An automated transonic design code has been developed which modifies an initial airfoil or wing in order to generate a specified pressure distribution. The design method uses an iterative approach that alternates between a potential-flow analysis and a design algorithm that relates changes in surface pressure to changes in geometry. The analysis code solves an extended small-disturbance potential-flow equation and can model a fuselage, pylons, nacelles, and a winglet in addition to the wing. A two-dimensional option is available for airfoil analysis and design. Several two- and three-dimensional test cases illustrate the capabilities of the design code.
A transonic-small-disturbance wing design methodology
1988-03-01
Report
No indication
English
Transonic-Small-Disturbance Wing Design Methodology
NTIS | 1988
|Coupling of a Wing Inverse Design Code to a Transonic Small Disturbance Flow Solver
British Library Conference Proceedings | 2001
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