AN EXPERIMENTAL INVESTIGATION AT A MACH NUMBER OF 2.01 OF THE EFFECTS OF BODY CROSS-SECTION SHAPE ON THE AERODYNAMIC CHARACTERISTICS OF BODIES AND WING-BODY COMBINATIONS

摘要

An experimental investigation has been performed in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. Each of the bodies had the same longitudinal area distribution as the ogive-cylinder body of revolution of fineness ratio 10.5. The bodies were tested alone and in combination with a 47° sweptlack wing having a 6-percent-thick hexagonal section.