Книги з теми "Transonic tunnel"

Brooks, Cuyler W. The NASA Langley 8-Foot Transonic Pressure Tunnel calibration. Hampton, Va: Langley Research Center, 1994.

Brooks, Cuyler W. The NASA Langley 8-foot transonic pressure tunnel calibration. Hampton: National Aeronautics and Space Administration, Langley Research Center, 1994.

Everhart, Joel L. Slotted-wall flow-field measurements in a transonic wind tunnel. Hampton, Va: Langley Research Center, 1991.

Capone, Francis J. The NASA Langley 16-Foot Transonic Tunnel: Historical overview, facility description, calibration, flow characteristics, and test capabilities. Hampton, Va: Langley Research Center, 1995.

Kuczka, Detlef. Hybridverfahren fur instationare Messungen in trassonischen Windkanalen am Beispiel der harmonischen Nickschwingung. Koln: DFVLR, 1988.

Bruce, Robert A. A vapor generator for transonic flow visualization. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

Bruce, Robert A. A vapor generator for transonic flow visualization. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

Al-Saadi, Jassim A. Wall interference and boundary simulation in a transonic wind tunnel with a discretely slotted test section. Hampton, Va: Langley Research Center, 1993.

Green, Lawrence L. Wall-interference assessment and corrections for transonic NACA 0012 airfoil data from various wind tunnels. Hampton, Va: Langley Research Center, 1991.

Schairer, Edward T. A two-dimensional adaptive-wall test section with ventilated walls in the Ames 2- by 2-foot transonic wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

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

Mabey, Dennis G. Further buffeting tests in a cryogenic wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

Sudani, Norikazu. Evaluation of NACA0012 airfoil test results in the NAL two-dimensional transonic wind tunnel. Tokyo, Japan: National Aerospace Laboratory, 1991.

Johnson, William G. Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Johnson, William G. Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Ohman, L. H. New transonic test sections for the NAE 5ftx5ft trisonic wind tunnel. Ottawa: National Aeronautical Establishment, 1990.

Schuster, D. M. Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2001.

E, Mercer Charles, and Langley Research Center, eds. Computations for the 16-foot transonic tunnel, NASA, Langley Research Center. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

Murthy, A. V. Sidewall boundary-layer measurements with upstream suction in the Langley 0.3-meter Transonic Cryogenic Tunnel. Hampton, Va: Langley Research Center, 1988.

Nugent, Jack. Comparison of wind tunnel and flight test afterbody and nozzle pressures for a twin-jet fighter aircraft at transonic speeds. Edwards, Calif: Ames Research Center, 1987.

S, Balakrishna. Performance of the active sidewall boundary-layer removal system for the Langley 0.3-meter transonic cryogenic tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

Mokry, M. Influence of the transonic doublet in the farfield of a lifting airfoil. Ottawa: National Research Council Canada, Institute for Aerospace Research, 1993.

Transonic Wind Tunnel Testing. Dover Publications, 2007.

Mass flux similarity for slotted transonic-wind-tunnel walls. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1991.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. The status of two-dimensional testing at high transonic speeds in the University of Southampton transonic self-streamlining wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. The status of two-dimensional testing at high transonic speeds in the University of Southampton transonic self-streamlining wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

1952-, Harris Charles D., Reagon Patricia G, and Langley Research Center, eds. The NASA Langley 8-foot transonic pressure tunnel calibration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

1952-, Harris Charles D., Reagon Patricia G, and Langley Research Center, eds. The NASA Langley 8-foot transonic pressure tunnel calibration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

1952-, Harris Charles D., Reagon Patricia G, and Langley Research Center, eds. The NASA Langley 8-foot transonic pressure tunnel calibration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Slotted-wall flow-field measurements in a transonic wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

Slotted-wall flow-field measurements in a transonic wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

B, Igoe William, Flechner Stuart G, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, eds. Slotted-wall flow-field measurements in a transonic wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

B, Igoe William, Flechner Stuart G, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Slotted-wall flow-field measurements in a transonic wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

K, Abeyounis W., and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Kelly, Abeyounis William, and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Kelly, Abeyounis William, and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

National Aeronautics and Space Administration (NASA) Staff. NASA Langley 8-Foot Transonic Pressure Tunnel Calibration. Independently Published, 2018.

S, Hill Acquilla, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Calibration of the 13- by 13-inch adaptive wall test section for the Langley 0.3-Meter Transonic Cryogenic Tunnel. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Allen, Kilgore W., and Langley Research Center, eds. Microcomputer based controller for the Langley 0.3-meter Transonic Cryogenic Tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

Experimental studies of transonic flow field near a longitudinally slotted wind tunnel wall. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Seizo, Sakakibara, and United States. National Aeronautics and Space Administration., eds. Flow quality of NAL two-dimensional transonic wind tunnel. Washington, D.C: National Aeronautics and Space Administration, 1988.

R, Sprinkle Danny, and Langley Research Center, eds. Langley 16-ft. Transonic Tunnel Pressure Sensitive Paint System. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2001.

Seizo, Sakakibara, and United States. National Aeronautics and Space Administration., eds. Flow quality of NAL two-dimensional transonic wind tunnel. Washington, D.C: National Aeronautics and Space Administration, 1988.

Langley 16-ft. Transonic Tunnel Pressure Sensitive Paint System. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2001.

R, Sprinkle Danny, and Langley Research Center, eds. Langley 16-ft. Transonic Tunnel Pressure Sensitive Paint System. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2001.

S, Hill Acquilla, and Langley Research Center, eds. High Reynolds number transonic tests of an NACA 0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

A two-dimensional adaptive-wall test section with ventilated walls in the Ames 2- by 2-foot transonic wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

A two-dimensional adaptive-wall test section with ventilated walls in the Ames 2- by 2-foot transonic wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

Pressure distributions from high Reynolds number transonic tests of an NACA 0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.