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Investigation of wing characteristics at a Mach number of 1.53 1: triangular wings of aspect ratio 2

Description: Report presenting wind-tunnel testing conducted on three sharp-edge wing models with a thickness ratio of 5 percent and a common triangular plan form of aspect ratio 2. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The experimental lift and moment curves were found to conform essentially with the superposition principle of the linear theory.
Date: December 19, 1947
Creator: Vincenti, Walter G.; Nielsen, Jack N. & Matteson, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep

Description: "A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression sho… more
Date: December 19, 1947
Creator: Luoma, Arvo A.; Bielat, Ralph P. & Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing

Description: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chor… more
Date: December 19, 1947
Creator: Conner, D. William & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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