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Record 30 of 393
X-33 Hypersonic Aerodynamic Characteristics
Author and Affiliation:
Murphy, Kelly J.(NASA Langley Research Center, Hampton, VA United States)
Nowak, Robert J.(NASA Langley Research Center, Hampton, VA United States)
Thompson, Richard A.(NASA Langley Research Center, Hampton, VA United States)
Hollis, Brian R.(NASA Langley Research Center, Hampton, VA United States)
Prabhu, Ramadas K.(Lockheed Martin Engineering and Sciences Co., Hampton, VA United States)
Abstract: Lockheed Martin Skunk Works, under a cooperative agreement with NASA, will build and fly the X-33, a half-scale prototype of a rocket-based, single-stage-to-orbit (SSTO), reusable launch vehicle (RLV). A 0.007-scale model of the X-33 604B0002G configuration was tested in four hypersonic facilities at the NASA Langley Research Center to examine vehicle stability and control characteristics and to populate an aerodynamic flight database in the hypersonic regime. The vehicle was found to be longitudinally controllable with less than half of the total body flap deflection capability across the angle of attack range at both Mach 6 and Mach 10. At these Mach numbers, the vehicle also was shown to be longitudinally stable or neutrally stable for typical (greater than 20 degrees) hypersonic flight attitudes. This configuration was directionally unstable and the use of reaction control jets (RCS) will be necessary to control the vehicle at high angles of attack in the hypersonic flight regime. Mach number and real gas effects on longitudinal aerodynamics were shown to be small relative to X-33 control authority.
Publication Date: Jan 01, 1999
Document ID:
19990080965
(Acquired Oct 15, 1999)
Subject Category: AERODYNAMICS
Report/Patent Number: AIAA Paper 99-4162
Document Type: Reprint
Meeting Information: Atmospheric Flight Mechanics; 9-11 Aug. 1999; Portland, OR; United States
Meeting Sponsor: American Inst. of Aeronautics and Astronautics; Reston, VA United States
Financial Sponsor: NASA Langley Research Center; Hampton, VA United States
Organization Source: NASA Langley Research Center; Hampton, VA United States
Description: 16p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: X-33 REUSABLE LAUNCH VEHICLE; SINGLE STAGE TO ORBIT VEHICLES; HYPERSONIC FLIGHT; HYPERSONIC SPEED; SPACECRAFT CONFIGURATIONS; LAUNCH VEHICLE CONFIGURATIONS; AERODYNAMIC CONFIGURATIONS; AERODYNAMIC CHARACTERISTICS; ANGLE OF ATTACK; THERMAL PROTECTION; LONGITUDINAL CONTROL; NAVIER-STOKES EQUATION; FINITE VOLUME METHOD; EULER EQUATIONS OF MOTION; WIND TUNNEL TESTS
Availability Source: Other Sources
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