Optimum Rate of Climb for High Performance Aircraft.
Abstract
The general aircraft performance problem is considered from the point of view of the balance of forces on an aircraft. The fundamental performance equation yields by use of calculus of variations a closed form equation for the velocity altitude relationship which represent the optimum time climb path. Application of this equation to an operational jet aircraft, the F-4J, yields an actual solution in close agreement with the generally accepted path. This work is done on the assumption that the thrust of a jet engine can be described by a simple quadratic expression. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 21, 1974
- Accession Number
- AD0784112
Entities
People
- Ray P. Craig
Organizations
- United States Naval Academy