Calculation of Transonic Flows Past Thin Airfoils by an Integral Method
Abstract
A method of calculating two dimensional compressible flows past thin airfoils is presented with particular reference to the transonic speed range. The method is based on the integral form of the equation of continuity and on the intrinsic form, in terms of the streamline curvature, of the irrotationality condition. The application to the transonic range conforms with, and is carried out within the framework of, the transonic similarity theory. The results include velocity distributions for various symmetric sections in the continuous potential flow speed range and for the symmetric biconvex airfoil at zero angle of attack through the transonic speed range and the associated variation of terminal and head-shock location and pressure drag with Mach umber. Comparisons with other theories and with available experimental data indicate at least qualitatively good agreement. The location and the movement of the terminal shock in the lower transonic speed range are discussed, as well as the limiting-line phenomenon.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1950
- Accession Number
- ADA380872
Entities
People
- William Perl
Organizations
- National Aeronautics and Space Administration