A method is presented for the estimation of the profile drag coefficient of airfoils at subsonic Mach numbers below the drag rise values. The method is applicable to smooth airfoils, with fully turbulent boundary layers, at any Reynolds number. The method is simple to apply for rapid estimation purposes, and to incorporate into an aircraft performance computation procedure.
Airfoil Profile Drag
1975
38 pages
Report
Keine Angabe
Englisch
Theoretical calculation of airfoil profile drag
| Engineering Index Backfile | 1938
Airfoil profile drag increase due to acoustic excitation
| AIAA | 1989
Improving Airfoil Drag Prediction
| AIAA | 2016
Improving Airfoil Drag Prediction
| Online Contents | 2016
Improving Airfoil Drag Prediction
| AIAA | 2016