The paper presented the analysis of optimum cruise at constant altitude of a typical high thrust-to-weight ratio fighter aircraft. A mathematical modeling of aerodynamic and engine characteristics was given and it facilitated the application of optimum control theory to analyze different cruise programs of practical interest. For the example aircraft, it has been found that in the problem of maximum range, there exist two optimum altitudes for cruise, one in the troposphere and one in the stratosphere. The corresponding optimum Mach number in the troposphere is subsonic and in the stratosphere is supersonic. (jes)
Optimum Supersonic Cruise
1979
40 pages
Report
No indication
English
NTIS | 1985
|NTRS | 1985
|TIBKAT | 1985
|NTRS | 1971
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