Accession Number:

AD0856900

Title:

Gemini B Re-Entry Module/Adapter Attachment Fairing Aerodynamic Heating and Pressure Tests in the McDonnell Hypervelocity Impulse Tunnel - Series 1

Descriptive Note:

Corporate Author:

MCDONNELL AIRCRAFT CO ST LOUIS MO

Personal Author(s):

Report Date:

1968-05-24

Pagination or Media Count:

381.0

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 moduleadapter 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.

Descriptors:

• *REENTRY VEHICLES
• *HYPERSONIC CHARACTERISTICS
• *SPACE STATIONS
• *MANNED SPACECRAFT
• AERODYNAMIC CONFIGURATIONS
• ANGLE OF ATTACK
• AERODYNAMIC LOADING
• THERMAL CONDUCTIVITY
• TABLES(DATA)
• AERODYNAMIC HEATING
• WIND TUNNEL MODELS
• FAIRINGS
• SPACE CAPSULES

Subject Categories:

• Spacecraft Trajectories and Reentry
• Manned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE