Far-field turbulent vortex-wake/exhaust plume interaction for subsonic and HSCT airplanes
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Far-field turbulent vortex-wake/exhaust plume interaction for subsonic and HSCT airplanes 27th AIAA Fluid Dynamics Conference, June 17-20, 1996/New Orleans, LA by

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Published by American Institute of Aeronautics and Astronautics, [National Aeronautics and Space Administration, National Technical Information Service, distributor in Washington, DC, Springfield, Va .
Written in English

Subjects:

  • Turbulent flow.,
  • Vortices.,
  • Navier-Stokes equation.,
  • Supersonic transports.,
  • Finite difference theory.,
  • Shear stress.,
  • Turbulent wakes.

Book details:

Edition Notes

Other titlesFar field turbulent vortex wake, exhaust plume interaction for subsonic and HSCT airplanes.
StatementOsama A. Kandil, Ihab Adam and Tin-Chee Wong.
Series[NASA contractor report] -- NASA-CR-203260.
ContributionsAdam, Ihab., Wong, Tin Chee., American Institute of Aeronautics and Astronautics., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL18122329M

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Get this from a library! Far-field turbulent vortex-wake/exhaust plume interaction for subsonic and HSCT airplanes: 27th AIAA Fluid Dynamics Conference, June , /New Orleans, LA. [Osama A Kandil; Ihab Adam; Tin-Chee Wong; American Institute of Aeronautics and Astronautics.; United States. National Aeronautics and Space Administration.]. Computational study of the far-field turbulent vortex-wake/exhaust plume interaction for subsonic and high speed civil transport (HSCT) airplanes is carried out. The Reynolds-averaged Navier-Stokes (NS) equations are solved using the implicit, upwind, Roe-flux-differencing, finite-volume by: 2.   Vortex interactions and decay in aircraft wakes. Far-field turbulent vortex-wake/exhaust plume interaction for subsonic and HSCT airplanes. Osama Kandil, Vortex interactions in multiple vortex wakes behind aircraft. D. CIFFONE; 14th Cited by: Far-field turbulent vortex-wake/exhaust plume interaction for subsonic and HSCT airplanes. Osama Kandil, Cited by:

For aircraft smaller than the semi-span of the wake-generator, a penetration of one vortex probably covers the most hazardous region in the wake. If, however, the penetrating aircraft is on the order of the same size as the wake-generating airplane, the most hazardous location in the wake is theoretically not at the center of a by: Aircraft fuel consumption has increased by about 75% during the past 20 years and is projected to increase by to % over the next 30 years. At the present time, approximately 3% of the worldwide usage of fossil fuels is by aircraft. Ninety-nine percent of this aircraft fuel is burned by subsonic aircraft, of which a large proportion. Journal of Sound and Vibration () (1), FLOW FIELD AND NEAR AND FAR SOUND FIELD OF A SUBSONIC JET K. B. M. Q. ZAMAN~ NASA Langley Research Center, Hampton, Virginia , U.S.A. (Received 12 June , and in revised form 22 November ) Flow and sound field data are presented for a cm diameter air jet at a Mach number of and a Reynolds number of 3 x Cited by:   Compressible large-eddy simulations are carried out to study the aero-optical distortions caused by Mach flat-plate turbulent boundary layers at Reynolds numbers of, and , based on momentum fluctuations of refractive index are calculated from the density field, and wavefront distortions of an optical beam traversing the boundary layer are computed based on Cited by:

In this paper, computational investigations of the far-field turbulent vortex-wake/exhaust jet plume interaction for a Boeing tip vortex and a single engine, and a HSCT vortex-wake and twin engines are carried out. The Boeing is in a holding condition and the HSCT is in a cruise condition. An overlapping zonal method is used to carry out. Interaction of Wing Vortices and Plumes in Supersonic Flight. Authors; Authors and affiliations D.C. (). Turbulent aspects of plume aerodynamic interactions, AIAA Paper 95– -Lye, R., Martinez-Sanchez, M., Brown, R., and Kolb, C. (). Plume and wake dynamics, mixing and chemistry behind an HSCT aircraft, AIAA paper 91– Cited by: 3. Computational modeling and studies of the near-field wake-vortex turbulent flows, far-field turbulent wake-vortex/exhaust-plume interaction for subsonic and High Speed Civil Transport (HSCT) airplane, and wake-vortex/exhaust-plume interaction with the ground are carried out. The three-dimensional, compressible Reynolds-Averaged Navier-Author: Ihab Gaber Adam. Box and Gaussian plume models of the exhaust composition evolution of subsonic transport aircraft in- and out of the ßight corridor I. L. Karol, Y. E. Ozolin, E. V. Rozanov Main Geophysical Observatory, 7 Karbyshev st., St. Petersburg, , Russia Received: 26 September /Revised: 19 June /Accepted: 3 July Abstract.