Military Climb: Landing

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For jet driven aircraft , the take-off thrust to weight ratio to meet Military Balked Landing Climb requirements is plotted using the following relationship:

 

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The aircraft lift coefficient at the given flight condition is found from:

 

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The  aircraft drag coefficient at the given flight condition is calculated from:

 

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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:

 

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The 'B' of the aircraft drag polar with landing flaps and gear up is calculated from:

 

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The engine factor accounts for the number of engines on the aircraft with one engine inoperative, and is calculated from:

 

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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:

 

image\PERF0896_wmf.gif

 

The aircraft lift coefficient at the given flight condition is found from:

 

image\PERF0897_wmf.gif

 

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.