Books on the topic 'Subsonic wind tunnels'

Watmuff, J. H. Design of a new contraction for the ARL low speed wind tunnel (U). Melbourne, Australia: Aeronautical Research Laboratories, 1986.

Gentry, Garl L. The Langley 14- by 22-foot subsonic tunnel: description, flow characteristics, and guide for users. Hampton, Va: Langley Research Center, 1990.

Bowcutt, K. G. The use of panel methods for the development of low subsonic wall interference and blockage corrections. New York: AIAA, 1985.

Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. Hampton, Va: Langley Research Center, 1989.

Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

Manuel, Gregory S. Effect of collector configuration on test section turbulence levels in an open-jet wind tunnel. Hampton, Va: Langley Research Center, 1992.

Frink, Neal T. Subsonic wind-tunnel measurements of a slender wind-body configuration employing a vortex flap. Hampton, Va: Langley Research Center, 1987.

Orie, Nettie M. User's manual for the Langley Research Center 14- by 22-foot subsonic tunnel static data acquisition system. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

Erickson, Gary E. Wind tunnel investigations of forebody strakes for yaw control on F/A-18 model at subsonic and transonic speeds. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Ulbrich, Norbert. The real-time wall interference correction system of the NASA Ames 12-foot pressure wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

Ulbrich, Norbert. The real-time wall interference correction system of the NASA Ames 12-foot pressure wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

Ulbrich, Norbert. The real-time wall interference correction system of the NASA Ames 12-foot pressure wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

Ulbrich, Norbert. The real-time wall interference correction system of the NASA Ames 12-foot pressure wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

Ulbrich, Norbert. The real-time wall interference correction system of the NASA Ames 12-foot pressure wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

Erickson, Gary E. Fiber-optic-based laser vapor screen flow visualization sysytem for aerodynamic research in larger scale subsonic and transonic wind tunnels. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Erickson, Gary E. Fiber-optic-based laser vapor screen flow visualization sysytem for aerodynamic research in larger scale subsonic and transonic wind tunnels. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Ulbrich, Norbert. Description of panel method code ANTARES. Moffett, Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 2000.

Ulbrich, Norbert. Description of panel method code ANTARES. Moffett, Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 2000.

Erickson, Gary E. Fiber-optic-based laser vapor screen flow visualization system for aerodynamic research in larger scale subsonic and transonic wind tunnels. Hampton, Va: Langley Research Center, 1994.

Erickson, Gary E. Fiber-optic-based laser vapor screen flow visualization system for aerodynamic research in larger scale subsonic and transonic wind tunnels. Hampton, Va: Langley Research Center, 1994.

Kieffer, Arthur E. Automatic control study of the icing research tunnel refrigeration system. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Hartmann, K. Experimetal investigations on wing-body combinations and their components at high angles of attack in the subsonic and transonic speed range. Köln: Deutsche Forschungsanstalt für Luft- und Raumfahrt, 1992.

Labrujere, Th E. Evaluation of measured-boundary-condition methods for 3D subsonic wall interference. Amsterdam: National Aerospace Laboratory, 1988.

Smith, J. A transonic model representation for two-dimensional wall interference assessment. Amsterdam: National Aerospace Laboratory, 1986.

United, States Congress House Committee on Science Space and Technology Subcommittee on Technology Environment and Aviation. Enhancing U.S. competitiveness: (NASA high speed and subsonic research programs) : hearing before the Subcommittee on Technology, Environment, and Aviation of the Committee on Science, Space, and Technology, U.S. House of Representatives, One Hundred Third Congress, second session, February 10, 1994. Washington: U.S. G.P.O., 1994.

United States. Congress. House. Committee on Science, Space, and Technology. Subcommittee on Technology, Environment, and Aviation. Enhancing U.S. competitiveness: (NASA high speed and subsonic research programs) : hearing before the Subcommittee on Technology, Environment, and Aviation of the Committee on Science, Space, and Technology, U.S. House of Representatives, One Hundred Third Congress, second session, February 10, 1994. Washington: U.S. G.P.O., 1994.

Smith, J. 2D wall interference assessment using "Calspan Pipes". Amsterdam: National Aerospace Laboratory, 1985.

Quinto, P. Frank. Langley 14- by 22-foot subsonic tunnel test engineer's data acquisition and reduction manual. Hampton, Va: Langley Research Center, 1994.

Erickson, Gary E. Wind tunnel investigation of the interaction and breakdown characteristics of slender-wing vortices at subsonic, transonic, and supersonic speeds. Hampton, Va: Langley Research Center, 1991.

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.

Erickson, Gary E. Wind tunnel investigation of vortex flows on F/A-18 configuration at subsonic through transonic speeds. Hampton, Va: Langley Research Center, 1991.

Applin, Zachary T. Pressure distributions from subsonic tests of a NACA 0012 semispan wing model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Applin, Zachary T. Pressure distributions from subsonic tests of a NACA 0012 semispan wing model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Mineck, Raymond E. Study of potential aerodynamic benefits from spanwise blowing at wingtip. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Mineck, Raymond E. Study of potential aerodynamic benefits from spanwise blowing at wingtip. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Spencer, Bernard. A study to determine methods of improving the subsonic performance of a proposed Personnel Launch System (PLS) concept. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Lessard, Wendy B. Subsonic analysis of 0.04-scale F-16XL models using an unstructured Euler code. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Powers, Sheryll Goecke. Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

Powers, Sheryll Goecke. Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers. Edwards, Cal: Dryden Flight Research Facility, 1986.

Powers, Sheryll Goecke. Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

American Institute of Aeronautics and As. Recommended Practice: Calibration of Subsonic and Transonic Wind Tunnels. AIAA (American Institute of Aeronautics & Ast, 2004.

Frank, Quinto P., and Langley Research Center, eds. User's manual for the model interface and plugboard cabinets in the 14- by 22-foot subsonic tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Frank, Quinto P., and Langley Research Center, eds. User's manual for the model interface and plugboard cabinets in the 14- by 22-foot subsonic tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Subsonic wind-tunnel measurements of a slender wing-body configuration employing a vortex flap. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

Subsonic wind-tunnel measurements of a slender wing-body configuration employing a vortex flap. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

American Institute of Aeronautics and As. Recommended Practice: Calibration of Subsonic and Transonic Wind Tunnels (Aiaa Standards). AIAA (American Institute of Aeronautics & Ast, 2003.

M, Krosel Susan, and United States. National Aeronautics and Space Administration., eds. A Lumped parameter mathematical model for simulation of subsonic wind tunnels. [Washington, DC]: National Aeronautics and Space Administration, 1986.