NDLI: Aircraft performance studied on an electronic analog computer

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Aircraft performance studied on an electronic analog computer

Content Provider	ACM Digital Library
Author	Wadel, L. B. Wan, C. C.
Abstract	Performance analysis of an airplane consists of the study of various operating characteristics and operating limits. These characteristics may be divided essentially into three major groups as follows: 1. Performance at Constant Altitudes. These include the conventional performance characteristics such as maximum speed, rate of climb, and equilibrium turn performance. All of these items may be determined by comparison of "thrust available" and "thrust required" for steady-state operations, based on constant airplane weight and constant altitude. 2. Performance at Varying Altitudes. For certain portions of a typical flight program, fuel economy and elapsed time become factors of major importance. It is necessary to establish a theoretical optimum operating schedule which would serve as an upper bound to the attainable performance. Optimum-climb programs for an interceptor and optimum-cruise profiles for a long range bomber belong to this category. Although these problems may be rigorously resolved by means of the calculus of variations, equivalent methods requiring only steady-state considerations can be formulated to yield the required solutions. 3. Range Performance. The maximum range, or radius of action, of an airplane for a specific mission profile is one of the most important items in performance analysis. Here, the variation of operating altitudes and airplane weight must be properly accounted for. Generally, this can be achieved through appropriate combination of results obtained from the first two groups.
Starting Page	78
Ending Page	82
Page Count	5
File Format	PDF
DOI	10.1145/1455292.1455306
Language	English
Publisher	Association for Computing Machinery (ACM)
Publisher Date	1955-03-01
Publisher Place	New York
Access Restriction	Subscribed
Content Type	Text
Resource Type	Article

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