The variation of pressure distribution is calculated for a two-dimensional supersonic airfoil either experiencing a sudden angle-of-attack change or entering a sharp-edge gust. From these pressure distributions the indicial lift functions applicable to unsteady lift problems are determined for two cases. Results are presented which permit the determination of maximum increment in lift coefficient attained by an unrestrained airfoil during its flight through a gust. As an application of these results, the minimum altitude for safe flight through a specific gust is calculated for a particular supersonic wing of given strength and wing loading.
Two-dimensional unsteady lift problems in supersonic flight
1949-01-01
Sonstige
Keine Angabe
Englisch
Three-dimensional unsteady lift problems in high-speed flight -- Triangular wing
Engineering Index Backfile | 1951
|Three-dimensional, unsteady-lift problems in high-speed flight -- Basic concepts
Engineering Index Backfile | 1950
|