NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
An investigation has been made in the Langley 8-foot transonic pressure tunnel to determine the damping-in-pitch and the oscillatory longitudinal stability characteristics of six bluntnose cylinder-flare reentry configurations that were designed for supersonic impact. Tests were made at Mach numbers from 0.80 to 1.15 and at mean angles of attack from 0 to 14 degrees. Reynolds numbers, based on 0.333 foot, varied from 0.62 to 0.69 times 10 to the 6th power. The amplitude of the forced oscillation was 2 degrees with reduced frequencies from 0.012 to 0.036. Some of the effects of flare angle, nose shape, and fins are noted.