ESDU 7202172nd Edition, November 1, 2009Complete DocumentEffect of wing on rolling moment due to yawing
Includes all amendments and changes through AC, November 1, 2009
Secure PDF
Single User
$260.00
Print
In Stock
Need it fast? Ask for rush delivery.
Most backordered items can be rushed in from the publisher in as little as 24 hours. Some rush fees may apply. Contact your nearest IHS Markit Office to request rush delivery of any backordered item.
$325.00
Product Details:
 Description / Abstract:
INTRODUCTION
The data given in this Item provide a means of estimating the contribution of a straight-tapered swept wing to the rolling moment derivative due to yawing at lift coefficients for which the flow remains fully attached (see Item No. 66033 for wings with symmetrical sections) and at Mach numbers for which the flow is subsonic over the whole of the wing. Some data are included for slender wings of delta and gothic planform. The basic planform contribution (p) and the contributions due to dihedral (Γ), twist (ε) and deflected trailing edge flaps (f) can be taken into account, i.e.  
|
English
(