Livres sur le sujet « Boundary Layer Wind Tunnel (BLWT) »

O'Hare, J. E. A nonperturbing boundary-layer transition detector. Arnold Air Force Station, Tenn : Arnold Engineering Development Center, 1985.

Ginger, J. D. A computerized data acquisition system for the boundary layer wind tunnel. ST. Lucia, Q., Australia : Dept. of Civil Engineering, the University of Queensland, 1990.

Harris, Charles D. Modifications to the Langley 8-foot transonic pressure tunnel for the laminar flow control experiment. Hampton, Va : Langley Research Center, 1988.

Evans, J. Research on boundary layer transition fixing in the DREV indraft wind tunnel. Valcartier, Quebec : Defence Research Establishment, 1988.

Murthy, A. V. Effects of aspect ratio on sidewall boundary-layer influence in two-dimensional airfoil testing. Hampton, Va : Langley Research Center, 1986.

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.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. Sidewall boundary-layer measurements with upstream suction in the Langley 0.3-meter transonic cryogenic tunnel. [Washington, DC] : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

T, Pot, et United States. National Aeronautics and Space Administration., dir. Shock wave/turbulent boundary layer interaction in the flow field of a tridimensional wind tunnel. Washington D.C : National Aeronautics and Space Administration, 1987.

Kreplin, Hans-Peter. Wall shear stress measurements on a prolate spheroid at zero incidence in the DNW wind tunnel. Gottingen : Koln, 1986.

Center, Ames Research, dir. Flow unsteadiness effects on boundary layers. [Moffett Field, Calif : NASA Ames Research Center, 1989.

G, Mateer George, Menter Florian R et United States. National Aeronautics and Space Administration., dir. Boundary-layer transition and global skin friction measurement with an oil-fringe imaging technique. [Washington, DC : National Aeronautics and Space Administration, 1993.

G, Mateer George, Menter Florian R et United States. National Aeronautics and Space Administration., dir. Boundary-layer transition and global skin friction measurement with an oil-fringe imaging technique. [Washington, DC : National Aeronautics and Space Administration, 1993.

Johnson, Charles B. A description of the active and passive sidewall-boundary-layer removal systems of the 0.3-meter transonic cryogenic tunnel. [Washington, DC] : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

Johnson, Charles B. A description of the active and passive sidewall-boundary-layer removal systems of the 0.3-Meter Transonic Cryogenic Tunnel. Hampton, Va : Langley Research Center, 1986.

O, Davis D., Hihngst W. R et United States. National Aeronautics and Space Administration., dir. Flow coefficient behavior for boundary layer bleed holes and slots. [Washington, DC] : National Aeronautics and Space Administration, 1995.

1933-, Davis David O., Hihngst W. R et United States. National Aeronautics and Space Administration., dir. Flow coefficient behavior for boundary layer bleed holes and slots. [Washington, DC] : National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., dir. Hybrid laminar flow control experiments in the NASA - Ames, 11-foot tunnel : Final report. [Washington, D.C : National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., dir. Hybrid laminar flow control experiments in the NASA - Ames, 11-foot tunnel : Final report. [Washington, D.C : National Aeronautics and Space Administration, 1995.

A, Thompson R., et United States. National Aeronautics and Space Administration., dir. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va : American Institute of Aeronautics and Astronautics, 1998.

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.

Center, Langley Research, dir. Aerothermodynamic calculations on X-34 at Mach 6 wind tunnel conditions. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1999.

Wood, William A. Aerothermodynamic calculations on X-34 at Mach 6 wind tunnel conditions. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1999.

E, Beckwith Ivan, Chen Fang-Jenq et United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., dir. 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 et United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., dir. 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.

P, Willis B., Schoenenberger M et United States. National Aeronautics and Space Administration., dir. Porous and microporous honeycomb composites as potential boundary-layer bleed materials. [Washington, D.C : National Aeronautics and Space Administration, 1997.

P, Willis B., Schoenenberger M et United States. National Aeronautics and Space Administration., dir. Porous and microporous honeycomb composites as potential boundary-layer bleed materials. [Washington, D.C : National Aeronautics and Space Administration, 1997.

Schneider, Steven P. Supersonic quiet-tunnel development for laminar-turbulent transition research : Final report for NASA Langley grant NAG-1-1607. [Washington, DC : National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., dir. Supersonic quiet-tunnel development for laminar-turbulent transition research : Final report for NASA Langley grant NAG-1-1607. [Washington, DC : National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., dir. Supersonic quiet-tunnel development for laminar-turbulent transition research : Final report for NASA Langley grant NAG-1-1607. [Washington, DC : National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. NASA SC(2)-0714 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-meter transonic cryogenic tunnel. [Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

Jenkins, Renaldo V. NASA SC(2)-0714 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-Meter Transonic Cryogenic Tunnel. Hampton, Va : Langley Research Center, 1989.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. NASA SC(2)-0714 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-meter transonic cryogenic tunnel. [Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., dir. NASA SC(2)-0714 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-meter transonic cryogenic tunnel. [Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

R, Amer Tahani, et United States. National Aeronautics and Space Administration., dir. Non-linear boundary-layer receptivity due to distributed surface roughness : Final report. Norfolk, Va : Old Dominion University Research Foundation, Dept. of Mechanical Engineering, College of Engineering & Technology, 1995.

R, Amer Tahani, et United States. National Aeronautics and Space Administration., dir. Non-linear boundary-layer receptivity due to distributed surface roughness : Final report. Norfolk, Va : Old Dominion University Research Foundation, Dept. of Mechanical Engineering, College of Engineering & Technology, 1995.

Roth, J. Reece. Boundary layer flow control with a One Atmosphere Uniform Glow Disclharge Surface Plasmaa. Reston, Va : American Institute of Aeronautics and Astronautics, 1998.

B, Adcock Jerry, et Langley Research Center, dir. Tables for correcting airfoil data obtained in the Langley 0.3-meter transonic cryogenic tunnel for sidewall boundary layer effects. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1986.

Gaster, Michael. The velocity field created by a shallow bump in a boundary layer. Hampton, VA : Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1994.

Gaster, Michael. The velocity field created by a shallow bump in a boundary layer. Hampton, VA : Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1994.

Center, Ames Research, dir. Supersonic laminar flow control research : Final report, July 1994-June 1996. Tullahoma, TN : University of Tennessee, Space Institute, 1996.

Center, Ames Research, dir. Supersonic laminar flow control research : Semiannual report #4, July 1995-December 1995. Moffett Field, CA : Ames Research Center, 1995.

G, Wiberg Clark, et United States. National Aeronautics and Space Administration., dir. Supersonic laminar flow control research : NASA grant no. NAG 2-881, final report, January 1994 - June 1996. [Washington, DC : National Aeronautics and Space Administration, 1996.

Ndaona, Chokani, et Langley Research Center, dir. 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, et Langley Research Center, dir. 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, et Langley Research Center, dir. 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, et Langley Research Center, dir. 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.

Center, Lewis Research, dir. Experimental study of boundary layer behavior in a simulated low pressure turbine. [Cleveland, Ohio] : National Aeronautics and Space Administration, Lewis Research Center, 1998.

Center, Lewis Research, dir. Experimental study of boundary layer behavior in a simulated low pressure turbine. [Cleveland, Ohio] : National Aeronautics and Space Administration, Lewis Research Center, 1998.

Center, Ames Research, et United States. National Aeronautics and Space Administration., dir. Boundary layer transition in the leading edge region of a swept cylinder in high speed flow. Moffett Field, Calif : National Aeronautics and Space Administration, Ames Research Center, 1998.

S, Reibert Mark, Saric W. S et United States. National Aeronautics and Space Administration., dir. Distributed-roughness effects on stability and transition in swept-wing boundary layers : Annual technical report ... NASA-Langley cooperative agreement # NCC-1-194 and the Boeing Company contract #ZA0078, during 5/17/96-12/31/96. [Washington, DC : National Aeronautics and Space Administration, 1997.