The maximum obtainable airfoil profile thickness for the simplest supercritical roof-top pressure distributions was determined using systematic exemplary calculations with the profile design method based on the integral method. These thick profiles with shock-free supercritical flow are especially suitable for application to transport aircraft. The maximum thickness limits found are in good agreement with empirical estimations.
The Thickness Distribution of Profiles for Shock-Free Flow Without Lift Untersuchungen ueber die Dickenverteilung von Profilen bei Stossfreier Umstroemung Ohne Auftrieb
1977
26 pages
Report
No indication
English
Engineering Index Backfile | 1935
|Engineering Index Backfile | 1934
|Experimentelle Untersuchungen der Umstroemung eines Laminarfluegels mit Absaugung
British Library Conference Proceedings | 1992
|