Książki na temat „Aerodynamic pressure”

Moshasrov, V. Luminescent pressure sensors in aerodynamic experiments. Zhukovsky, Russia : Central Aerohydrodynamic Institute (TsAGI): CWA 22 Corporation, 1998.

Nemec, Marian. Aerodynamic computations using the convective upstream split pressure scheme with local preconditioning. [Toronto]: Dept. of Aerospace Science and Engineering, University of Toronto, 1998.

Nemec, Marian. Aerodynamic computations using the convective upstream split pressure scheme with local preconditioning. Ottawa: National Library of Canada, 1998.

Schuster, D. M. Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2001.

Emre, Ilgin Hüseyin, red. Tall buildings: Structural systems and aerodynamic form. London: Routledge, Taylor & Francis Group, 2014.

Labrujere, Th E. Correction for wall interference in a solid-wall wind tunnel using sparse measured boundary conditions. Amsterdam: National Aerospace Laboratory, 1989.

Wing, David J. Afterbody/nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Martin, Colin A. Surface pressure measurements on the wing of a wind tunnel model during steady rotation. Melbourne, Australia: Aeronautical Research Laboratory, 1991.

Garry, Kevin P. A summary of the scale model wind tunnel measurements and full scale surface pressure tests on the Leyland T45 and DAF3300 vehicles used for the TRRL spray dispersion programme. Cranfield [U.K.]: College of Aeronautics, Cranfield Institute of Technology, 1987.

Guerrera, Michael H. Laser anemometry and pressure measurements in the endwall region of an annular turbine cascade utilizing a pressurized aerodynamic window. Monterey, Calif: Naval Postgraduate School, 1996.

K. B. M. Q. Zaman. Some observations on transitory stall in conical diffusers. Cleveland, Ohio: Lewis Research Center, 1989.

Moes, Timothy R. In-flight investigation of shuttle tile pressure orifice installations. Edwards, Calif: Ames Research Center, 1990.

Moes, Timothy R. In-flight investigation of shuttle tile pressure orifice installations. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Piziali, R. A. 2-D and 3-D oscillating wing aerodynamics for a range of angles of attack including stall. Moffett Field, Ca: Ames Research Center, 1994.

Applin, Zachary T. Pressure distributions from subsonic tests of a NACA 0012 semispan wing model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Applin, Zachary T. Pressure distributions from subsonic tests of a NACA 0012 semispan wing model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Hallissy, James B. Wind-tunnel investigation of aerodynamic characteristics and wing pressure distributions of an airplane with variable-sweep wings modified for laminar flow. Hampton, Va: Langley Research Center, 1989.

Jenkins, Renaldo. Aerodynamic performance and pressure distributions for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel. Hampton, Va: Langley Research Center, 1988.

Lee, Harvey Shui-Hong. Assessment of potential aerodynamic effects on personnel and equipment in proximity to high-speed train operations: Safety of high-speed ground transportation systems. Washington, D.C: U.S. Dept. of Transportation, Federal Railroad Administration, Office of Research and Development, 1999.

Siemers, Paul M. Pressure distributions obtained on a 0.10-scale model of the space shuttle orbiter's forebody in the Ames unitary plan wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

National Research Council (U.S.). Transportation Research Board, National Cooperative Highway Research Program, American Association of State Highway and Transportation Officials i United States. Federal Highway Administration, red. Fatigue loading and design methodology for high-mast lighting towers. Washington, D.C: Transportation Research Board, 2012.

Siemers, Paul M. Pressure distributions obtained on a 0.10-scale model of the space shuttle orbiter's forebody in the AEDC 16T propulsion wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

Building aerodynamics. London: Imperial College Press, 2001.

Kontos, K. B. Improved NASA-ANOPP noise prediction computer code for advanced subsonic propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1996.

Kontos, K. B. Improved NASA-ANOPP noise prediction computer code for advanced subsonic propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1996.

Kontos, K. B. Improved NASA-ANOPP noise prediction computer code for advanced subsonic propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1996.

Kontos, K. B. Improved NASA-ANOPP noise prediction computer code for advanced subsonic propulsion systems. [Washington, DC: National Aeronautics and Space Administration, 1996.

Jankovsky, Robert S. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Raman, Ganesh. Aeroacoustic characteristics of a rectangular multi-element supersonic jet mixer-ejector nozzle. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

Fisher, David F. F-18 High Alpha Research Vehicle surface pressures: Initial in-flight results and correlation with flow visualization and wind-tunnel data. Edwards, Calif: NASA Ames Resarch Center, Dryden Flight Research Facility, 1990.

Fisher, David F. F-18 High Alpha Research Vehicle surface pressures: Initial in-flight results and correlation with flow visualization and wind-tunnel data. Edwards, Calif: NASA Ames Resarch Center, Dryden Flight Research Facility, 1990.

Goodyer, M. J. Derivation of jack movement influence coefficients as a basis for selecting wall contours giving reduced levels of interference in flexible walled test sections. Hampton, VA: National Aeronautics and Space Administration, Langley Research Center, 1985.

Johnson, Steven. Pressure-sensing performance of upright cylinders in a Mach-10 boundary layer. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1994.

Johnson, Steven A. Pressure-sensing performance of upright cylinders in a Mach-10 boundary layer. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1994.

Johnson, Steven. Pressure-sensing performance of upright cylinders in a Mach-10 boundary layer. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1994.

Burley, James R. Experimental and numerical results for a generic axisymmetric single-engine afterbody with horizontal and vertical tails at transonic speeds. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

Burley, James R. Experimental and numerical results for a generic axisymmetric single-engine afterbody with horizontal and vertical tails at transonic speeds. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

K, Notestine Kristopher, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. Aerodynamic pressure and heating-rate distributions in tile gaps around chine regions with pressure gradients at a Mach number of 6.6. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

H, Ricketts Rodney, Hess R. W i Langley Research Center, red. Recent transonic unsteady pressure measurements at the NASA Langley Research Center. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

E, Mineck Raymond, i United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., red. Aerodynamic characteristics and pressure distributions for an executive-jet baseline airfoil section. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Center, Ames Research, red. Improved two-equation k - [omega] turbulence models for aerodynamic flows. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.

Improved two-equation k - [omega] turbulence models for aerodynamic flows. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.

Improved two-equation k - [omega] turbulence models for aerodynamic flows. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.

Center, Ames Research, red. Improved two-equation k - [omega] turbulence models for aerodynamic flows. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.

United States. National Aeronautics and Space Administration., red. IPAC--Inlet Performance Analysis Code. [Washington, DC: National Aeronautics and Space Administration, 1997.

IPAC--Inlet Performance Analysis Code. [Washington, DC: National Aeronautics and Space Administration, 1997.

United States. National Aeronautics and Space Administration., red. IPAC--Inlet Performance Analysis Code. [Washington, DC: National Aeronautics and Space Administration, 1997.

United States. National Aeronautics and Space Administration., red. IPAC--Inlet Performance Analysis Code. [Washington, DC: National Aeronautics and Space Administration, 1997.

S, Hultberg Randy, Martin Colin A i United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., red. Measurements of pressures on the tail and aft fuselage of an airplane model during rotary motions at spin attitudes. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989.

Laser Anemometry and Pressure Measurements in the Endwall Region of an Annular Turbine Cascade Utilizing a Pressurized Aerodynamic Window. Storming Media, 1996.