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Aerodynamic characteristics of the HL-20 and HL-20A lifting-body configurationsThe data show that the HL-20 is longitudinally and laterally stable over the test range from Mach 10 to 0.2. At hypersonic speeds it has a trimmed lift/drag ratio of 1.4. This values gives the vehicle a cross range capability similar to that of the Space Shuttle. At subsonic speeds, the HL-20 has a trimmed lift/drag ratio of about 3.6. Replacing the flat plate outboard fins with fins having an airfoil shape, increased the maximum trimmed L/D to 4.3. Preliminary evaluation of configuration modifications (the HL-20A series), indicates that trim at higher values of lift at hypersonic speeds could be achieved with an L/D of about 1.0. In the supersonic range, the lift and directional stability characteristics were improved. The untrimmed subsonic L/D was increased to 5.8 with airfoil fins.
Document ID
19910069242
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ware, George M.
(NASA Langley Research Center Hampton, VA, United States)
Spencer, Bernard, Jr.
(NASA Langley Research Center Hampton, VA, United States)
Micol, John R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-3215
Accession Number
91A53865
Distribution Limits
Public
Copyright
Other

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