Download Free Effects Of Twist And Camber On The Low Speed Longitudinal Stability Characteristics Of A 45c Swept Back Wing Of Aspect Ratio 8 At Reynolds Numbers From 15 X 106 To 48 X 10 As Determined By Pressure Distributions Force Tests And Calculations Book in PDF and EPUB Free Download. You can read online Effects Of Twist And Camber On The Low Speed Longitudinal Stability Characteristics Of A 45c Swept Back Wing Of Aspect Ratio 8 At Reynolds Numbers From 15 X 106 To 48 X 10 As Determined By Pressure Distributions Force Tests And Calculations and write the review.

An investigation at low scale has been made in the Langley stab unity tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber on the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio 0.6, and with 45 deg sweepback of the quarter-chord line. Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the wings investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted and cambered or plane wing. A combination of twist and camber generally extended the initial linear range of several of the static- and rotary-stability derivatives to a higher lift coefficient and, although these effects were small, higher Reynolds numbers may result in larger effects.
Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tail locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 105 and at Mach numbers less than 0.25.