Unsteady aerodynamics of missiles. Part 3: Determination of the longitudinal stability of wings at high angles of attack in supersonic flight
Abstract
A theoretical method for the determination of unsteady aerodynamic coefficients associated with the longitudinal stability of slender wings in supersonic flight is presented. It is based on the indicial functional theory of Tobak. Extension to higher incidences is effected by combining the indicial functions with steady nonlinear coefficients derived from a semiempiricial procedure. The unsteady nonlinear aerodynamic coefficients are determined for delta wings with subsonic and supersonic leading edges, respectively.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- May 1980
- Bibcode:
- 1980STIN...8125129S
- Keywords:
-
- Angle Of Attack;
- Longitudinal Stability;
- Slender Wings;
- Supersonic Flight;
- Unsteady Aerodynamics;
- Delta Wings;
- Leading Edges;
- Nonlinear Equations;
- Semiempirical Equations;
- Subsonic Flow;
- Unsteady Flow;
- Launch Vehicles and Space Vehicles