364. Gross Weight Estimation of an Attack Airplane by Generalized Graphical Solution
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Paper
Abstract
This paper was presented at the Twenty-second Annual National Conference of the Society of Aeronautical Weight Engineers at St. Louis, Missouri, April 29-May 1, 1963. A method of analysis is described in this paper which permits the rapid determination of gross weight and certain design and performance characteristics of an airplane for a given set of specifications.
The subject method requires the establishment of equations for the weight and performance characteristics. These equations are then generalized such that they contain common variables. The variables are fuel load, wing area and take-off gross weight for various values of aspect ratio, structural weight ratio, external stores and constant weight components.
In applying this method it is necessary to select three significant parameters which will permit the weight engineer to write three equations relating structural, propulsion and aerodynamic inputs to the selected parameters. The parameters selected for discussion in this paper are: (1) take-off weight, (2) range, and (3) landing speed.
With the aid of a digital computer the weight engineer is able to investigate a large range of values of take-off weight, wing area, and fuel load. A graphical simultaneous solution of the previously mentioned equations permits the determination of the basic airplane geometric and weight parameters. By plotting gross weight versus wing area for various values of fuel load, structural weight ratio and aspect ratio, a solution is obtained at the intersection of three lines of equal fuel weight. Thus, the solution enforces the compatibility of the resulting gross weight with the performance parameters.
The subject method of preliminary design is equally effective whether there is a large of meager amount of data. It is necessarily approximate, but it will eliminate the need for the weight engineer to use a trail-and-error method for the determination of design data.
