› › A Comparative Study Of Two Computational Methods For Calculating Unsteady Transonic Flows About Oscillating Airfoils

A Comparative Study of Two Computational Methods for Calculating Unsteady Transonic Flows About Oscillating Airfoils

Author : Donald P. Rizzetta

Publisher :

Page : 43 pages

File Size : 23,12 MB

Release : 1977

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ISBN :

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Book Description

This report provides a direct comparison of the calculations for the flow field about an oscillating airfoil in a transonic freestream predicted by two computational methods; namely, harmonic analysis and time integration. Details of the two methods are summarized and results for NACA64A010 airfoil oscillating in pitch are considered. Comparisons of the unsteady pressure distribution and resultant lift are presented for several values of free-stream Mach number, angle of attack, and reduced frequency of oscillation. (Author).





Computational Research on Inviscid, Unsteady, Transonic Flow Over Airfoils

Author : R. J. Magnus

Publisher :

Page : 76 pages

File Size : 40,9 MB

Release : 1977

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Book Description

The inviscid transonic flow over an NACA 64A410 airfoil oscillating in pitch in a Mach 0.72 stream was calculated with a program based on the unsteady Euler equations. The airfoil oscillates about a mid-chord axis with attitude alpha = 1 deg + or - 1 deg at reduced frequency k = omega C/U(infinty) = 0.2. The effects of two approximations made in the analysis, handling of boundary conditions at the airfoil surface and at the perimeter of the computation field, have been studied. (Author).





Calculation of Boundary Layers of Oscillating Airfoils

Author : National Aeronautics and Space Administration (NASA)

Publisher : Createspace Independent Publishing Platform

Page : 30 pages

File Size : 34,54 MB

Release : 2018-07-25

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ISBN : 9781724254054

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Book Description

A two-point finite difference unsteady laminar and turbulent boundary layer computational method was used to investigate the properties of the flow around an airfoil (NACA 0012) oscillating through angles of attack up to 18 degrees, for reduced frequencies of 0.01 and 0.20. The unsteady potential flow was determined using the unsteady potential flow method of Geissler. The influence of transition location on stal behavior was investigated, using both experimentally determined transition information, and transition located at the pressure peak; the results show the need for viscous-inviscid interaction in future computation of such flows. Cebeci, T. and Carr, L. W. Ames Research Center NASA-TM-85943, A-9599, NAS 1.15:85943, USAAVSCOM-TR-84-A-1 RTOP 505-31-32











Monthly Catalog of United States Government Publications

Author : United States. Superintendent of Documents

Publisher :

Page : pages

File Size : 39,81 MB

Release : 1985

Category : Government publications

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Book Description

February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index