Books on the topic 'Wind tunnel cascade test'

Norris, R. B. The flying wind tunnel. New York: AIAA, 1989.

B, Kelley P., and United States. National Aeronautics and Space Administration, eds. Wind tunnel test IA300 analysis and results. Huntsville, AL: Lockheed Missiles & Space Co., Huntsville Engineering Center, 1987.

K, Wailes W., and Ames Research Center, eds. Advanced recovery systems wind tunnel test report. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

Keas, Paul. SOFIA II model telescope and wind tunnel test. [Moffett Field, Calif.]: NASA Ames Research Center, 1995.

Baydar, Adem. Hot-wire measurements of compressor blade wakes in a cascade wind tunnel. Monterey, California: Naval Postgraduate School, 1988.

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.

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.

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

Randall, Peterson, and Ames Research Center, eds. Shake test results of the MDHC test stand in the 40- by 80-foot wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

L, Peterson Randall, and Ames Research Center, eds. Shake test results of the MDHC test stand in the 40- by 80-foot wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

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

Glynn, J. L. Space shuttle phase B wind tunnel model and test information. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

Allen, Dale, Lorber Peter, and Ames Research Center, eds. Wind tunnel test of a variable-diameter tiltrotor (VDTR) model. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

Center, Ames Research, ed. Analysis of the free-tip rotor wind-tunnel test results. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.

Glynn, J. L. Space shuttle Phase B wind tunnel test database: Summary report. Hampton, Va: Langley Research Center, 1988.

Center, Ames Research, ed. Analysis of the free-tip rotor wind-tunnel test results. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.

Khadjavi, F. Two-dimensional test section with preadjusted adaptive walls for low speed wind tunnel. Stockholm: Royal Institute of Technology, Department of Aeronautics, 1987.

Center, Langley Research, ed. Wall adjustment strategy software for use with the NASA Langley 0.3-meter transonic cryogenic tunnel adaptive wall test section. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

Hoad, Danny R. Rotor performance characteristics from an aeroacoustics helicopter wind-tunnel test program. Hampton, Va: Langley Research Center, 1986.

W, Elliott Joe, Orie Nettie M, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., United States. Army Aviation Systems Command., and Langley Research Center, eds. Rotor performance characteristics from an aeroacoustic helicopter wind-tunnel test program. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

National Research Council of Canada. and National Aeronautical Establishment (Canada), eds. New transonic test sections for the NAE 5ftx5ft trisonic wind tunnel. Ottawa: National Research Council Canada, 1990.

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.

Murray, Kenneth Douglas. Automation and extension of LDV measurements of off-design flow in a cascade wind tunnel. Monterey, Calif: Naval Postgraduate School, 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.

Center, Langley Research, ed. The experimental verification of wall movement influence coefficients for an adaptive walled test section. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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.

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.

Center, Lewis Research, and United States. National Aeronautics and Space Administration., eds. Flow field surveys of the NASA Lewis Research Center 8- by 6-foot supersonic wind tunnel (1993 test). [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

A, Campbell William. Large scale advanced prop-fan (LAP) high speed wind tunnel test report. [Windsor Locks, CT]: Hamilton Standard Division, United Technologies Corporation, 1989.

R, Riley Donald, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Low-speed wind-tunnel test of a STOL supersonic-cruise fighter concept. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

R, Moes Timothy, and Dryden Flight Research Facility, eds. Wind-tunnel development of an SR-71 aerospike rocket flight test configuration. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1996.

R, Moes Timothy, and Dryden Flight Research Facility, eds. Wind-tunnel development of an SR-71 aerospike rocket flight test configuration. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1996.

Coe, Paul L. Low-speed wind-tunnel test of a STOL supersonic-cruise fighter concept. Hampton, Va: Langley Research Center, 1988.

R, Riley Donald, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Low-speed wind-tunnel test of a STOL supersonic-cruise fighter concept. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

United States. National Aeronautics and Space Administration., ed. SOFIA, AFT cavities wind tunnel test: SOFIA II, final report : appendix E. [Washington, DC: National Aeronautics and Space Administration, 1994.

R, Riley Donald, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Low-speed wind-tunnel test of a STOL supersonic-cruise fighter concept. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

Sprinkle, Danny R. Langley 8-ft. HTT test 139 gas analyses. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Sprinkle, Danny R. Langley 8-ft. HTT test 139 gas analyses. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

P, Davis Patricia, and Langley Research Center, eds. Langley 8-ft. HTT test 139 gas analyses. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Sprinkle, Danny R. Langley 8-ft. HTT test 139 gas analyses. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Sprinkle, Danny R. Langley 8-ft. HTT test 139 gas analyses. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Sprinkle, Danny R. Langley 8-ft. HTT test 139 gas analyses. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

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.

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.

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

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.

United States. National Aeronautics and Space Administration., ed. Methods for scaling icing test conditions. [Washington, DC]: National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Computer simulation of a wind tunnel test section with discrete finite-length wall slots. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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.