Książki na temat „Wind tunnel cascade test”

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

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

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

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

Kelly, Abeyounis William, i Langley Research Center, red. 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, i Ames Research Center, red. 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, i Ames Research Center, red. 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, i Ames Research Center, red. 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 i Ames Research Center, red. 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, red. 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, red. 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, red. 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. i Langley Research Center, red. 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. i National Aeronautical Establishment (Canada), red. 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, red. 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, i United States. National Aeronautics and Space Administration., red. 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, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. 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, i Dryden Flight Research Facility, red. 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, i Dryden Flight Research Facility, red. 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, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. 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., red. SOFIA, AFT cavities wind tunnel test: SOFIA II, final report : appendix E. [Washington, DC: National Aeronautics and Space Administration, 1994.

R, Riley Donald, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. 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, i Langley Research Center, red. 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, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. 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., red. 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., red. 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.