Prediction of Subsonic Separation Bubbles on Airfoils by Viscous-Inviscid Interaction,
Abstract
An iterative viscous-inviscid interaction calculation procedure is used to predict leading edge and midchord separation bubbles on airfoils in steady subsonic flow. The procedure utilizes an inverse finite-difference boundary layer calculation scheme to predict the viscous flow and a direct Hilbert integral formulation for the inviscid flow. Three models for laminar-turbulent transition are discussed. Predictions are compared with experimental measurements for several transitional separation bubble flows at angles of attack up through 7 deg. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1981
- Accession Number
- ADP001944
Entities
People
- O. K. Kwon
- R. H. Pletcher
Organizations
- General Motors