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| Author | : Frederick C. Grant |
| Publisher | : |
| Total Pages | : 108 |
| Release | : 1960 |
| Genre | : |
| ISBN | : |
| Author | : Richard T. Whitcomb |
| Publisher | : |
| Total Pages | : 20 |
| Release | : 1960 |
| Genre | : Airplanes |
| ISBN | : |
Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
| Author | : Thomas C. Kelly |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1957 |
| Genre | : Aerodynamic load |
| ISBN | : |
Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
| Author | : George H. Holdaway |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1960 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : Odell A. Morris |
| Publisher | : |
| Total Pages | : 22 |
| Release | : 1962 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : Donald L. Loving |
| Publisher | : |
| Total Pages | : 92 |
| Release | : 1961 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 1134 |
| Release | : 1989 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Macon C. Ellis |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1949 |
| Genre | : Aerodynamic, Supersonic |
| ISBN | : |
Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.
| Author | : George H. Holdaway |
| Publisher | : |
| Total Pages | : 62 |
| Release | : 1959 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : J. A. Clyde |
| Publisher | : |
| Total Pages | : 157 |
| Release | : 1984 |
| Genre | : |
| ISBN | : |
A tactical supercritical flow research model was designed to achieve high aerodynamic efficiency at Mach number 0.90 and lift coefficient 0.50 using numerical transonic design procedures. A wind tunnel model was built and tested in the Rockwell International Trisonic Wind Tunnel at Mach numbers of 0.40, 0. 85, 0.90, 0.95. Lift-drag ratio at the design condition compared favorably with theoretical upper bound levels for the test arrangement and conditions. Six component force measurements for the joined wing are well behaved and near linear over an angle-of-attack range of -4
