Full-scale wind-tunnel tests, conducted to determine the effects of three different airfoil sections on the aft-fuselage drag of a low-wing aircraft, are described. The measurements indicate a maximum difference in aft fuselage drag between the three airfoils of about 0.002. Measured changes in the locations of the fuselage pressure contours with airfoil section correlated well with the changes predicted by a three dimensional paneling code. A criterion, based on the inviscid computer code, is then proposed as an indicator for possible adverse viscous interactions at the wing-fuselage juncture.
Full-scale wind-tunnel study of wing-fuselage interaction and comparison with paneling method
Aircraft Systems and Technology Conference ; 1981 ; Dayton, OH
1981-08-01
Conference paper
No indication
English
Engineering Index Backfile | 1933
|Engineering Index Backfile | 1933
|