An investigation was conducted in the Langley 8 foot transonic pressure tunnel to determine the effects of wing transition location and of slotted and unslotted full span flaps on the longitudinal aerodynamic characteristics of a 1/15 scale model of a variable wing sweep tactical fighter model. Tests were at Mach numbers from 0.70 to 0.85 for a wing leading edge sweep of 26 deg.
Effect of Wing-Transition Location and Slotted and Unslotted Flaps on Aerodynamic Characteristics of a Fighter Model at High Subsonic Speeds
1969
46 pages
Report
No indication
English