Numerical studies of unsteady transonic flow over an oscillating airfoil
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Numerical studies of unsteady transonic flow over an oscillating airfoil

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Published by National Aeronautics and Space Administration, Ames Research Center in Moffett Field, Calif .
Written in English


  • Navier-Stokes equations -- Numerical solutions

Book details:

Edition Notes

StatementW.J. Chyu and S.S. Davis
SeriesNASA technical memorandum -- 86011
ContributionsDavis, S. S, Ames Research Center
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL14926545M

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To check out the unsteady flow simulation's capability of presenting numerical methods, an unsteady transonic flow around an NACA airfoil was simulated at . The analysis of flow around advanced turboprop airfoil sections requires methods capable of modeling unsteady, transonic flow. As the number of blades Increase, the cascade effects are expected to become more signiflcant. date, most of the flow codes that model unsteady, transonic cascades are line- arized potential solvers. Transonic Flow Past Oscillating Airfoils Article (PDF Available) in Annual Review of Fluid Mechanics 12(1) November with Reads How we measure 'reads'. The paper focus on exclusive review in the field of ransonic flow T over an airfoil. Various research and analysis has been done for the improvement and development of Airfoil in transonic regimes by means of Computational Fluid Dynamics (CFD), Direct Numerical Simulation (DNS) in form of analytical model and variousFile Size: KB.

model transonic flow over three airfoil sections. The method uses a two-dimensional, implicit, con- servative finite difference scheme for solving the compressible Navier-Stokes equations. Results are presented as prescribed for the Viscous Transonic Airfoil Workshop to held at the AIAA 25th Aerospace Sciences Size: KB. A numerical investigation of unsteady transitional flow over an oscillating NACA airfoil at a Reynolds number of 44, and reduced frequency of is carried out and the results are compared with experimental by: 3. - Variable-domain variational finite element solution of inverse problem of 2-D unsteady transonic flow around oscillating airfoils. Author links open overlay panel Author: Jia-Hong Guo, Gao-Lian Liu. As experimental and numerical time-resolved shadowgraphs show, such waves initiate near the sharp trailing edge of a supercritical airfoil and in the wake, propagate upstream in the subsonic region of the flow, and strengthen before becoming apparently weaker and almost disappear near the leading by: 1.

  Ideally I would want to consider the motion of the airfoil over the duration of a single time period, and calculate the Lift and Pitch Moment Coefficient of the Airfoil. method based on harmonic balance, as opposed to a time-marching unsteady flow solver. Since the airfoil motion is periodic (and it seems that it's already given as a.   The present paper carries out, for the first time, a detailed theoretical investigation on the inverse problem in unsteady aerodynamics. Special attention is paid to finding proper ways of problem-posing and mathematical formulation. To demonstrate the basic idea, only an inverse problem of typeI A of unsteady transonic flow with shocks around oscillating airfoils is studied Author: G. L. Liu, J. H. Guo. An experimental and computational investigation of the steady and unsteady transonic flowfields about a thick airfoil is described. An operational computer code for solving the two-dimensional, compressible Navier-Stokes equations for flow over airfoils was modified to include solid-wall, slip-flow boundary conditions toCited by:   Dimitrov, Diliana () Unsteady aerodynamics of wings with an oscillating flap in transonic flow. 8th PEGASUS-AIAA Student Conference, , Poitiers, Frankreich.. Dieses Archiv kann nicht den gesamten Text zur Verfügung by: 2.