Method developed for estimating, for airfoil section at arbitrary angle of attack, drag divergence Mach number, and free stream Mach number at which abrupt supercritical drag rise starts.
Study of flow changes associated with airfoil section drag rise at supercritical speeds
Nat Advisory Committee Aeronautics -- Tech Note
1949
31 pages
Charts
Report
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Engineering Index Backfile | 1952
|Airfoil Section Drag Reduction at Transonic Speeds by Numerical Optimization
SAE Technical Papers | 1976
|