FLOW OVER AIRFOILS IN THE TRANSONIC REGIME-PREDICTION OF BUFFET ONSET.
Abstract
The report is concerned with the calculations of the viscous supercritical flow over planar airfoils, and in particular with the prediction of buffet onset using as a criterion the pressure divergence at the trailing edge. To determine the above flow an iterative procedure is considered in which the initial approximation is obtained by quasi-decoupling the boundary layer flow from the outer inviscid flow. The steady inviscid flow is then calculated by an unsteady finite difference method, in which the desired steady flow is obtained as the asymptotic flow at large times. The inviscid procedure is then applied to two examples with satisfactory results. For the treatment of the boundary layer, the initial laminar portion, and the transition zone are calculated in a conventional way, and an integral procedure based upon the continuity and streamwise momentum equations is suggested for the turbulent portion, containing the shock-induced separation, and for the wake, in which specific empirical input is required. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1970
- Accession Number
- AD0709377
Entities
People
- Hideo Yoshihara
- Richard Magnus
Organizations
- General Dynamics