Optimum Supersonic Cruise.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1979
- Accession Number
- ADA214799
Entities
People
- Ching F. Lin
- Jeng S. Chern
- Nguyen X. Vinh
Organizations
- University of Michigan