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Standard

Thermodynamics of Incompressible and Compressible Fluid Flow
2019-04-11
CURRENT
AIR1168/1A
The fluid flow treated in this section is isothermal, subsonic, and incompressible. The effects of heat addition, work on the fluid, variation in sonic velocity, and changes in elevation are neglected. An incompressible fluid is one in which a change in pressure causes no resulting change in fluid density. The assumption that liquids are incompressible introduces no appreciable error in calculations, but the assumption that a gas is incompressible introduces an error of a magnitude that is dependent on the fluid velocity and on the loss coefficient of the particular duct section or piece of equipment. Fig. 1A-1 shows the error in pressure drop resulting from assuming that air is incompressible. With reasonably small loss coefficients and the accuracy that is usually required in most calculations, compressible fluids may be treated as incompressible for velocities less than Mach 0.2.
Standard

Thermodynamics of Incompressible and Compressible Fluid Flow
2011-06-20
HISTORICAL
AIR1168/1
The fluid flow treated in this section is isothermal, subsonic, and incompressible. The effects of heat addition, work on the fluid, variation in sonic velocity, and changes in elevation are neglected. An incompressible fluid is one in which a change in pressure causes no resulting change in fluid density. The assumption that liquids are incompressible introduces no appreciable error in calculations, but the assumption that a gas is incompressible introduces an error of a magnitude that is dependent on the fluid velocity and on the loss coefficient of the particular duct section or piece of equipment. Fig. 1A-1 shows the error in pressure drop resulting from assuming that air is incompressible. With reasonably small loss coefficients and the accuracy that is usually required in most calculations, compressible fluids may be treated as incompressible for velocities less than Mach 0.2.
Standard

The Control of Excess Humidity in Avionics Cooling
2003-10-31
HISTORICAL
ARP987A
The purpose of this document is threefold: (1) to review the problem of moisture in avionics equipment, (2) to outline methods for correcting conditions of excess moisture in existing avionics installations, and (3) to recommend design practices for new avionics cooling system installations which will minimize the adverse effects of moisture.
Standard

The Control of Excess Humidity in Avionics Cooling
2020-05-12
CURRENT
ARP987B
This Aerospace Recommended Practice (ARP) outlines the causes and impacts of moisture and/or condensation in avionics equipment and provides recommendations for corrective and preventative action.
Standard

The Advanced Environmental Control System (AECS) Computer Program for Steady State Analysis and Preliminary System Sizing
2003-10-31
HISTORICAL
AIR1706B
Many different computer programs have been developed to determine performance capabilities of aircraft environmental control systems, and to calculate size and weight tradeoffs during preliminary design. Many of these computer programs are limited in scope to a particular arrangement of components for a specific application. General techniques, providing flexibility to handle varied types of ECS configurations and different requirements (i.e., during conceptual or preliminary design, development, testing, production, and operation) are designated “company proprietary” and are not available for industry-wide use. This document describes capabilities, limitations, and potentials of a particular computer program which provides a general ECS analysis capability, and is available for use in industry. This program, names AECS1, was developed under the sponsorship of the U.S. Air Force Flight Dynamics Laboratory (References 1 and 2).
Standard

THE ADVANCED ENVIRONMENTAL CONTROL SYSTEM (AECS) COMPUTER PROGRAM FOR STEADY STATE ANALYSIS AND PRELIMINARY SYSTEM SIZING
1986-10-01
HISTORICAL
AIR1706A
Many different computer programs have been developed to determine performance capabilities of aircraft environmental control systems, and to calculate size and weight tradeoffs during preliminary design. Many of these computer programs are limited in scope to a particular arrangement of components for a specific application. General techniques, providing flexibility to handle varied types of ECS configurations and different requirements (i.e., during conceptual or preliminary design, development, testing, production, and operation) are designated "company proprietary" and are not available for industry-wide use. This document describes capabilities, limitations, and potentials of a particular computer program which provides a general ECS analysis capability, and is available for use in industry. This program, names AECS1, was developed under the sponsorship of the U.S. Air Force Flight Dynamics Laboratory (References 1 and 2).
Standard

TESTING OF PROTOTYPE AIRPLANE AIR CONDITIONING SYSTEMS
1951-03-15
HISTORICAL
ARP217
These recommendations are written to cover the testing of air conditioning equipment as installed in the prototype aircraft for the purpose of: A Demonstrating safety of the installation. B Demonstrating performance of the installation. a Aircraft ducting and distribution system. b Component parts (i.e., vendors equipment) C Obtaining data for future design.
Standard

TESTING OF COMMERCIAL AIRPLANE ENVIRONMENTAL CONTROL SYSTEMS
1997-10-01
HISTORICAL
ARP217C
These recommendations are written to cover the testing of environmental control equipment, functioning as a complete and installed system in civil aircraft for the purpose of: a Demonstrating the safety of the installation and equipment. b Demonstrating proper functioning of the installation and equipment. c Demonstrating performance of the installation and equipment. d Obtaining data for future design and to aid in the analysis of in-service performance of the system and equipment.
Standard

TESTING OF COMMERCIAL AIRPLANE ENVIRONMENTAL CONTROL SYSTEMS
1973-10-15
HISTORICAL
ARP217B
These recommendations are written to cover the testing of environmental control equipment, functioning as a complete and installed system in civil aircraft for the purpose of: a Demonstrating the safety of the installation and equipment. b Demonstrating proper functioning of the installation and equipment. c Demonstrating performance of the installation and equipment. d Obtaining data for future design and to aid in the analysis of in-service performance of the system and equipment.
Standard

TEMPERATURE CONTROL EQUIPMENT, AUTOMATIC, AIRPLANE CABIN
1956-03-15
HISTORICAL
ARP89B
This recommended practice covers automatic cabin temperature control systems of the following types for pressurized and unpressurized cabins: Type I - Proportioning. Type II - On-Off, or Cycling. Type III - Floating, including modifications thereof.
Standard

TEMPERATURE CONTROL EQUIPMENT, AUTOMATIC, AIRCRAFT COMPARTMENT
1992-03-01
HISTORICAL
ARP89C
The recommendations of this ARP are primarily intended to be applicable to temperature control of compartments, occupied or unoccupied, of civil aircraft whose prime function is the transporting of passengers or cargo. The recommendations will apply, however, to a much broader category of civil and military aircraft where automatic temperature control systems are applicable.
Standard

TEMPERATURE CONTROL EQUIPMENT, AUTOMATIC AIRPLANE CABIN
1943-01-01
HISTORICAL
ARP89
These specifications are written to cover automatic temperature controls under three classifications, namely: A AUTOMATIC TEMPERATURE CONTROLS - GENERAL - Dealing with features applicable to all types and uses. B AUTOMATIC TEMPERATURE CONTROLS - MILITARY AND COMMERCIAL - Covering features applicable to military aircraft and commercial aircraft. C DESIRABLE DESIGN FEATURES - General information for use of those concerned in meeting the requirements contained herein.
Standard

Spacecraft Life Support Systems
2011-06-20
HISTORICAL
AIR1168/14
A life support system (LSS) is usually defined as a system that provides elements necessary for maintaining human life and health in the state required for performing a prescribed mission. The LSS, depending upon specific design requirements, will provide pressure, temperature, and composition of local atmosphere, food, and water. It may or may not collect, dispose, or reprocess wastes such as carbon dioxide, water vapor, urine, and feces. It can be seen from the preceding definition that LSS requirements may differ widely, depending on the mission specified, such as operation in Earth orbit or lunar mission. In all cases the time of operation is an important design factor. An LSS is sometimes briefly defined as a system providing atmospheric control and water, waste, and thermal management.
Standard

Heat Sinks for Airborne Vehicles
2012-07-12
HISTORICAL
AIR1957
This document summarizes types of heat sinks and considerations in relation to the general requirements of aircraft heat sources, and it provides information to achieve efficient utilization and management of these heat sinks. In this document, a heat sink is defined as a body or substance used for removal of the heat generated by hydrodynamic or thermodynamic processes. This document provides general data about airborne heat sources, heat sinks, and modes of heat transfer. The document also discusses approaches to control the use of heat sinks and techniques for analysis and verification of heat sink management. The heat sinks are for aircraft operating at subsonic and supersonic speeds.
Standard

General Requirements for Application of Vapor Cycle Refrigeration Systems for Aircraft
1997-10-01
HISTORICAL
ARP731B
Recommendations of this ARP refer specifically to the application of closed cycle vapor cycle refrigeration systems as a source of cooling in an aircraft air conditioning system. General recommendations for an air conditioning system which may include a vapor cycle system as a cooling source are included in ARP85, Air Conditioning Equipment, General Requirements for Subsonic Airplanes, ARP292, Air Conditioning, Helicopters, General Requirements For, and AIR806, Air Conditioning Design Information for Cargo and High Density Passenger Transport Airplanes, and are not included herein. Vapor cycle refrigeration system design recommendations are presented in this ARP in the following general areas: a SYSTEM Design Recommendations: (See Section 3) b COMPONENT Design Recommendations: (See Section 4) c Desirable Design Features: (See Section 5)
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