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SAE Aerospace Applied Thermodynamics Manual Aerothermodynamic Systems Engineering and Design
- Aerospace Standard
- AIR1168/3A
- Revised
Downloadable datasets available
Annotation ability available
Sector:
Issuing Committee:
Language:
English
Scope
This section presents methods and examples of computing the steady-state heating and cooling loads of aircraft compartments. In a steady-state process the flows of heat throughout the system are stabilized and thus do not change with time. In an aircraft compartment, several elements compose the steady-state air conditioning load. Transfer of heat occurs between these sources and sinks by the combined processes of convection, radiation, and conduction in the following manner:
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1
Convection between the boundary layer and the outer airplane skin.
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2
Radiation between the external skin and the external environment.
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3
Solar radiation through transparent areas directly on flight personnel and equipment and on the cabin interior surfaces.
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4
Conduction through the cabin walls and structural members.
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5
Convection between the interior cabin surface and the cabin air.
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6
Convection between cabin air and flight personnel or equipment.
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7
Convection and radiation from internal sources of heat such as electrical equipment.
The subsequent paragraphs discuss methods of determining each of the heat transfer rates listed above, as well as the physiological considerations involved in the selection of proper cabin conditions that are to be maintained.
Rationale
Needed to correct errors in document and clarify ground radiation values.
Topic
Data Sets - Support Documents
| Title | Description | Download |
|---|---|---|
| Unnamed Dataset 1 | ||
| Table 3A-1 | Load Values at Sea Level and 20,000 Ft | |
| Table 3A-2 | Values for Temperature and Heat Transfer Coefficient | |
| Table 3A-3 | Results of Analysis | |
| Table 3A-4 | Passenger Heat Generation | |
| Table 3A-5 | Average Values of Heat Transfer Coefficient | |
| Table 3A-6 | Summation of UA Values | |
| Table 3A-7 | Heating Load at 20,000 Ft | |
| Table 3A-8 | Heating and Cooling Loads at Sea Level and 20,000 Ft Altitude | |
| Table 3B-1 | Performance of Vapor Cycle Systems | |
| Table 3B-2 | System Summary | |
| Table 3B-3 | Summary of System COP Values |
Issuing Committee
AC-9 Aircraft Environmental Systems Committee
Furthers the advancement of technology related to the research, design, test and utilization of aircraft environmental and anti-icing/deicing systems. Develops and updates standards, recommended practices, and information reports contributing to the quality, economy, and safety of commercial and military aircraft.
Reference
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