A Low Speed Investigation Of A High Lift Lateral Control Device Consisting Of A Spoiler Slot Deflector And A Trailing Edge Flap On A Tapered 45 Degree Sweptback Wing

A Low-speed Investigation of a High-lift Lateral-control Device Consisting of a Spoiler-slot-deflector and a Trailing-edge Flap on a Tapered 45 Degree Sweptback Wing

An investigation has been made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a spoiler-slot-deflector configuration in combination with a trailing-edge 29-percent-chord high-lift flap extending from the 14- to the 67-percent-semispan station. The wing has a sweepback of 45 degree of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil parallel to the plane of symmetry. Additional tests were made with the flap neutral to evaluate the effects of deflector projection on the characteristics of the wing equipped with a spoiler-slot-deflector configuration having the same span and spanwise position as the spoiler and deflector had with the flap deflected.

Effect of High-Lift Devices on the Static-Lateral-Stability Derivatives of a 45 Deg Sweptback Wing of Aspect Ratio 4.0 and Taper Ratio 0.6 in Combination With A Body

An investigation has been made in the Langley stability tunnel to determine the effect of high-lift devices on the low-speed static-lateral-stability derivatives of a 45 deg sweptback wing of aspect ratio 4.0 and taper ratio 0.6. Comparison between the increments in the static-lateral-stability derivatives due to flap deflection obtained from experiment and the increments evaluated by a simple sweep theory is also made. The results of the investigation show that, for moderate and high lift coefficients, an increase in trailing-edge flap span, with or without a leading-edge slat, generally resulted in increased effective dihedral and directional stability. The leading-edge slats tended mainly to extend the trends obtained at low lift coefficients for the dihedral effect to nearer maximum lift. An application of simple sweep theory and measured lift and drag increments to the evaluation of the increments in the static-lateral-stability derivatives due to trailing-edge flaps indicates that the trend and approximate magnitude of the variation of these increments with flap span are predicted in the moderate and high lift-coefficient range.

Investigation at Low Speed of 45 Deg and 60 Deg Sweptback, Tapered, Low-Drag Wings Equipped With Various Types of Full-Span, Trailing-Edge Flaps