For jet driven aircraft , the take-off thrust to weight ratio to meet Military Balked Landing Climb requirements is plotted using the following relationship:
The aircraft lift coefficient at the given flight condition is found from:
The aircraft drag coefficient at the given flight condition is calculated from:
The zero-lift drag coefficient during approach landing is dependent on the value of the change in zero-lift drag due to flaps at approach position:
The 'B' of the aircraft drag polar with landing flaps and gear up is calculated from:
The engine factor accounts for the number of engines on the aircraft with one engine inoperative, and is calculated from:
See Matching Plot Guidelines: Jet Driven Airplanes
For propeller powered aircraft , the take-off weight to power ratio to meet Military Balked Landing Climb requirements is plotted using the following relationship:
The aircraft lift coefficient at the given flight condition is found from:
See Aircraft Drag Coefficient at the Given Flight Condition described above.
See Factor Accounting for the Number of Engines on the Airplane described above.
See Matching Plot Guidelines: Propeller Driven Airplanes
Note : Equations used in this topic assume the British unit of the parameter used in the program. For the SI unit system, appropriate conversions must be made.