A small-disturbance theory is developed for predicting the aerodynamics of an airplane in sideslip. Second-order terms involving the interaction between sideslip angle and angle of attack, sideslip angle and wing camber, etc., are retained. It is found that the second-order terms can produce the dominant sideslip effects when the dihedral of the lifting surfaces is small. Numerical implementation of the theory requires a solution procedure capable of producing accurate velocity gradients in the first-order solution.
Sideslip of wing-body combinations
1972-10-01
Report
No indication
English
Rolling moment due to sideslip for swept wing
Engineering Index Backfile | 1949
|Influence of sideslip on double delta wing aerodynamics
AIAA | 1995
|Influence of Sideslip on Double Delta Wing Aerodynamics
Online Contents | 1995
|