High-angle-of-attack yawing moment asymmetry of the X-31 aircraft from flight test
Author:
Affiliation:
1. PRC, Inc., Edwards, CA
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1994-1803
Reference23 articles.
1. Controlling forebody asymmetries in flight - Experience with boundary layer transition strips
2. 2Croom, Mark A., David J. Fratello, Raymond D. Whipple, Matthew J. O'Rourke, and Todd W. Trilling, "Dynamic Model Testing of the X-31 Configuration for HighAngleof Attack Flight DynamicsResearch," AIAA 93-3674CP,FlightMechanicsConference,Monterey,CA, Aug.9-11,1993.
3. %eerier, Earl P., Gary T. Chapman, Lee Cohen, and Jamshid Taleghani, Side Forces on a Tangent Ogive Forebody witha FinenessRatio of 3J atHighAngles of Attack and Mach Numbers from .I to .7, NASA TM X-3437,1977.
4. 4Lamont,PJ. "Pressure Measurements on an Ogive-Cylinder at High Anglesof Attack with Laminar,Transitional,orTurbulentSeparation,"AIAA80-1556,Jan.1980.
5. Experimental investigation of a new device to control the asymmetricflowfield on forebodies at large angles of attack
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