Abstract
It is not necessary to use time-consuming lifting surface theories for the purpose of calculating global forces and moments during wake vortex encounters. This paper presents computational methods that are currently used to quickly and accurately predict these rolling moments of an aircraft encountering a wake vortex. Appropriate modifications to strip theory are developed that account for the effects of finite wingspan. The paper shows that, in the case of an elliptic wing, the aspect ratio correction to the lift curve slope should be based on the semispan and a recipricol theorem is used to relate the rolling moment on a wing in a downwash field to that on a wing in steady rolling motion. The paper also presents calculations for a wing encountering a vortex with a Betz velocity distribution.
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