Shopping Cart

No products in the cart.

ESDU 10022:2011

$163.80

Trailing-Vortex Drag Coefficient in Shock-Free Attached Flow – Cambered and Twisted Wings

Published By Publication Date Number of Pages
ESDU 2011-12-01 154
Guaranteed Safe Checkout
Category:

If you have any questions, feel free to reach out to our online customer service team by clicking on the bottom right corner. We’re here to assist you 24/7.
Email:[email protected]

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° wash-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
$163.80