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The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow

Description: Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date: November 12, 1952
Creator: Love, Eugene S.

Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Description: Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds.
Date: July 10, 1953
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.

Investigation of wing characteristics at a Mach number of 1.53 II : swept wings of taper ratio 0.5

Description: Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.
Date: June 28, 1948
Creator: Vincenti, Walter G; Van Dyke, Milton D & Matteson, Frederick H

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds

Description: Results are presented, in graphical and tabular form, from a wind tunnel investigation of the lift, drag, and pitching moment characteristics of thin, low-aspect-ratio wings in combination with a body at Mach numbers from 0.25 to as high as 1.9. The following are analyzed and compared with existing theoretical results: 1. Effects of aspect ratio on 3-percent-thick triangular wings; 2. Effects of plan form on 3-percent-thick triangular, sweptback, and unswept wings of aspect ratios 2 and 3; 3. Effects of wing thickness on triangular wings of aspect ratio 2; 4. Effects of profile shape on triangular, sweptback, and unswept wings; and 5. Effects of camber and twist on triangular wings of aspect ratios 2 and 4.
Date: April 14, 1953
Creator: Hall, Charles F