Effect of Fixed Forward Fins! Changes in Lift and Moment Characteristics of Slender Aircraft and Missiles
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 1 September 1960
Abstract
An estimate is made of the effect of adding a small forward fin on the lift and centre of pressure of a slender wing‐body combination. The fin is assumed to discharge a trailing vortex which interacts with the main lifting surface. Design charts permit rapid estimation of lift loss and centre of pressure movement for a delta wing plus body. At the lower angles of attack, the lift loss on the wing is approximately equal to the lift of the forward surface itself. Most of the lift is lost at the front of the wing, and so wing centre of pressure moves aft with addition of the forward fin. Theoretical estimates are in general agreement with experimental results at Mach numbers 1·65 and 2·41.
Citation
Campbell, G.S. (1960), "Effect of Fixed Forward Fins! Changes in Lift and Moment Characteristics of Slender Aircraft and Missiles", Aircraft Engineering and Aerospace Technology, Vol. 32 No. 9, pp. 271-274. https://doi.org/10.1108/eb033299
Publisher
:MCB UP Ltd
Copyright © 1960, MCB UP Limited