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Theoretical Analyses to Determine Unbalanced Trailing-Edge Controls Having Minimum Hinge Moments Due to Deflection at Supersonic Speeds

Description: Memorandum presenting analyses based on theoretical results of NACA Report 1041 to determine the plan forms of unbalanced trailing-edge flap-type controls with minimum hinge moments due to deflection and requiring minimum work to overcome the hinge moments due to deflection at supersonic speeds. Results of the analyses for longitudinal controls show high-aspect-ratio untapered controls to possess maximum ratios of lift to hinge moment. Results regarding ratios of lift to hinge moment, ratios of lift to deflection work, ratios of rolling moment to hinge moment, and ratios of rolling moment to deflection work are provided.
Date: November 19, 1952
Creator: Goin, Kennith L.
Partner: UNT Libraries Government Documents Department

Effects of Plan Form, Airfoil Section, and Angle of Attack on the Pressures Along the Base of Blunt-Trailing-Edge Wings at Mach Numbers of 1.41, 1.62, and 1.96

Description: Memorandum presenting an investigation at Mach numbers of 1.41, 1.62, and 1.96 to determine the effects of airfoil section and wing plan form on the pressures acting on the base of blunt-trailing-edge wings operating through an angle-of-attack range. The investigation included two groups of untapered wings of aspect ratio 2.7, with one group being unswept and the other with 45 degrees of sweepback. Results regarding the effects of wing location and body size, spanwise variations of base pressures, variations of average base pressure coefficients with angle of attack and wing section, and effects of plan form are provided.
Date: September 16, 1952
Creator: Goin, Kennith L.
Partner: UNT Libraries Government Documents Department

Equations and Charts for the Rapid Estimation of Hinge-Moment and Effectiveness Parameters for Trailing-Edge Controls Having Leading and Trailing Edges Swept Ahead of the Mach Lines

Description: "Existing conical-flow solutions have been used to calculate the hinge-moments and effectiveness parameters of trailing-edge controls having leading and trailing edges swept ahead of the Mach lines and having streamwise root and tip chords. Equations and detailed charts are presented for the rapid estimation of these parameters. Also included is an approximate method by which these parameters may be corrected for airfoil-section thickness" (p. 937).
Date: September 8, 1950
Creator: Goin, Kennith L.
Partner: UNT Libraries Government Documents Department

Effects of trailing-edge bluntness on the lift, drag, and pitching-moment characteristics of unswept, 45 degree swept, and 45 degree delta wings at Mach numbers of 1.41, 1.62, and 1.96

Description: Report presenting an investigation of systematic series of sharp- and blunt-trailing-edge wings to determine the effects of thickening the trailing edges on the lift, drag, and pitching moment characteristics at several Mach numbers. Results indicate that no appreciable zero-lift drag reduction can be obtained by thickening the trailing edges from 1.41 to 1.96, but trailing edges can be thickened appreciably with no increases in zero-lift drag.
Date: June 10, 1953
Creator: Goin, Kennith L. & Westrick, Gertrude C.
Partner: UNT Libraries Government Documents Department