ESDU 10022 provides a means of predicting the trailing-vortex drag coefficient@ CDV@ of wings with or without camber and twist@ at a given value of CL in shock-free attached flow. Equations and graphs are provided for predicting the trailing-vortex drag coefficient of wings with quarter-chord sweep angles not exceeding 45??aspect ratios not exceeding 12@ and linear or simple non-linear spanwise twist variations of up to 10??ash-in or wash-out. ESDU 10022 is applicable to both straight-tapered and cranked wing planforms where the section geometry@ including camber@ either remains unaltered or varies with spanwise location. The method is based on a theoretical analysis using inviscid spanwise loading distributions generated by the Multhopp-Richardson lifting-surface method@ obtained from ESDU 95010. As a result the trailing-vortex drag coefficient obtained by the method is the inviscid component of the total wing drag coefficient in shock-free attached flow. The viscous drag coefficient@ which is predicted using ESDU 07002@ is the component of the total drag coefficient arising from all viscous effects. Therefore@ ESDU 07002 can be used in conjunction with the method of ESDU 10022 to predict the total wing drag coefficient at a given value of CL in a shock-free flow. Trailing-vortex drag coefficient data obtained using the Full Potential (FP) program and a post processing program@ both contained in ESDU 06016@ are compared with data obtained using the method of ESDU 10022. There is good agreement between the two sets of data.
ESDU 10022-2011 history
2011ESDU 10022-2011 Trailing-vortex drag coefficient in shock-free attached flow – cambered and twisted wings