Optimum Rate of Climb for High Performance Aircraft.
NAVAL ACADEMY ANNAPOLIS MD
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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