A wind-tunnel investigation of the development of lift on wings in accelerated longitudinal motion
National Aeronautics and Space Administration, 1960 - Technology & Engineering - 16 pages
An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the development of lift on a wing during a simulated constant-acceleration catapult take-off. The investigation included models of a two-dimensional wing, an unswept wing having an aspect ratio of 6, a 35 deg. swept wing having an aspect ratio of 3.05, and a 60 deg. delta wing having an aspect ratio of 2.31. All the wings investigated developed at least 90 percent of their steady-state lift in the first 7 chord lengths of travel. The development of lift was essentially independent of the acceleration when based on chord lengths traveled, and was in qualitative agreement with theory.
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accelerated lift acceleration when based Aeronautical Laboratory agreement with theory airfoil section angle of attack aspect ratio based on chord catapult take-off CD H chord lengths traveled constant acceleration constant velocities CQ H delta wing develop steady-state lift developed 90 percent development of lift Door open doors were opened Dynamic pressure Dynamic-pressure pickup effect of acceleration experimental curve experimental two-dimensional fewer chord lengths finite given in figure H CD high sensitivity independent of acceleration Langley Field lengths of travel lift ratio lift-ratio value low sensitivity mean aerodynamic chords model had NACA NACA RM obtained oscillograms plan-form wing practically independent presented in figure qualitative agreement ratio of accelerated ratio with chord special test section stall swept swept-wing theoretical curves theory of reference three chord lengths tube tunnel airstream two-dimensional wing unswept wing fig variation WIND-TUNNEL INVESTIGATION wings develop WINGS IN ACCELERATED wings investigated developed