Scientific and Technical Aerospace Reports, 29. sējums,1-3. izdevumsScientific and Technical Information Office, National Aeronautics and Space Administration, 1991 |
No grāmatas satura
1.–5. rezultāts no 99.
. lappuse
... boundary layers ; hydrodynamics ; fluidics ; mass transfer and ablation cooling . For related information see also 02 Aerodynamics and 77 Thermodynamics and Statistical Physics . 35 INSTRUMENTATION AND PHOTOGRAPHY 44 Includes remote ...
... boundary layers ; hydrodynamics ; fluidics ; mass transfer and ablation cooling . For related information see also 02 Aerodynamics and 77 Thermodynamics and Statistical Physics . 35 INSTRUMENTATION AND PHOTOGRAPHY 44 Includes remote ...
1. lappuse
... boundary - layer displacement are available . A particular advantage of the code , in addition to its speed , is that it can often be made to complete calculation for near - equilibrium situations where other reacting flow codes ...
... boundary - layer displacement are available . A particular advantage of the code , in addition to its speed , is that it can often be made to complete calculation for near - equilibrium situations where other reacting flow codes ...
4. lappuse
... boundary layer is investigated . The instability has a wavelength comparable with the boundary layer thickness so that a quasi - parallel approach to the instability problem can be justified . The generalization of the Rayleigh equation ...
... boundary layer is investigated . The instability has a wavelength comparable with the boundary layer thickness so that a quasi - parallel approach to the instability problem can be justified . The generalization of the Rayleigh equation ...
5. lappuse
... boundary layer method for three - dimensional compressible laminar or turbulent flow is proposed . The resulting computer program is valid only for simple wings . The panel model may also contain body - like components , however . The ...
... boundary layer method for three - dimensional compressible laminar or turbulent flow is proposed . The resulting computer program is valid only for simple wings . The panel model may also contain body - like components , however . The ...
13. lappuse
... boundary layer at the trailing edge and subtracting the friction drag obtained from integration of surface friction along the chord . Herein , the pressure drag is obtained by integrating the streamwise components of surface pressure ...
... boundary layer at the trailing edge and subtracting the friction drag obtained from integration of surface friction along the chord . Herein , the pressure drag is obtained by integrating the streamwise components of surface pressure ...
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Citi izdevumi - Skatīt visu
Bieži izmantoti vārdi un frāzes
A17 CSCL Abstr aerodynamic aeroelastic Aeronautics and Space Aerospace AGARD AGARD/Scientific Publications Executive Air Traffic Handling airfoil algorithm alloys Ames Research Center analysis Atmospheric Author cirrus cirrus clouds cloud composite Computational Fluid Dynamics Contract Copyright Avail Dept described developed effects electron energy Engineering ENGLISH summary equations evaluation experimental field flow function grid Guidance of Aircraft HC/MF A03 CSCL heat Includes Inst interaction investigated Langley Research Center laser lidar magnetic measurements mechanical Meteorological Satellite Center method Microfilms Order NASA National Aeronautics National Lab Nationals requests available Navier-Stokes equations Netherlands Non-NATO Nationals requests nonlinear NTIS HC/MF A03 numerical observed operating optical parameters performance Ph.D plasma Plasma Physics Prediction presented primary document problems Propulsion Report Sandia National Labs simulation solar Space Administration spacecraft superconducting surface techniques Technology temperature thermal Thesis turbulence Univ Universiteit Twente velocity wave wind windshear
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