Books on the topic '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., ed. 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, and United States. National Aeronautics and Space Administration., eds. 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, ed. Flow unsteadiness effects on boundary layers. [Moffett Field, Calif: NASA Ames Research Center, 1989.

G, Mateer George, Menter Florian R, and United States. National Aeronautics and Space Administration., eds. 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, and United States. National Aeronautics and Space Administration., eds. 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, and United States. National Aeronautics and Space Administration., eds. 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, and United States. National Aeronautics and Space Administration., eds. 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., ed. 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., ed. 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., and United States. National Aeronautics and Space Administration., eds. 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, ed. 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, 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.

P, Willis B., Schoenenberger M, and United States. National Aeronautics and Space Administration., eds. 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, and United States. National Aeronautics and Space Administration., eds. 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., ed. 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., ed. 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., ed. 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., ed. 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., ed. 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, and United States. National Aeronautics and Space Administration., eds. 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, and United States. National Aeronautics and Space Administration., eds. 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, and Langley Research Center, eds. 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, ed. Supersonic laminar flow control research: Final report, July 1994-June 1996. Tullahoma, TN: University of Tennessee, Space Institute, 1996.

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

G, Wiberg Clark, and United States. National Aeronautics and Space Administration., eds. 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, 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.

Center, Lewis Research, ed. 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, ed. 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, and United States. National Aeronautics and Space Administration., eds. 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, and United States. National Aeronautics and Space Administration., eds. 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.