Note On The Drag Of Swept Back And Delta Wings At Supersonic Speeds
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A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0
| Author | : Robert S. Osborne |
| Publisher | : |
| Total Pages | : 20 |
| Release | : 1960 |
| Genre | : Aerodynamics |
| ISBN | : |
Trim Drag at Supersonic Speeds of Various Delta-planform Configurations
| Author | : M. E. Graham |
| Publisher | : |
| Total Pages | : 104 |
| Release | : 1960 |
| Genre | : Drag (Aerodynamics) |
| ISBN | : |
Charts for the Computation of Lift and Drag of Finite Wings at Supersonic Speeds
| Author | : Ellis Lapin |
| Publisher | : |
| Total Pages | : 150 |
| Release | : 1998 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-wedge Sections with the Maximum Thickness at 0.18 Chord
| Author | : Mitchel H. Bertram |
| Publisher | : |
| Total Pages | : 58 |
| Release | : 1954 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section has been conducted at the Langley 11-inch hypersonic tunnel. These wings had a maximum thickness of 8 percent of the chord located at the 18-percent-chord point. For the wings tested at a Mach number of 6.9, the semiapex angle was varied from 5 to 30 degrees and the wings were tested over a range of angle of attack from 0 to 28 degrees and Reynolds numbers in the range of 800,000 to 3,600,000 based on root chord. In addition, pertinent results from tests at Mach number as low as 1.62 have been utilized. The shock-expansion theory and the Newtonian impact theory have been used to analyze the effects of changes made in the various parameters investigated.
Reduction of Drag Due to Lift at Supersonic Speeds
| Author | : Douglas Aircraft Company |
| Publisher | : |
| Total Pages | : 124 |
| Release | : 1955 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
$EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers
| Author | : John A. Moore |
| Publisher | : |
| Total Pages | : 28 |
| Release | : 1957 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
The damping-in-pitch derivative was determined experimentally at Mach numbers of 2.96 and 3.92 for two delta wings having aspect ratios of 2 and 3 and for one sweptback tapered wing having an aspect ratio of 3 by using a free-oscillation technique. The tests were made at Reynolds numbers based on mean aerodynamic chord from 4,000,000 to 12,000,000 for an angle-of-attack range of zero to 10 degrees. The reduced-frequency parameter ranged from 0.006 to 0.022.
