Download Free Wind Tunnel Investigation At High Subsonic Speeds Of The Effect Of Spoiler Profile On The Lateral Control Characteristics Of A Wing Fuselage Combination With Quarter Chord Line Swept Back 326 Degrees And Naca 65a006 Airfoil Section Book in PDF and EPUB Free Download. You can read online Wind Tunnel Investigation At High Subsonic Speeds Of The Effect Of Spoiler Profile On The Lateral Control Characteristics Of A Wing Fuselage Combination With Quarter Chord Line Swept Back 326 Degrees And Naca 65a006 Airfoil Section and write the review.

An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
A wind-tunnel investigation has been made through a speed range from a Mach number of approximately 0.90 to determine the lateral-control characteristics of a 2-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoiler on a semispan-wing model with aspect ratio of 3.06 having 51.3 degree sweepback of the wing leading edge. In addition, the aerodynamic characteristics of the plain wing were determined through the speed range.