Книги з теми "Laminar layer"

Rogers, David F. Laminar flow analysis. Cambridge: Cambridge University Press, 1992.

Joslin, Ronald D. Overview of laminar flow control. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

1940-, Rahman M., ed. Laminar and turbulent boundary layers. Southampton: Computational Mechanics Publication, 1997.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Distributed acoustic receptivity in laminar flow control configurations. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

Joslin, Ronald D. Active control of instabilities in laminar boundary-layer flow. Hampton, VA: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1994.

Theory of laminar film condensation. New York: Springer-Verlag, 1991.

United States. National Aeronautics and Space Administration., ed. Parametric study on laminar flow for finite wings at supersonic speeds. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Ya, Levchenko V., Polyakov N. F, and United States. National Aeronautics and Space Administration., eds. Laminar boundary layer with moderate turbulence of the incoming flow. Washington, DC: National Aeronautics and Space Administration, 1989.

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.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. A three-dimensional, compressible laminar boundary-layer method for general fuselages. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. A three-dimensional, compressible laminar boundary-layer method for general fuselages. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

1906-, Rosenhead Louis, ed. Laminar boundary layers: An account of the development, structure, and stability of laminar boundary layers in incompressible fluids, together with a description of the associated experimental techniques. New York: Dover Publications, 1988.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. A three-dimensional, compressible laminar boundary-layer method for general fuselages. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Center, Langley Research, ed. Instability of flow in a streamwise corner. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., ed. A three-dimensional, compressible laminar boundary-layer method for general fuselages. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Choudhari, Meelan. Boundary layer receptivity mechanisms relevant to laminar flow control. [Tucson, Ariz.]: University of Arizona, 1990.

Tokyo, Japan) International Workshop on "Prediction of Laminar-turbulent Transition in Boundary Layers" (2000. Prediction of laminar-turbulent transition in boundary layers. Tokyo: National Aerospace Laboratory, 2000.

J, Holmes Bruce, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Flight-measured laminar boundary-layer transition phenomena including stability theory analysis. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Goldstein, Marvin E. The effect of nonlinear critical layers on boundary layer transition. [Washington, D.C: National Aeronautics and Space Administration, 1995.

Lysenko, V. I. Stability characteristics of a supersonic boundary layer and their relation to the position of the laminar-turbulent transition point. Washington, D.C: National Aeronautics and Space Administration, 1987.

Drake, Aaron. Selected experiments in laminar flow: An annotated bibliography. [Washington, D.C.?]: National Aeronautics and Space Administration, 1992.

Ball, Norman George. Acoustic excitation of Tollmien-Schlichting waves in a laminar boundary layer. [Downsview, Ont.]: [Institute for Aerospace Studies], 1987.

Ball, Norman George. Acoustic excitation of Tollmien-Schlichting waves in a laminar boundary layer. [Downsview, Ont.]: Institute for Aerospace Studies, 1987.

Fujii, Tetsu. Theory of Laminar Film Condensation. New York, NY: Springer New York, 1991.

D, Crouch Jeffrey, and Langley Research Center, eds. Simulation of boundary-layer transition: Receptivity to spike stage. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

Moraes, Augusto C. M. Compressible laminar boundary layers for perfect and real gases in equilibrium at Mach numbers to 30. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

Arnal, D. Laminar-Turbulent Transition: IUTAM Symposium Toulouse/France September 11-15, 1989. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990.

Wierciński, Zygmunt. Przejście laminarno-turbulentne w warstwie przyściennej indukowane śladami spływowymi. Gdańsk: Wydawn. IMP PAN, 1999.

Wendt, Volker. Experimentelle Untersuchung der Instabilitat von ebenen und konischen laminaren Hyperschallgrenzschichten. Koln, Germany: DLR, 1993.

IUTAM Symposium on Laminar-Turbulent Transition (5th 1999 Sedona, Arizona). Laminar-turbulent transition: IUTAM Symposium, Sedona/USA, 1999. Berlin: Springer, 2000.

United States. National Aeronautics and Space Administration., ed. An approach to the constrained design of natural laminar flow airfoils: A thesis ... [Washington, D.C: National Aeronautics and Space Administration, 1995.

Institute for Computer Applications in Science and Engineering., ed. Modelling the transitional boundary layer. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, Institute for Computer Applications in Science and Engineering, 1990.

Marshall, Laurie A. Boundary-layer transition results from the F-16XL-2 supersonic laminar flow control experiment. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

Hugh L. Dryden Flight Research Center., ed. Boundary-layer transition results from the F-16XL-2 supersonic laminar flow control experiment. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

Hugh L. Dryden Flight Research Center., ed. Boundary-layer transition results from the F-16XL-2 supersonic laminar flow control experiment. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

Zang, Thomas A. Multiple paths to subharmonic laminar breakdown in a boundary layer. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1989.

Yousuff, Hussaini M., and Langley Research Center, eds. Multiple paths to subharmonic laminar breakdown in a boundary layer. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

Wang, B. Y. Laminar sidewall boundary layer in a dusty-gas shock tube. [Downsview, Ont.]: Institute for Aerospace Studies, 1986.

United States. National Aeronautics and Space Administration., ed. The response of a laminar boundary layer in supersonic flow to small amplitude progressive waves. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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

United States. National Aeronautics and Space Administration., ed. The role of nonlinear critical layers in boundary layer transition. [Washington, D.C: National Aeronautics and Space Administration, 1995.

V, Kozlov V., International Union of Theoretical and Applied Mechanics., and IUTAM Symposium on Laminar-Turbulent Transition (2nd : 1984 : Novosibirsk, R.S.F.S.R.), eds. Laminar-turbulent transition: Symposium, Novosibirsk, USSR, July 9-13, 1984. Berlin: Springer-Verlag, 1985.

Cebeci, Tuncer. Modeling and computation of boundary-layer flows: Laminar, turbulent, and transitional boundary layers in incompressible flows. Long Beach, Calif: Horizons Pub., 1999.

United States. National Aeronautics and Space Administration., ed. Generation and development of small-amplitude disturbances in a laminar boundary layer in the presence of an acoustic field. Washington D.C: National Aeronautics and Space Administration, 1985.

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

Harris, Charles D. The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil: Design overview. Hampton, Va: Langley Research Center, 1988.

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

D, Arnal, Michel Roger 1920-, International Union of Theoretical and Applied Mechanics., and IUTAM Symposium on Laminar-Turbulent Transition (3rd : 1989 : Toulouse, France), eds. Laminar-turbulent transition: IUTAM symposium, Toulouse, France, September 11-15, 1989. Berlin: Springer-Verlag, 1990.

Facility, Dryden Flight Research, ed. Preliminary in-flight boundary layer transition measurements on a 45-degree swept wing at Mach numbers between 0.9 and 1.8. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1988.

Facility, Dryden Flight Research, ed. Preliminary in-flight boundary layer transition measurements on a 45-degree swept wing at Mach numbers between 0.9 and 1.8. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1988.