Effect of Fixed Forward Fins! Changes in Lift and Moment Characteristics of Slender Aircraft and Missiles

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