摘要 :
Equations are developed using the source distribution method for the velocity potential function and pressure on thin wings in steady and unsteady motion. Closed form solutions are given for harmonically oscillating wings of gener...
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Equations are developed using the source distribution method for the velocity potential function and pressure on thin wings in steady and unsteady motion. Closed form solutions are given for harmonically oscillating wings of general plan form including the effect of the wing wake. Some useful examples are presented in an appendix for arrow, semielliptical, and hexagonal plan form wings.
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摘要 :
A summary of some results from tests of a wing-body general research missile model is presented for a Mach number range up to 4.63. A basic ogive-cylinder body with a length-to-diameter ratio of 10 was used to which was attached a...
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A summary of some results from tests of a wing-body general research missile model is presented for a Mach number range up to 4.63. A basic ogive-cylinder body with a length-to-diameter ratio of 10 was used to which was attached a series of wing planforms. The planforms included a family of delta wings and a family of rectangular wings having a constant root chord but varying spans so that wings of constant exposed area could be compared. In addition, a cranked-tip planform was included and a rectangular planform with reduced chord. Some results are presented for wing-body-tail configurations - one utilizing a cranked wing planform and one with wings having a constant root chord and span, but tip chords that were 0, 20, and 40 percent of the root chord.
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摘要 :
Force and moment characteristics were measured for two trapezoidal oblique wings and a conventional swept wing mounted on a body of revolution at Mach numbers from 0.2S to 2.0. Both oblique wings had the same planform, but differe...
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Force and moment characteristics were measured for two trapezoidal oblique wings and a conventional swept wing mounted on a body of revolution at Mach numbers from 0.2S to 2.0. Both oblique wings had the same planform, but differed in profile and flexibility. One of the oblique wings was made of solid steel and had a maximum thickness-to-chord ratio of 4 percent. The other wing was built up by taking an aluminum wing (having a geometrically similar profile and planform to that of the steel wing) and adding epoxy material to the upper surface to increase the maximum thickness-to-chord ratio to 8.2 percent. The aspect ratio for both oblique wings when swept 45°, and for the swept wing with 45° of sweep was 4.1. Data were obtained at unit Reynolds numbers ranging from 3.3 to 8.2 million per meter in order to vary the dynamic pressure and to explore any flexibility effects. These data were compared with previously obtained data (ref. 5) on the aluminum wing before it was built up with epoxy.
Wing flexibility designed into the aluminum and built-up aluminum oblique wings increased the range of lift coefficients from 0.30 to 0.70 over which the pitching-moment curves were linear. However, flexibility did not improve the linearity of the rolling-moment curves and produced sizable side forces. At a Mach number of 0.95, the trapezoidal oblique wing had little or no improvement in the lift/drag ratios over those for a conventional swept wing of the same aspect ratio, sweep, and profile, probably because of the thinness of the wing profile. Thicker, highly cambered profiles previously investigated on oblique wings showed considerable improvement in the maximum lift/drag ratios over those for a conventional swept wing with the same profiles throughout a Mach number range from 0.6 to 1.2.
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摘要 :
Design studies on an oblique folding wing for a 34-in.-diameter, subsonic, cruise-type missile are described. Aeroelastic divergence and load amplification are investigated. It is found that divergence is not a problem, but load b...
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Design studies on an oblique folding wing for a 34-in.-diameter, subsonic, cruise-type missile are described. Aeroelastic divergence and load amplification are investigated. It is found that divergence is not a problem, but load buildup on the forward-swept wing and load reduction on the aft-swept wing result in large rolling moments. Design studies of the wing pivot indicate that a Conrad four-point bearing and a torsion-spring actuator should result in a lightweight, reliable, and inexpensive fold mechanism. Weights and volumes of the oblique wing design are computed and compared with results of previous studies of swing-wing and wraparound-wing configurations. The wraparound wing is found to be the lightest and provides the greatest fuel volume. (Author)
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