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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 52.5 degree delta-wing and an unswept horizontal tail
Alan B Kehlet
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Abstract
A free-flight investigation of an airplane configuration having a low 52.5 degrees delta wing and an unswept horizontal tail was conducted over a Mach number range of 1.40 to 2.78. At a fixed tail setting of -3.0 degrees, the trim lift coefficient and angle of attack varied from about 0.12 to 0.04 and 3.8 degrees to 2.0 degrees, 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 to 2.74. Theoretical calculations of lift-curve slope and aerodynamic-center location were in good agreement with experimental results. (Author)