Minimal safe speed of the asymmetrically loaded combat airplane
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Purpose The purpose of this paper is to present a method for determining the safe flight boundaries of the asymmetrically loaded airplane in the terminal flight phases. The method is applicable to both, the inherent airplane asymmetries and those asymmetries resulting from the airplane use irregularities, asymmetric stores under the wing being one of the examples. The method is aimed to be used in the airplane design and combat airplane service life support.Keywords:
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A method for making preliminary estimates of wing weights is described. Equations are given to show the manner in which spar cap, spar web, rib, and miscellaneous weights vary with the dimensions of the airplane. F purposes of making preliminary weight estimates it is desirable to know the manner in which wing weight depends upon the size and shape of an airplane. Such knowledge can also be of use in determining a wing that will give the best compromise between structural lightness and performance for any given case. In this present report is described an approximate method that has been used at the Douglas Company for estimating wing weights and also for studying the trend of wing weights for large airplanes.
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Weight estimation
Wing loading
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A theoretical lateral-stability analysis of the XC-120 airplane, equipped with a detachable fuselage, was made to determine the effect on the lateral stability of the high angle of wing incidence for which the airplane was designed. The results of the investigation indicated that the lateral stability of the airplane is satisfactory with or without the detachable fuselage installed (p. 1).
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Fuselage
Longitudinal static stability
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Computational figures of airplane surface are made to catch an airplane shape in the sence of sight. The airplane surface is described with a large number of quadrangles which are based on section lines of the airplane. In one concrete example, the section lines of an airplane model are measured. This airplane model is composed of a body, a wing, a tail unit and two jet engine nacelles. Several figures of the airplane model in various point of vision are drawn by using the law of perspective. These figures give us clear information of the Shape of the airplane model.
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Jet engine
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The calculation of mass distribution characteristics of airplane is an important but complicated and difficult work. A method for calculating mass distribution characteristics of passenger airplane is studied in this paper, it is simple and easy to calculate. Numerical results show that the method provides an effective tool for calculation of passenger airplane design.
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Mass distribution
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A flight investigation was made on a large sweptback-wing bomber airplane and the results are compared with data previously obtained at low altitude (5,000 feet). The effects of wing flexibility on the wing strains were, on the average, about 20 percent larger at the higher altitude.
Airplane
Wing loading
Wing twist
Wing configuration
Low altitude
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Purpose The purpose of this paper is to present a method for determining the safe flight boundaries of the asymmetrically loaded airplane in the terminal flight phases. The method is applicable to both, the inherent airplane asymmetries and those asymmetries resulting from the airplane use irregularities, asymmetric stores under the wing being one of the examples. The method is aimed to be used in the airplane design and combat airplane service life support.
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Report presenting power spectral methods of analysis as applied to flight test measurements of the strain responses of a large swept-wing bomber airplane in rough air in order to determine the effects of airplane in rough air in order to determine the effects of airplane structural dynamics on the strain responses.
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Wing loading
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