Low-Speed Static and Dynamic Force Tests of a Generic Supersonic Cruise Fighter Configuration
Low-Speed Static and Dynamic Force Tests of a Generic Supersonic Cruise Fighter Configuration
- Neue Suche nach: D. E. Hahne
- Neue Suche nach: D. E. Hahne
Static and dynamic force tests of a generic fighter configuration designed for sustained supersonic flight were conducted in the Langley 30- by 60-foot tunnel. The baseline configuration had a 65 deg arrow wing, twin wing mounted vertical tails and a canard. Results showed that control was available up to C sub L,max (maximum lift coefficient) from aerodynamic controls about all axes but control in the pitch and yaw axes decreased rapidly in the post-stall angle-of-attack region. The baseline configuration showed stable lateral-directional characteristics at low angles of attack but directional stability occurred near alpha = 25 deg as the wing shielded the vertical tails. The configuration showed positive effective dihedral throughout the test angle-of-attack range. Forced oscillation tests indicated that the baseline configuration had stable damping characteristics about the lateral-directional axes.
Dokumentinformationen
Low-Speed Static and Dynamic Force Tests of a Generic Supersonic Cruise Fighter Configuration
1989
35 pages
Report
Keine Angabe
Englisch
Aerodynamics , Test Facilities & Equipment , Aircraft control , Dynamic tests , Low speed stability , Static tests , Supersonic cruise aircraft research , Fighter aircraft , Wind tunnel tests , Aerodynamic configurations , Aircraft configurations , Directional control , Directional stability , Angle of attack , Damping , Oscillations , Pitch (Inclination) , Yaw