping the nose in the direction of the inlet was tested at a Mach number of 1.42 in a free-air jet. The nose shapes, one pointed and two spherical, were tested through a range of mass-flow ratios at three different angles of attack and one angle of yaw.

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