The Squire-Young formula is widely used to calculate profile drag in two-dimensional airfoil analyses. Although experience shows that the formula provides reasonable and accurate predictions, full Navier-Stokes computational fluid dynamics allows for a numerical validation of the formula. A method is presented for evaluating the Squire-Young formula from a computational fluid dynamics solution, and demonstrated for several airfoils. The agreement between profile-drag coefficients determined using the Squire-Young formula and those calculated directly from the computational fluid dynamics solution using surface integration is typically within 2-3% in the low-drag range, with error increasing at higher lift coefficients. The applicability of the underlying assumptions is discussed, and the validity of the assumed variation of shape factor and edge velocity in the wake is investigated for a symmetric airfoil at zero lift. The formula is also demonstrated as being insensitive to spurious drag that may occur due to far-field boundary conditions. Finally, a derivation of the Squire-Young formula is included to further aid in understanding the influence of its assumptions on its predictions. Presented as Paper 2013-0966 at the 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine, TX, 7-10 January 2013
Numerical Validation of the Squire–Young Formula for Profile-Drag Prediction
Journal of aircraft ; 52 , 3
2015
Aufsatz (Zeitschrift)
Englisch
Numerical Validation of the Squire-Young Formula for Profile Drag Prediction
British Library Conference Proceedings | 2013
|SLUB | 1998
|Motor cabin cruiser "the squire"
Engineering Index Backfile | 1951