Aeroelastic Analysis of Aircraft: Wing and Wing/Fuselage Configurations
Aeroelastic Analysis of Aircraft: Wing and Wing/Fuselage Configurations
- Neue Suche nach: Chen, H. H.
- Neue Suche nach: Chang, K. C.
- Neue Suche nach: Tzong, T.
- Neue Suche nach: Cebeci, T.
- Neue Suche nach: Chen, H. H.
- Neue Suche nach: Chang, K. C.
- Neue Suche nach: Tzong, T.
- Neue Suche nach: Cebeci, T.
A previously developed interface method for coupling aerodynamics and structures is used to evaluate the aeroelastic effects for an advanced transport wing at cruise and under-cruise conditions. The calculated results are compared with wind tunnel test data. The capability of the interface method is also investigated for an MD-90 wing/fuselage configuration. In addition, an aircraft trim analysis is described and applied to wing configurations. The accuracy of turbulence models based on the algebraic eddy viscosity formulation of Cebeci and Smith is studied for airfoil flows at low Mach numbers by using methods based on the solutions of the boundary-layer and Navier-Stokes equations.
Dokumentinformationen
Aeroelastic Analysis of Aircraft: Wing and Wing/Fuselage Configurations
1997-05-01
Report
Keine Angabe
Englisch
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