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
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 power/ft with limited comparative testing being done at a unit test section Reynolds number of 1.1 x 10 to the 6th power/ft.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1964
- Accession Number
- AD0608830
Entities
People
- Lawrence Meckler
Organizations
- Grumman