Gemini B Re-Entry Module/Adapter Attachment Fairing Aerodynamic Heating and Pressure Tests in the McDonnell Hypervelocity Impulse Tunnel - Series 1
Abstract
Tests of a 9 percent Gemini B model were conducted in the McDonnell Hypervelocity Impulse Tunnel. A total of 25 data producing shots were made at Mach numbers ranging from 13 to 17, and Reynolds number per foot ranging from 1. 0 X 10 to the 6th power to 2.0 X 10 to the 6th power. The model was tested at angles of attack of 160 deg, 165 deg, and 170 deg. The initial three test shots assisted in determining the heat transfer and pressure gage locations by determining the areas of high heating behind the lower re-entry module/adapter fairing. This was accomplished by the use of thermographic phosphor temperature mapping techniques. The remaining 22 test shots determined the heat transfer rate and pressure distributions on the re-entry module in the area behind the noted fairing and along the windward centerline.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 24, 1968
- Accession Number
- AD0856900
Entities
Organizations
- McDonnell Aircraft Corporation