Książki na temat „Edge layer”

J, Shamroth S., Langley Research Center i Scientific Research Associates, red. On the application of a hairpin vortex model of wall turbulence to trailing edge noise prediction. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

Lin, N. Receptivity of the boundary layer on a semi-infinite flat plate with an elliptic leading edge. Tempe, Ariz: Arizona State University, Department of Mechanical and Aerospace Engineering, 1989.

Mueller, Thomas J. The structure of separated flow regions occurring near the leading edge of airfoils - including transition. Notre Dame, Ind: Dept. of Aerospace and Mechanical Engineering, University of Notre Dame, 1985.

Hulshoff, Steven John. The response of the unsteady laminar boundary layer to leading edge acoustic diffraction. [Downsview, Ont.]: Department of Aerospace Science and Engineering, 1989.

Institute for Computer Applications in Science and Engineering., red. Görtler vortices in growing boundary layers: The leading edge receptivity problem, linear growth and the nonlinear breakdown stage. Hampton, Va: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1989.

Institute for Computer Applications in Science and Engineering., red. Görtler vortices in growing boundary layers: The leading edge receptivity problem, linear growth and the nonlinear breakdown stage. Hampton, Va: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1989.

United States. National Aeronautics and Space Administration., red. Analysis of the leading edge effects on the boundary layer transition: Technical report, March 1, 1984 - August 31, 1990. [Washington, DC: National Aeronautics and Space Administration, 1990.

Center, Ames Research, i United States. National Aeronautics and Space Administration., red. 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.

J, Ghosn Louis, Miller Robert A. 1947- i Lewis Research Center, red. Effect of layer-graded bond coats on edge stress concentration and oxidation behavior of thermal barrier coatings. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

J, Ghosn Louis, Miller Robert A. 1947- i Lewis Research Center, red. Effect of layer-graded bond coats on edge stress concentration and oxidation behavior of thermal barrier coatings. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

J, Ghosn Louis, Miller Robert A. 1947- i Lewis Research Center, red. Effect of layer-graded bond coats on edge stress concentration and oxidation behavior of thermal barrier coatings. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

Mueller, T. J. The structure of separated flow regions occurring near the leading edge of airfoils, including transition: Semi-annual status report, February 1986-July 1986. [Washington, D.C: National Aeronautics and Space Administration, 1986.

United States. National Aeronautics and Space Administration., red. The structure of separated flow regions occurring near the leading edge of airfoils, including transition: Semi-annual status report, November 1984 - April 1985. Notre Dame, Ind: Dept. of Aerospace and Mechanical Engineering, University of Notre Dame, 1985.

Nicolas, Spitz, i NASA Glenn Research Center, red. Predicting modes of the unsteady vorticity field near the trailing edge of a blade. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2003.

Nicolas, Spitz, i NASA Glenn Research Center, red. Predicting modes of the unsteady vorticity field near the trailing edge of a blade. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2003.

A, Campbell Bryan, i Langley Research Center, red. Subsonic investigation of a leading-edge boundary layer cont[r]ol suction system on a high-speed civil transport configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

A, Campbell Bryan, i Langley Research Center, red. Subsonic investigation of a leading-edge boundary layer cont[r]ol suction system on a high-speed civil transport configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Lessard, Victor R. Low speed analysis of mission adaptive flaps on a high speed civil transport configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Lessard, Victor R. Low speed analysis of mission adaptive flaps on a high speed civil transport configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Center, Langley Research, red. Supersonic leading edge receptivity. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate). Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

V, Ustinov M., i Langley Research Center, red. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Center, Ames Research, red. Rotor vortex filaments: Living on the slipstream's edge. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1997.

American Bar Association. Section of State and Local Government Law, red. At the cutting edge 2009: Land use law from The urban lawyer. Chicago, Ill: American Bar Association, Section of State and Local Government Law, 2010.

Merriam, Dwight H. At the cutting edge 2009: Land use law from The urban lawyer. Redaktor American Bar Association. Section of State and Local Government Law. Chicago, Ill: American Bar Association, Section of State and Local Government Law, 2010.

American Bar Association. Section of State and Local Government Law, red. At the cutting edge, 2010: Land use law from The Urban Lawyer. Chicago, Ill: American Bar Association, Section of State and Local Government Law, 2011.

United States. National Aeronautics and Space Administration., red. Numerical studies of boundary-layer receptivity: A progress report. [Washington, DC: National Aeronautics and Space Administration, 1995.

Sampson, C. Garth. Nightfire Island: Later Holocene lakemarsh adaptation on the western edge of the Great Basin. Eugene, Or: Dept. of Anthropology, University of Oregon, 1985.

Sampson, C. Garth. Nightfire Island: Later Holocene lakemarsh adaptation on the western edge of the Great Basin. Eugene, Or: Dept. of Anthropology, University of Oregon, 1985.

Melvin, Aikens C., red. Nightfire Island: Later Holocene lakemarsh adaptation on the western edge of the Great Basin. Eugene, Or: Dept. of Anthropology, University of Oregon, 1985.

Witzigmann, Bernd. Design and implementation of a three-dimensional edge emitting quantum well laser simulator / Bernd Witzigmann. Konstanz: Hartung-Gorre, 2000.

R, Sarma Garimella, Mangalam Siva M i United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., red. Flight demonstration of a shock location sensor using constant voltage hot-film anemometry. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

Mario, Vargas, i United States. National Aeronautics and Space Administration., red. A laser-based ice shape profilometer for use in icing wind tunnels. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

Mario, Vargas Meza, i United States. National Aeronautics and Space Administration., red. A laser-based ice shape profilometer for use in icing wind tunnels. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

Mario, Vargas, i United States. National Aeronautics and Space Administration., red. A laser-based ice shape profilometer for use in icing wind tunnels. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

Mario, Vargas, i United States. National Aeronautics and Space Administration., red. A laser-based ice shape profilometer for use in icing wind tunnels. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

Hall, Philip. Gortler vortices in growing boundary layers: the leading edge receptivity problem, linear growth and the nonlinear breakdown stage. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1989.

D, Saunders J., i United States. National Aeronautics and Space Administration., red. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., i United States. National Aeronautics and Space Administration., red. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., i United States. National Aeronautics and Space Administration., red. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., i United States. National Aeronautics and Space Administration., red. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., red. Control of unsteady separated flow associated with the dynamic stall of airfoils: Final report, 95-09. San Jose, CA: MCAT Institute, 1995.

United States. National Aeronautics and Space Administration., red. Control of unsteady separated flow associated with the dynamic stall of airfoils. San Jose, CA: MCAT Institute, 1994.

E, Mineck Raymond, i Langley Research Center, red. Assessment of dual-point drag reduction for an executive-jet modified airfoil section. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Allison, Dennis O. Assessment of dual-point drag reduction for an executive-jet modified airfoil section. Hampton, Virginia: National Aeronautics and Space Administration, Langly Research Center, 1996.

E, Mineck Raymond, i Langley Research Center, red. Assessment of dual-point drag reduction for an executive-jet modified airfoil section. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., red. Finite-element analysis of a Mach-8 flight test article using nonlinear contact elements. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.