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Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air (1999)
BibTeX
@MISC{Sti99aerodynamiccharacteristics,
author = {The Nasa Sti and William I. Scallion},
title = {Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air},
year = {1999}
}
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Abstract
A 0.0196-scale model of the HL-20 lifting-body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 20 to 41, the sideslip angles were 0, 2, and-2, and the test Reynolds number was 1.06 x 10 6 based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30. The lower surface body flaps were effective for roll control and the associated adverse ya...
Keyphrases
control effectiveness hl-20 lifting body configuration aerodynamic characteristic fin-mounted elevons lateral control effectiveness nominal angle-of-attack range hl-20 lifting-body langley 31-inch mach several configuration hypersonic speed sideslip angle primary longitudinal control 0196-scale model surface flush-mounted body flap model reference length test reynolds number nominal center surface body flap flush-mounted yaw controller roll control surface oil flow visualization hypersonic entry desired entry angle associated adverse ya
