Aerodynamic Loads on Advanced Fighter Aircraft
Aerodynamic Loads on Advanced Fighter Aircraft
- New search for: J. P. Giesing
- New search for: T. P. Kalman
- New search for: J. P. Giesing
- New search for: T. P. Kalman
A study was conducted to obtain the effects of various configuration idealizations on the subsonic airloads of a twin vertical tail fighter aircraft. Particular attention has been given to the empennage since this is usually the critical region for flutter. The configurations considered are: (1) the stabilator alone (with a symmetry plane at its root), (2) the stabilator and fins alone, (3) the stabilator, fin and several fuselage lengths, (4) the entire aircraft and (5) a flat plate representation of the fuselage. Three reduced frequencies were considered (0.0, 0.5, 1.0) and two Mach numbers (0.0 and 0.9). The results are analyzed and the implications for flutter discussed.
Document information
Aerodynamic Loads on Advanced Fighter Aircraft
1973
96 pages
Report
No indication
English
Aircraft , Aerodynamics , Jet fighters , Aerodynamic loading , Flutter , Tails(Aircraft) , Aerodynamic control surfaces , Lifting surfaces , Aerodynamic configurations , urations , Fins , Roll , Fuselages , Length , Stabilization systems , Vertical orientation , Theory , Subsonic characteristics , External stores , Aspect ratio , Wing body configurations , Subsonic flow , Interference , Mach number , Gusts , Computer programs , Oscillation , Airplane models , Turbulent flow , Flat plate models , Mathematical models , Approximation(Mathematics) , Stabilators , Twin tailed aircraft , Lifting surface theory , Vertical tails , Finite element analysis , Doublet lattice method
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