Calculation of unsteady transonic flows with shocks by field panel methods

Title

Calculation of unsteady transonic flows with shocks by field panel methods

 Author

Hounjet, M.H.L.

Institution

National Aerospace Laboratory NLR

 Date

1981-07-01

 Abstract

A field panel method, FTRAN2, is presented for the calculation of twodimensional inviscid transonic flow including shock waves about an oscillating wing. For a NACA 6UAOO6 and a NACA 6UA010 airfoil results are presented and compared with results of finite difference methods. The good agreement obtained and the lower computer cost shows the feasibility of the method. Also a modification of FTRAN2 is proposed to achieve further reduction of the computational effort. Results are given for an oscillating flat plate as a first test case.

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 Publisher

Nationaal Lucht- en Ruimtevaartlaboratorium

 Access restriction

Campus only

 Source

NLR MP 81041 U

 Part of collection

Aerospace Engineering Reports

 Document type

report

 Rights

(c)1981 National Aerospace Laboratory NLR
Files
PDF 81041.pdf 3.64 MB
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