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SAE AIR1168/8 Revision A, July 1, 2011
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Aircraft Fuel Weight Penalty Due to Air Conditioning
Includes all amendments and changes through Stabilization Notice (No longer revised / updated) , July 2011
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AIA/NAS Aerospace Standards
The purpose of this section is to provide methods and a set of convenient working charts to estimate penalty values in terms of take-off fuel weight for any given airplane mission. The curves are for a range of specific fuel consumption (SFC) and lift/drag ratio (L/D) compatible with the jet engines and supersonic aircraft currently being developed. A typical example showing use of the charts for an air conditioning system is given.

Evaluation of the penalty imposed on aircraft performance characteristics by the installation of an air conditioning system is important for two reasons:

1. It provides a common denominator for comparing systems in the preliminary design stage, thus aiding in the choice of system to be used.

2. It aids in pinpointing portions of existing systems where designs improvements can be most readily achieved.

All factors that influence the flight performance of an aircraft can be expressed in terms of weight, external and momentum drags, and changes in powerplant performance due to bleed air or shaft power extraction, or both. These factors lend themselves to numerical analysis, and the purpose of this chapter is to present and discuss methods that permit their evaluation.

The methods of evaluating performance penalties to an aircraft in flight employ such parameters as flight range, aircraft gross weight, fuel load, payload, speed-altitude characteristics (Refs. 1-3), and the effects of power, landing, and take-off field length limiting cases.

Two major criteria need to be considered in arriving at system take-off weight penalties:

1. Air vehicle weight is assumed fixed, and degradation in range occurs as a result of weight displacing fuel.

2. Range is assumed fixed, and the resultant take-off weight penalty is added to the total airplane weight.

The latter method will be discussed in this section, and is based, in part, on Ref. 4. The former method (degradation in range) can be found, in detail, in Ref. 5.

The optimization process consists of calculating specific penalty numbers for system fixed weight, variable weight, power consumption, ram air, and bleed air consumption, in terms of take-off weight and selecting the system that results in greater payload or range.