A method is developed consistent with the assumptions of small perturbation theory which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The equivalence in subsonic and supersonic flow of the downwash at infinity corresponding to a given load distribution is proved.
The calculation of downwash behind supersonic wings with an application to triangular plan forms
1950-01-01
Sonstige
Keine Angabe
Englisch
Calculation of downwash behind supersonic wings with application to triangular plan forms
Engineering Index Backfile | 1948
|Calculation of downwash behind supersonic wings with application to triangular plan forms
Engineering Index Backfile | 1950
|Calculation of downwash behind wings of arbitrary plan form at supersonic speeds
Engineering Index Backfile | 1950
|