Heat Transfer Measurements at Mach 9 on an Aerodynamically Controllable Winged Re-Entry Configuration: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Item

Title
Heat Transfer Measurements at Mach 9 on an Aerodynamically Controllable Winged Re-Entry Configuration: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
Date
1964
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
FDL TDR 64-142
Corporate Author
Grumman Aircraft Engineering Corporation
Extent
438
Identifier
AD0608830
Access Rights
OTS
Distribution Classification
1
Contract
AF 33(616)-8130
DoD Project
8219
DoD Task
821902
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
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.
Report Availability
Full text available
Date Issued
1964-09
Laboratory
AF Flight Dynamics Laboratory
Provenance
Lockheed Martin Missiles & Fire Control
AFRL/VACA
Type
report
Format
1 online resource
Creator
Meckler, Lawrence
Media
FDLTDR64-142.pdf