Accession Number : AD0463569


Title :   A STUDY OF TWIST AND CAMBER ON WINGS IN SUPERSONIC FLOW


Descriptive Note : Final rept.


Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB


Personal Author(s) : Durgin, Frank H


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/463569.pdf


Report Date : Nov 1964


Pagination or Media Count : 191


Abstract : The object of this program was to study both theoretically and experimentally methods for designing the twist and camber of wing planforms to yield high lift-drag ratios at supersonic speeds. Calculations based on linear supersonic wing theory were made to determine the effects of various types of load distributions on the drag due to lift and on the wing shape. In particular, only solutions with smooth finite pressure distributions and finite perturbation velocities, leading to easily built wing shapes, were accepted. It was hoped, by imposing such constraints, to avoid the high drag losses due to shock waves, flow separation and the formation of detached vortices. The calculation procedure was used to design versions of arrow and double delta planforms warped to obtain improved drag due to lift at Mach number 3.


Descriptors :   *DELTA WINGS , *JET TRANSPORT AIRCRAFT , OPTIMIZATION , DISTRIBUTION , SHOCK WAVES , BOUNDARY LAYER , VORTICES , FLOW VISUALIZATION , MODEL TESTS , MATHEMATICAL ANALYSIS , AERODYNAMIC LOADING , PRESSURE , GRAPHICS , TABLES(DATA) , SEPARATION , EQUATIONS , SUPERSONIC FLOW , DRAG , WINGS , LIFT , SUPERSONIC CHARACTERISTICS , REYNOLDS NUMBER , WIND TUNNEL MODELS , SUPERSONIC AIRCRAFT , CAMBER , THIN WINGS , THICKNESS , EXPERIMENTAL DATA


Subject Categories : Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE