Prediction of the loss of wing leading-edge thrust and the accompanying increase in drag due to lift, when flow is not completely attached, presents a difficult but commonly encountered problem. current airplane design and evaluation problems. An improved method for design and evaluation provides for a greater range of airfoil shapes from very sharp to very blunt leading edges. It is also based on a wider range of Reynolds numbers than was available for the previous method. The new method, when employed in computer codes for aerodynamic analysis, generally results in improved correlation with experimental wing-body axial-force data and provides reasonable estimates of the measured drag.
Improved Method for Prediction of Attainable Wing Leading-Edge Thrust
1996
68 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Aerodynamic drag , Aircraft design , Angle of attack , Blunt leading edges , Leading edge thrust , Sharp leading edges , Applications programs (Computers) , Computational fluid dynamics , Reynolds number , Aerodynamic forces , Aircraft performance , Airfoil profiles , Body-wing configurations , Drag coefficients , Lift , Prediction analysis techniques , Two dimensional models , Wing loading
Wing design with attainable thrust considerations
AIAA | 1984
|Wing design with attainable thrust considerations
NTRS | 1984
|