I calculated the maximum Structural/Physiological limit load factor for the F-4. With this I am able to calculate the maximum turn rate and the minimum turn radius at 25,000 ft and at sea level.

I used a drag model that represented the F-43 to compute its thrust and drag at 40,000 ft with afterburner on (Configuration 1) and at 10,000 ft with afterburner off (Configuration 2). I also calculated the F-34's range factor for the altitudes in the troposphere and stratosphere.

I developed a program that incorporates the Hill-Peterson procedure to determine the thrust and thrust-specific fuel consumption of a low bypass turbofan engine with afterburner at sea level and from Mach number 0 to 1. If given specific jet engine parameters, this program output various values such as the thrust and the thrust specific fuel consumption at a given altitude.

A mathematical model of the atmosphere from 0 to 232940 ft in altitude.