STATIC PRESSURE DISTRIBUTIONS ON VARIOUS BODIES OF REVOLUTION AT MACH NUMBERS FROM 0.60 TO 1.60
Abstract
An investigation was conducted in the Propulsion Wind Tunnel, Transonic (16T) to determine the static pressure distributions on various bodies of revolution. The nose shapes tested were 20-, 40-, and 60-deg (total-angle) cones, an ellipse, and an ogive. The data were obtained for various angles of pitch and yaw at Mach numbers from 0.60 to 1.60. Primarily these data will be used for the test section calibration of a new transonic wind tunnel with a 4- ft-square test section; consequently, the models were designed for 1-percent blockage in the 4-ft wind tunnel, making them 0.0625-percent blockage in Tunnel 16T. Despite their relatively small size in 16T, some wall effects were experienced between Mach numbers 0.95 and 1.05. Both above and below this Mach number range the data were found to be relatively free of wall effects. In the range from M = 0.95 to 1.05 attempts were made to reduce the wall effects by varying wall angle and test section pressure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1968
- Accession Number
- AD0828571
Entities
People
- J. L. Jacocks
- M. S. Hartley
Organizations
- Arnold Engineering Development Complex