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Measured and Computed Hypersonic Aerodynamic/Aeroheating Characteristics for an Elliptically Blunted Flared CylinderComputational and experimental hypersonic aerodynamic forces and moments and aeroheating levels for Kistler Aerospace Corporation's baseline orbiter vehicle at incidence are presented. Experimental data were measured in ground-based facilities at the Langley Research Center and predictions were performed using the Langley Aerothermodynamic Upwind Relaxation Algorithm code. The test parameters were incidence (-4 to 24 degrees), freestream Mach number (6 to 10), freestream ratio of specific heats (1.2 to 1.4), and freestream Reynolds number (0.5 to 8.0 million per foot). The effects of these parameters on aerodynamic characteristics, as well as the effects of Reynolds number on measured heating levels are discussed. Good agreement between computational and experimental aerodynamic and aeroheating values were observed over the wide range of test parameters examined. Reynolds number and ratio of specific heats were observed to significantly alter the trim L/D value. At Mach 6, laminar flow, was observed along the entire windward centerline up to the flare for all angles and Reynolds numbers tested. Flow over the flare transitioned front laminar to transitional turbulent between 4 and 8 million per foot at 8 and 12 degrees angle of attack, and near 4 million per foot at 16 degrees angle of attack.
Document ID
20010023933
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Greene, Francis A.
(NASA Langley Research Center Hampton, VA United States)
Buck, Gregory M.
(NASA Langley Research Center Hampton, VA United States)
Wood, William A.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2001-0562
Meeting Information
Meeting: Aerospace Sciences
Location: Reno, NV
Country: United States
Start Date: January 8, 2001
End Date: January 11, 2001
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
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