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Boeing AV-8 Harrier
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Boeing C-17 Globemaster III
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Boeing F-15 Eagle
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Boeing F-18 Hornet
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Boeing T-45 Goshawk
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Fairchild A-10 Thunderbolt II
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General Dynamics F-111 Aardvark
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  4. Polhamus, E. C.: Application of Slender Wing Benefits to Military Aircraft. AIAA-83-2566, 1983.
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  33. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
Grumman A-6 Intruder
  1. Mercer, Charles E.; Salters, Leland B., Jr.; and Capone, Francis J.: Afterbody Temperatures, Pressures, and Aerodynamic Characteristics Resulting From Extension of Speed-Brake Configurations Into the Exhaust Jets of a Twin-Engine Attack-Type-Airplane Model. NASA TM X-517, 1961.
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Grumman EA-6B Prowler
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  6. Hanley, Robert J.: Development of an Airframe Modification To Improve the Mission Effectiveness of the EA-6B Airplane. A Collection of Technical Papers—AIAA 5th Applied Aerodynamics Conference, Aug. 1987, pp. 241–247. (Available as AIAA-87-2358.)
Grumman F-14 Tomcat
  1. Harris, Roy V.; et. al.: Summary of Langley Contributions to the F-14, F-15, F-16, and F-18 Fighter Aircraft. Memorandum to the Director from Chief, High-Speed Aerodynamics Division. NASA Internal Memo, Aug. 26, 1981.
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  7. Putnam, Lawrence E.: Effects of Modifications and External Stores on Aerodynamic Characteristics of a Fighter Airplane With Variable-Sweep Wing and Twin Vertical Tails at Mach 0.65 to 2.01. NASA TM X-2366, 1974.
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  11. Reubush, David E.; and Berrier, Bobby L.: Effects of the Installation and Operation of Jet-Exhaust Yaw Vanes on the Longitudinal and Lateral-Directional Characteristics of the F-14 Airplane. NASA TP-2769, 1987.
  12. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
Grumman X-29 Advanced Technology Demonstrator
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  5. Doggett, Robert V., Jr.; and Ricketts, Rodney H.: Dynamic Response of a Forward-Swept-Wing Model at Angles of Attack up to 15¾ at a Mach Number of 0.8. NASA TM-81863, 1980.
  6. Murri, D. G.; Croom, M. A.; and Nguyen, L. T.: High Angle-of-Attack Flight Dynamics of a Forward-Swept Wing Fighter Configuration. AIAA-83-1837, 1983.
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  9. Fratello, David J.; Croom, Mark A.; Nguyen, Luat T.; and Domack, Christopher S.: Use of the Updated NASA Langley Radio-Controlled Drop-Model Technique for High-Alpha Studies of the X-29A Configuration. A Collection of Technical Papers—AIAA Atmospheric Flight Mechanics Conference, Aug. 1987, pp. 305–317. (Available as AIAA-87-2559.)
  10. Raney, David L.; and Batterson, James G.: Lateral Stability Analysis for X-29A Drop Model Using System Identification Methodology. NASA TM-4108, 1989.
  11. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
Lockheed Martin C-130 Hercules
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Lockheed Martin C-141 Starlifter
  1. Ruhlin, Charles L.; Sandford, Maynard C.; and Yates, E. Carson, Jr.: Wind-Tunnel Flutter Studies of the Sweptback T-Tail of a Large Multijet Cargo Airplane at Mach Numbers to 9.90. NASA TN D-2179, 1964.
  2. Sandford, Maynard C.; Ruhlin, Charles L.; and Yates, E. Carson, Jr.: Subsonic and Transonic Flutter and Flow Investigations of the T-Tail of a Large Multijet Cargo Airplane. NASA TN D-4316, 1968.
  3. Sandford, Maynard C.; and Ruhlin, Charles L.: Wind-Tunnel Study of Deflected-Elevator Flutter Encountered on a T-Tail Airplane. NASA TN D-5024, 1969.
  4. Abel, Irving: Evaluation of a Technique for Determining Airplane Aileron Effectiveness and Roll Rate by Using an Aeroelastically Scaled Model. NASA TN D-5538, 1969.
  5. Cleveland, F. A.; and Gilson, R. D.: Development Highlights of the C-141 Starlifter. AIAA-64-596, 1965.
  6. Victor Crash. Aviat. Week & Space Technol., vol. 61, no. 4, July 26, 1954, p. 16.
  7. Loving, Donald L.: Wind-Tunnel—Flight Correlation of Shock-Induced Separated Flow. NASA TN D-3580, 1966.
  8. MacWilkinson, D. G.; Blackerby, W. T.; and Paterson, J. H.: Correlation of Full-Scale Drag Predictions With Flight Measurements on the C-141A Aircraft—Phase II, Wind Tunnel Test, Analysis, and Prediction Techniques. Volume 1—Drag Predictions, Wind Tunnel Data Analysis and Correlation. NASA CR-2333, 1974.
  9. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
Lockheed Martin C-5 Galaxy
  1. Luoma, Arvo A.; Re, Richard J.; and Loving, Donald L.: Subsonic Longitudinal Aerodynamic Measurements on a Transport Model in Two Slotted Tunnels Differing in Size. NASA TM X-1660, 1968.
  2. Loving Donald L.; and Luoma, Arvo A.: Sting-Support Interference on Longitudinal Aerodynamic Characteristics of Cargo-Type Airplane Models at Mach 0.70 to 0.84. NASA TN D-4021, 1967.
  3. Patterson, James C., Jr.; and Flechner, Stuart G.: Jet-Wake Effect of a High-Bypass Engine on Wing-Nacelle Interference Drag of a Subsonic Transport Airplane. NASA TN D-6067, 1970.
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  11. Perry, Boyd, III; Noll, Thomas E.; and Scott, Robert C.: Contributions of the Transonic Dynamics Tunnel to the Testing of Active Control of Aeroelastic Response. AIAA-2000-1769, 2000.
Lockheed Martin F-16 Fighting Falcon
  1. Jackson, Charles M.: NASA/General Dynamics Cooperative Research Leading to and Involving SCAMP. NASA Internal Report, May 1980.
  2. Polhamus, E. C.: Application of Slender Wing Benefits to Military Aircraft. AIAA-83-2566, 1983.
  3. Buckner, J. K.; Benepe, D. B.; and Hill, P. W.: Aerodynamic Design Evolution of the YF-16. AIAA-74-935, Aug. 1974.
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  5. Peloubet, R. P., Jr.; and Haller, R. L.: Wind-Tunnel Demonstration of Active Flutter Suppression Using F-16 Model With Stores. AFWAL-TR 83-3046, Vol.1, 1983.
  6. Foughner, J. T., Jr.; and Bensinger, C. T.: F-16 Flutter Model Studies With External Wing Stores. NASA TM-74078, 1977.
  7. Perry, Boyd, III; Noll, Thomas E.; and Scott, Robert C.: Contributions of the Transonic Dynamics Tunnel to the Testing of Active Control of Aeroelastic Response. AIAA-2000-1769, 2000.
Lockheed Martin F-22 Raptor
  1. Mullin, Sherman N.: The Evolution of the F-22 Advanced Tactical Fighter. Wright Brothers Lecture, AIAA-92-4188, 1992.
  2. Aronstein, David C.; Hirchberg, Michael J.; and Piccirillo, Albert C.: Advanced Tactical Fighter to F-22 Raptor—Origins of the 21st Century Air Dominance Fighter. AIAA, 1998.
Lockheed Martin P-3 Orion
  1. Baals, Donald D.; and Corliss, William R.: Wind Tunnels of NASA. NASA SP-440, 1981.
  2. Abbot, F. T., Jr; Kelly, H. Neale; and Hampton, Kenneth D.: Investigation of Propeller-Power-Plant Auto-Precession Boundaries for a Dynamic-Aeroelastic Model of a Four-Engine Turboprop Transport Airplane. NASA TN D-1806, June 1963.
  3. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
Lockheed Martin S-3 Viking
  1. Lee, Henry A.; and White, William L.: Spin-Tunnel Investigation of a 1/32-Scale Model of the Lockheed S-3A Airplane—COORD No. N-AM-161. NASA TM SX-3057, U.S. Navy, 1974.
  2. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
McDonnell Douglas F-4 Phantom II
  1. Carmel, Melvin M.; and Gregory, Donald T.: Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a Model of a 45¾ Swept Wing Airplane at Mach Numbers of 1.59, 1.89, and 2.09. NASA MEMO 3-30-59L, 1959.
  2. Carmel, Melvin M.; and Turner, Kenneth L.: Investigation of Drag and Static Longitudinal and Lateral Stability and Control Characteristics of a Model of a 45¾ Swept Wing Airplane at Mach Numbers of 1.57, 1.87, 2.16, and 2.53, Phase II Model. NASA MEMO 3-31-59L, 1959.
  3. Oehman, Waldo I.; and Turner, Kenneth L.: Aerodynamic Characteristics of a 45¾ Swept-Wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53. NACA RM L58C17, 1958.
  4. Chambers, Joseph R.; and Anglin, Ernie L.: Analysis of Lateral-Directional Stability Characteristics of a Twin-Jet Fighter Airplane at High Angles of Attack. NASA TN D-5361, 1969.
  5. Chambers, Joseph R.; Bowman, James S., Jr.; and Anglin, Ernie L.: Analysis of the Flat-Spin Characteristics of a Twin-Jet Swept-Wing Fighter Airplane. NASA TN D-5409, 1969.
  6. Ray, Edward J.; and Hollingsworth, Eddie G.: Subsonic Characteristics of a Twin-Jet Swept-Wing Fighter Model With Maneuvering Devices. NASA TN D-6921, 1973.
  7. Moore, Frederick L.; Anglin, Ernie L.; Adams, Mary S.; Deal, Perry L.; and Person, Lee H., Jr.: Utilization of a Fixed-Base Simulator To Study the Stall and Spin Characteristics of Fighter Airplanes. NASA TN D-6117, 1971.
  8. Newsom, William A., Jr.; and Grafton, Sue B.: Free-Flight Investigation of Effects of Slats on Lateral-Directional Stability of a 0.13-Scale Model of the F-4E Airplane—COORD No. AF-AM-113. NASA TM SX-2337, U.S. Air Force, 1971.
  9. Doggett, R. V.; and Hanson, P. H.: Wind Tunnel Buffet Pressure Investigation on the Lower Nose Portion of the RF-4C Aircraft. NASA LWP-227, 1966.
Missiles
  1. Blair, A. B., Jr.; Allen, Jerry M.; and Hernandez, Gloria: Effect of Tail-Fin Span on Stability and Control Characteristics of a Canard-Controlled Missile at Supersonic Mach Numbers. NASA TP-2157, 1983.
  2. Blair, A. B., Jr.; and Rapp, G. H.: Experimental and Analytical Comparison of Aerodynamic Characteristics of a Forward-Control Missile. AIAA-80-0374, 1980.
Rockwell B-1 Lancer
  1. Newsom, William A., Jr.; and Grafton, Sue B.: Free-Flight Investigation of a 1/17-Scale Model of the B-1 Airplane at High Angles of Attack—COORD No. AF-AM-128. NASA TM SX-2744, U.S. Air Force, 1973.
  2. Grantham, William D.; Deal, Perry L.; and Libbey, Charles E.: Piloted Simulator Study of the Stability and Control Characteristics of the B-1 Airplane at High Angles of Attack—COORD No. AF-AM-128. NASA TM SX-3381, U.S. Air Force, 1976.
  3. Re, Richard J.; and Reubush, David E.: Effect of Several Airframe/Nozzle Modifications on the Drag of a Variable-Sweep Bomber Configuration. NASA TM-80129, 1979.
  4. Seiner, John M.; Manning, James C.; Capone, Francis J.; and Pendergraft, Odis C., Jr.: Study of External Dynamic Flap Loads on a 6 Percent B-1B Model. ASME-PAPER-91-GT-236, 1991.
  5. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
Rockwell X-31 Enhanced Fighter Maneuverability Demonstrator
  1. Croom, M. A.; and Schnellenger, H. G.: High-Alpha Flight Dynamics of the X-31 Configuration. NASA CP-3149, 1990.
  2. Knox, Fred D.: X-31 Flight Test Update. AIAA-92-1035, 1992.
  3. Banks, Daniel W.; Gatlin, Gregory M.; and Paulson, John W., Jr.: Low-Speed Longitudinal and Lateral-Directional Aerodynamic Characteristics of the X-31 Configuration. NASA TM-4351, 1992.
  4. Scott, William B.: X-31 Completes Post-Stall Test. Aviat. Week & Space Technol., vol. 138, no. 20, May 17 1993, pp. 29–30.
  5. Croom, Mark A.; Fratello, David J.; Whipple, Raymond D.; O’Rourke, Matthew J.; and Trilling, Todd W.: Dynamic Model Testing of the X-31 Configuration for High-Angle-of-Attack Flight Dynamics Research. AIAA-93-3674, 1993.
  6. Cobleigh, Brent R.: High-Angle-of-Attack Yawing Moment Asymmetry of the X-31 Aircraft From Flight Test. NASA CR-186030, 1994.
Appendix
  1. Perry, Boyd, III; Noll, Thomas E.; and Scott, Robert C.: Contributions of the Transonic Dynamics Tunnel to the Testing of Active Control of Aeroelastic Response. AIAA-2000-1769, 2000.
  2. Cole, Stanley R.; and Garcia, Jerry L.: Past, Present, and Future Capabilities of the Transonic Dynamics Tunnel from an Aeroelastic Perspective. AIAA-2000-1767, 2000.
  3. Schuster, David M.; Edwards, John W.; and Bennett, Robert M.: An Overview of Unsteady Pressure Measurements in the Transonic Dynamics Tunnel. AIAA-2000-1770, 2000.
  4. Rivera, Jose A.; and Florance, James R.: Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance. AIAA-2000-1768, 2000.
  5. Baals, D. D.; and Corliss, W. R.: Wind Tunnels of NASA. NASA SP-440, 1981.
 

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