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X-29 High AOA Flight Test Results: An Overview
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Abstract
An extensive high angle-of-attack (AOA) flight testing program has been performed with the X-29-2 (AF 82-0049) forward swept wing research aircraft. The high AOA envelope expansion phase cleared the aircraft to fly in a broad flight regime and produced important data on the high AOA clearance process and data analysis. Lessons learned during the military utility phase on the tactical advantages and disadvantages associated with high AOA maneuvering are impacting programs such as the X-31, HARV, and F-22. Insight on the critical forebody flow-field of the X-29 at high AOA was gained using on-surface pressure measurements and off-surface flow visualization during the aerocharacterization phase. The Vortex Flow Control (VFC) experiment conducted on the X-29 successfully proved the viability of a pneumatic blowing device manipulating forebody vortices to act as an aircraft controller, an historical first. Finally, throughout the aircraft #2 flight test program, important data concerning the aircraft’s air data system, digital flight control system, vertical tail, engine, and subsystems operating in the high AOA environment were gathered. This paper is intended as a broad overview of the high AOA testing of the X - 29, with the purpose of directing the reader towards the numerous excellent references which describe the flight test program in more detail.
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Authors
Citation
Smith, W., "X-29 High AOA Flight Test Results: An Overview," SAE Technical Paper 931367, 1993, https://doi.org/10.4271/931367.Also In
References
- Trippensee, G. Update of the X-29 High-Angle-of-Attack Program SAE 912006 presented at the International Pacific Air & Space Technology Conference Gisu, Japan October 1991
- Herbst, W. Future Fighter Techniques Journal of Aircraft August 1980
- Huband, G. Gillard, W. X-29 High Angle-of-Attack Flight Testing-Program Status AIM-90-3303 presented at AIAA/AHS/ASEE Aircraft, Design, Systems, and Operations Conference Dayton, OH September 1990
- Webster, F. Purifoy, D. X-29A High Angle of Attack Flying Qualities AFFTC-TR-91-15 July 1991
- Walchli, L. Smith, R. Flying Qualities of the X-29 Forward Swept Wing presented at the AGARD Flight Mechanics Panel Symposium on Flying Qualities Quebec City, Canada October 1990
- Trippensee, G. Lux, D. X-29A Forward-Swept-Wing Flight Research Program Status NASA TM-100413 1987
- Pellicano, P., X-29 High Angle-of-Attack Flight Test Procedures, Results, and Lessons Learned presented at the Society of Flight Test Engineers 21st Annual Symposium, Garden Grove, CA August 1990
- Ishmael, S., X-29 High Angle of Attack presented at the 34th Society of Experimental Test Pilots Symposium Beverly Hills, CA September 1990
- Smith, R. Flying Qualities Development for the X-29A Demonstrator presented at the German Aerospace Research Establishment (DLR) International Symposium In-Flight Simulation for the ‘90’s Braunschweig, Germany July 1991
- Lawless, A. Butts, S. Flight Testing for Aircraft Agility AIAA-90-1308 presented at the Fifth Biennial Flight Test Conference Ontario, CA, May 1990
- Butts, S. X-29A High Angle-of-Attack Agility Flight Test Results AFFTC-TIM-91-02 September 1991
- Smith, W. Pellicano, P. X-29 High Angle-of-Attack Military Utility Flight Test Results AIAA-92-4080 presented at the Sixth Biennial Flight Test Conference Hilton Head, SC August 1992
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- Bjarke, L., A Summary of the Forebody High Angle-of-Attack Aerodynamics Research on the F-18 and the X-29A Aircraft NASA TM-104261 November 1992
- Del Frate, J. Saltzman, J. In-Flight Flow Visualization Results From the X-29A Aircraft at High Angles of Attack AIAA-92-4102 presented at the Sixth Biennial Flight Test Conference Hilton Head, SC August 1992
- Fisher, D., Correlation of Forebody Pressures and Aircraft Yawing Moments on the X-29A Aircraft at High Angles of Attack NASA TM-4417 November 1992
- Walchli, L., High Angle-of-Attack Control Enhancement on a Forward Swept Wing Aircraft AIAA-92-4427 presented at the AIAA Atmospheric Flight Mechanics Conference Hilton Head, SC August 1992
- Krumenacker, J. Pellicano, P. Flight Simulation and Data Analysis During a High Angle-of-Attack Vortex Flow Control Flight Test Program AIAA-92-4108 presented at the Sixth Biennial Flight Test Conference Hilton Head, SC August 1992
- Pellicano, P., Flight Test Techniques, Simulation and Data Analysis During a High-Angle-of-Attack Vortex Flow Control Flight Test Program presented at the Society of Flight Test Engineers Fifth European Chapter Symposium Munich, Germany September 1992
- Luria, F. Guyton, R. Flight Testing of Pneumatic Forebody Vortex Control on the X-29 Technology Demonstrator SAE- 922008 presented a Aerotech ’92 Anaheim, CA October 1992
- Skow, A., Control of Forebody Vortex Orientation to Enhance Departure Recovery of Fighter Aircraft Journal of Aircraft October 1982
- Guyton, R. Maerki, G. X-29 Forebody Jet Blowing AIAA-92-0017 presented at the 30th Aerospace Sciences Meeting & Exhibit Reno, NV January 1992
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- Clarke, R., Development and Flight Test of the X-29A High Angle-of-Attack Flight Control System NASA TM-101738, February 1991
- Rajczewski, D. X-29A High AOA Flight Test Air Data Comparisons of an INS and Noseboom Probe presented at the Society of Flight Test Engineers 21st Annual Symposium Garden Grove, CA August 1990
- Edwards, J. Deets, D. Development of a Remote Digital Augmentation System and Application to a Remotely Piloted Research Vehicle NASA TN-D-7941, April 1975
- Harter, J. Damage Tolerance Management of the X-29 Vertical Tail presented at the 1991 USAF Structural Integrity Conference San Antonio, TX December 1991
- Voracek, D. Clarke, R. An Interaction Between the Vertical Stabilizer and the Flight Control System of the X-29A Aircraft During High Angle of Attack presented at the AIAA 32nd Structures, Structural Dynamics, & Materials Conference Baltimore, MD April 1991
- Cotton, S. Bjarke, L. High Angle of Attack Flow Visualization Study of a 1/48 scale Model of the X-29A NASA TM-104268 Awaiting Publication