Accession Number : ADA214799
Title : Optimum Supersonic Cruise.
Descriptive Note : Final rept.,
Corporate Author : MICHIGAN UNIV ANN ARBOR DEPT OF AEROSPACE ENGINEERING
Personal Author(s) : Lin, Ching F. ; Vinh, Nguyen X. ; Chern, Jeng S.
Report Date : JUN 1979
Pagination or Media Count : 40
Abstract : This 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)
Descriptors : AERODYNAMIC CHARACTERISTICS, ALTITUDE, AIRCRAFT, CONTROL THEORY, JET ENGINES, JET FIGHTERS, LEVEL FLIGHT, MACH NUMBER, MATHEMATICAL MODELS, OPTIMIZATION, STRATOSPHERE, SUBSONIC FLIGHT, SUPERSONIC FLIGHT, THRUST, TROPOSPHERE.
Subject Categories : Aerodynamics
Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE