Bücher zum Thema „Wing test“

Goodyer, M. J. A swept wing panel in a low speed flexible walled test section. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

Goodyer, M. J. A swept wing panel in a low speed flexible walled test section. Hampton, Va: Langley Research Center, 1987.

C, Wilson John. Wind tunnel test results of a 1/8-scale fan-in-wing model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Phelps, Arthur E. Description of the U.S. Army small-scale 2-meter rotor test system. Hampton, Va: Langley Research Center, 1987.

Lance, Michael B. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Lance, Michael B. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. Hampton, Va: Langley Research Center, 1991.

Yip, Long P. Static wind-tunnel and radio-controlled flight test investigation of a remotely piloted vehicle having a delta wing planform. Hampton, Va: Langley Research Center, 1990.

Yip, Long P. Static wind-tunnel and radio-controlled flight test investigation of a remotely piloted vehicle having a delta wing planform. Hampton, Va: Langley Research Center, 1990.

Larson, Richard R. Flight control system development and flight test experience with the F-111 mission adaptive wing aircraft. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1986.

MacKinnon, A. Wind tunnel tests on a variable camber wing. Cranfield, Bedford, England: College of Aeronautics, Cranfield University, 1993.

Buttrill, Carey S. Aeroservoelastic simulation of an active flexible wing wind tunnel model. Hampton, Va: Langely Research Center, 1996.

F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration (1992 Edwards, Calif.). Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration: Proceedings of an anniversary celebration held at NASA Dryden Flight Research Center, Edwards, California, May 27, 1992. Edwards, Calif: The Division, 1996.

F-8, Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration (1992 Edwards Calif ). Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration: Proceedings of an anniversary celebration held at NASA Dryden Flight Research Center, Edwards, California, May 27, 1992. Edwards, Calif: The Division, 1996.

F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration (1992 Edwards, Calif.). Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration: Proceedings of an anniversary celebration held at NASA Dryden Flight Research Center, Edwards, California, May 27, 1992. Edwards, Calif: The Division, 1996.

F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration (1992 Edwards, Calif.). Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration: Proceedings of an anniversary celebration held at NASA Dryden Flight Research Center, Edwards, California, May 27, 1992. Edwards, Calif: The Division, 1996.

Bolonkin, Alexander. Estimated benefits of variable-geometry wing camber control for transport aircraft. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

Mineck, Raymond E. Wind-tunnel investigation of aerodynamic efficiency of three planar elliptical wings with curvature of quarter-chord line. Hampton, Va: Langley Research Center, 1993.

Petersen, Søren Markkilde. Wind turbine test NORDTANK NTK 500/37 system test. Roskilde, Denmark: Risø National Laboratory, 1994.

Pedersen, Troels Friis. Wind Turbine Test Wind Matic WM 17S. Roskilde: Riso National Laboratory, 1986.

Pedersen, Troels Friis. Wind Turbine Test Wind Matic WM 15S. Roskilde: Riso National Laboratory, 1986.

Peter, Bradshaw. Flow over swept flaps and flap tips: Final technical report to NASA Langley Research Center on NAG-1-1614. [Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Martin, Colin A. Surface pressure measurements on the wing of a wind tunnel model during steady rotation. Melbourne, Australia: Aeronautical Research Laboratory, 1991.

Paulsen, Uwe Schmidt. Wind Turbine Test Bonus 95 kw. Roskilde: Riso National Laboratory, 1987.

Pedersen, Troels Friis. Wind turbine test micon 55 kw. Roskilde, Denmark: Riso National Laboratory, 1986.

Pedersen, Troels Friis. Wind Turbine Test Nordtank 55 KW. Roskilde, Denmark: Riso National Laboratory, 1986.

Pedersen, Troels Friis. Wind Turbine Test Danwin 23 Prototype. Roskilde, Denmark: Riso National Laboratory, 1988.

1962-, Anderson Kevin J., Hrsg. Hurtling wings. Hollywood, CA: Galaxy Press, 2007.

Galway, R. D. The IAR high Reynolds number two-dimensional test facility - a description of equipment and procedures common to most 2-D airfoil tests. Ottawa: National Research Council of Canada, Institute for Aerospace Research, 1990.

Galway, R. D. The IAR High Reynolds Number Two-Dimensional Test Facility - a description of equipment and procedures common to most 2-D airfoil tests. Ottawa, Ont: National Research Council Canada, Institute for Aerospace Research, 1990.

Applin, Zachary T. Wing pressure distributions from subsonic tests of a high-wing transport model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Applin, Zachary T. Wing pressure distributions from subsonic tests of a high-wing transport model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

A, Kennelly Robert, und Ames Research Center, Hrsg. Transonic wind tunnel test of a 14% thick oblique wing. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

Tip aerodynamics from wind tunnel test of semi-span wing. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1986.

E, Walker Charlotte, und Langley Research Center, Hrsg. Computational test cases for a rectangular supercritical wing undergoing pitching oscillations. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Obara, Derrick. West Wing Trivia: 100 Questions and Answer about the West Wings to Test Your Knowledge. Independently Published, 2020.

Center, Langley Research, Hrsg. Low speed wind tunnel test of a propulsive wing/canard concept in the STOL configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

E, Erickson R., und Ames Research Center, Hrsg. NASA rotor systems research aircraft fixed-wing configuration flight-test results. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.

Detailed analysis and test correlation of a stiffened composite wing panel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

W, Kehoe M., und Langley Research Center, Hrsg. Flight test of a decoupler pylon for wing/store flutter suppression. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

L, Lawing Pierce, und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

L, Lawing Pierce, und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

L, Lawing Pierce, und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

L, Lawing Pierce, und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Wing force and surface pressure data from a hover test of a 0.658-scale V-22 rotor and wing. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

Y, Sung Daniel, Stroub Robert H und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Y, Sung Daniel, Stroub Robert H und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Y, Sung Daniel, Stroub Robert H und United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., Hrsg. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Vertical drop test of a transport fuselage section located aft of the wing. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

B, Smeltzer D., Smith Ronald C und Ames Research Center, Hrsg. Test results at transonic speeds on a contoured over-the-wing propfan model. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

Flight test results from a supercritical mission adaptive wing with smooth variable camber. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.