Accession Number:

AD0608830

Title:

HEAT TRANSFER MEASUREMENTS AT MACH 8 ON AN AERODYNAMICALLY CONTROLLABLE WINGED RE-ENTRY CONFIGURATION. PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS

Descriptive Note:

Corporate Author:

GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY

Personal Author(s):

Report Date:

1964-09-01

Pagination or Media Count:

437.0

Abstract:

Heat transfer data were obtained at Mach 8 for a winged re-entry configuration with several types of aerodynamic controls. The basic model consisted of a clipped delta wing with an overslung cone-cylinder body. Most of the tests were conducted with partial span trailing edge flaps. The effects of tip fins, a hemisphere-cylinder body, a full span trailing edge flap, and a full span, plugtype, trailing edge spoiler were also investigated. The partial span flap deflection were varied between 39 degrees in an angle of attack range of 20 degrees. Selected configurations were used to examine the angle of attack ranges of -30 degrees to -50 degrees and 30 degrees to 50 degrees. The major portion of the program was conducted at a unit test section Reynolds number of 3.3 x 10 to the 6th powerft with limited comparative testing being done at a unit test section Reynolds number of 1.1 x 10 to the 6th powerft.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE