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Aerodynamic Characteristics over a Mach Number Range of 1.40 to 2.78 of a Rocket-Propelled Airplane Configuration having a Low 52.50 Delta Wing and an Unswept Horizontal TailA free-flight investigation of an airplane configuration having a low 52.5 deg. delta wing and an unswept horizontal tail has been conducted over a Mach number range of 1.40 to 2.78. At a fixed tail setting of -3.0 deg., the trim lift coefficient and angle of attack varied from about 0.12 to 0.04 and 3.8 deg. to 2.0 deg., respectively. The base drag was approximately 5 percent of the total drag at trim lift. Lift-curve slope, static longitudinal stability, and damping in pitch were obtained only at Mach numbers of 2.59 t o 2.74. Theoretical calculations of lift-curve slope and aerodynamic-center location were in good agreement with experimental results.
Document ID
20040047109
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Kehlet, Alan B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
May 1, 1961
Subject Category
Aeronautics (General)
Report/Patent Number
NASA-TN-D-836
L-1556
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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