Books on the topic 'Wind tunnel noise'

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

Abrahamson, A. Louis. An evaluation of proposed acoustic treatments for the NASA LaRC 4 x 7 meter wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 Wind Tunnel and extrapolated to far field. Moffett Field, Calif: Ames Research Center, 1991.

Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 wind tunnel and extrapolated to far field. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 wind tunnel and extrapolated to far field. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Martin, R. M. Acoustic measurements from a rotor blade-vortex interaction noise experiment in the German-Dutch Wind Tunnel (DNW). Hampton, Va: Langley Research Center, 1988.

Soderman, Paul T. Sources and levels of background noise in the NASA Ames 40- by 80-foot wind tunnel: A status report. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

Block, P. J. W. Directory and trends of noise generated by a propeller in a wake. Hampton, Va: Langley Research Center, 1986.

Fears, Scott P. Low-speed wind-tunnel investigation of a porous forebody and nose strakes for yaw control of a multirole fighter aircraft. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Fears, Scott P. Low-speed wind-tunnel investigation of a porous forebody and nose strakes for yaw control of a multirole fighter aircraft. Hampton, Va: Langley Research Center, 1995.

Brandon, Jay M. Low-speed wind-tunnel investigation of the effect of strakes and nose chines on lateral-directional stability of a fighter configuration. Hampton, Va: Langley Research Center, 1986.

National Aeronautics and Space Administration (NASA) Staff. Active Control of Wind Tunnel Noise. Independently Published, 2018.

R, Booth Earl, and Langley Research Center, eds. Acoustic survey of a 3/8-scale automotive wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Active control of wind tunnel noise: A technical report ... [Washington, DC: National Aeronautics and Space Administration, 1991.

B, Connor Andrew, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Wind-tunnel acoustic results of two rotor models with several tip designs. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

B, Connor Andrew, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Wind-tunnel acoustic results of two rotor models with several tip designs. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

B, Connor Andrew, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Wind-tunnel acoustic results of two rotor models with several tip designs. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

United States. National Aeronautics and Space Administration., ed. Cruise noise of counterrotation propeller at angle of attack in wind tunnel. [Washington, D.C.]: National Aeronautics and Space Administration, 1987.

Wind-tunnel acoustic results of two rotor models with several tip designs. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

Comparison of propeller cruise noise data taken in the NASA Lewis 8- by 6-foot wind tunnel with other tunnel and flight data. [Washington, DC]: National Aeronautics and Space Administration, 1989.

Current wind tunnel capability and planned improvements at Lewis Research Center. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis 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.

The effect of swirl recovery vanes on the cruise noise of an advanced propeller. [Washington, DC]: National Aeronautics and Space Administration, 1990.

1956-, Martin R. M., and Ames Research Center, eds. Background noise measurements from jet exit vanes designed to reduce flow pulsations in an open-jet wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1985.

E, Beckwith Ivan, Chen Fang-Jenq, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

E, Beckwith Ivan, Chen Fang-Jenq, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Fluctuating pressures on fan blades of a turbofan engine: Flight test investigation. Washington, D.C: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Sources and levels of background noise in the NASA Ames 40- by 80-foot wind tunnel: A status report. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

J, McDonald Timothy, and NASA Glenn Research Center, eds. Static and wind tunnel aero-performance tests of NASA AST separate flow nozzle noise reduction configurations. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

P, Woodward Richard, and United States. National Aeronautics and Space Administration., eds. Background noise levels measured in the NASA Lewis 9-by 15-foot low-speed wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., ed. Background noise levels measured in the NASA Lewis 9-by 15-foot low-speed wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, 1995.

National Aeronautics and Space Administration (NASA) Staff. Sources and Levels of Background Noise in the NASA Ames 40- by 80-Foot Wind Tunnel. Independently Published, 2018.

United States. National Aeronautics and Space Administration., ed. Flow structure generated by perpendicular blade vortex interaction and implications for helicopter noise predictions. [Washington, D.C: National Aeronautics and Space Administration, 1994.

Flow structure generated by perpendicular blade vortex interaction and implications for helicopter noise predictions: Semi-annual report to NASA Langley for worked performed under the grant. [Washington, DC: National Aeronautics and Space Administration, 1995.

Flow structure generated by perpendicular blade vortex interaction and implications for helicopter noise predictions: Semi-annual report to NASA Langley for worked performed under the grant. [Washington, DC: National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., ed. Ultra-high bypass ratio jet noise. [Washington, D.C.]: National Aeronautics and Space Administration, 1994.

United States. National Aeronautics and Space Administration., ed. Ultra-high bypass ratio jet noise. [Washington, D.C.]: National Aeronautics and Space Administration, 1994.

United States. National Aeronautics and Space Administration., ed. Ultra-high bypass ratio jet noise. [Washington, D.C.]: National Aeronautics and Space Administration, 1994.

R, Allmen J., Soderman Paul T, and Ames Research Center, eds. Modification of the Ames 40- by 80-foot wind tunnel for component acoustic testing for the second generation supersonic transport. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

A quiet tunnel investigation of hypersonic boundary-layer stability over a cooled, flared cone: Final report. Norfolk, Va: Dept. of Mechanical Engineering, College of Engineering & Technology, Old Dominion University, 1996.

Center, Langley Research, ed. Nacelle integration to reduce the sonic boom of aircraft designed to cruise at supersonic speeds. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Noise measurements from an ejector suppressor nozzle in the NASA Lewis 9- by 15-foot low speed wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, 1990.

Noise of a simulated installed model counter rotation propeller at angle-of-attack and takeoff/approach conditions. [Washington, D.C.]: National Aeronautics and Space Administration, 1990.

Center, NASA Glenn Research, ed. Acoustic and aerothermal performance test of the axisymmetric coannular ejector nozzle. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2000.

Blade-mounted flap control for BVI noise reduction proof-of-concept test. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Ndaona, Chokani, and Langley Research Center, eds. Hypersonic boundary-layer stability experiments on a flared-cone model at angle of attack in a quiet wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Ndaona, Chokani, and Langley Research Center, eds. Hypersonic boundary-layer stability experiments on a flared-cone model at angle of attack in a quiet wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Ndaona, Chokani, and Langley Research Center, eds. Hypersonic boundary-layer stability experiments on a flared-cone model at angle of attack in a quiet wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Ndaona, Chokani, and Langley Research Center, eds. Hypersonic boundary-layer stability experiments on a flared-cone model at angle of attack in a quiet wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.