Unsteady Airload Computations for Airfoils Oscillating in Attached and Separated Compressible Flow,
Abstract
Recent developments in coupled inviscid flow-boundary layer computations are discussed for airfoils in unsteady motion in attached and separated subsonic and transonic flow. The applicability of quasi-simultaneous strong interaction coupling procedures for transonic small perturbation theory and boundary layer integral methods is illustrated for oscillating airfoils with shock-induced separation. The relevance of the predicted airfoils for aeroelastic applications is illustrated using the analysis of an aeroelastic instability of a supercritical wing wind-tunnel model.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1985
- Accession Number
- ADP005018
Entities
People
- R. Houwink
Organizations
- National Aerospace Laboratory