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ESDU 72021

72nd Edition, November 1, 2009

Complete Document

Effect of wing on rolling moment due to yawing

Includes all amendments and changes through AC, November 1, 2009

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Product Details:

  • Revision: 72nd Edition, November 1, 2009
  • Published Date: November 1, 2009
  • Status: Active, Most Current
  • Document Language: English
  • Published By: Engineering Sciences Data Unit (ESDU)
  • Page Count: 21
  • ANSI Approved: No
  • DoD Adopted: No

Description / Abstract:


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.