SAE AIR1168/1

SECTION 1A - INCOMPRESSIBLE FLUID FLOW
1 INTRODUCTION
  1.1 Scope
  1.2 Nomenclature
2 BASIC FLUID MECHANICS
  2.1 Continuity Equation
  2.2 Momentum Equation
  2.3 Energy Equation
  2.4 Viscosity Concepts
  2.5 Boundary Layer Flow
  2.6 Total Pressure Loss Due to Change of Fluid
       Velocity Profile
3 SPECIFIC PRESSURE LOSS DATA
  3.1 Pressure Losses, Straight Ducts
  3.2 Pressure Losses, Elbows
  3.3 Pressure Losses, Duct Area Changes
  3.4 Pressure Losses, Duct Branches
  3.5 Pressure Losses, Internal Installations
  3.6 Pressure Losses, Exits To Compartments
  3.7 Example of Pressure Loss Calculations
4 REFERENCES
SECTION 1B - THERMODYNAMICS AND COMPRESSIBLE FLOW
1 INTRODUCTION
  1.1 Definition and Scope
  1.2 Nomenclature
2 FIRST LAW OF THERMODYNAMICS
3 IDEAL OR PERFECT GASES AS WORKING FLUIDS
  3.1 Equation of State
  3.2 Energy Equations of a Ideal Gas
  3.3 Equations for Mixtures of Ideal Gases
4 THE SECOND LAW OF THERMODYNAMICS
  4.1 Carnot Cycle and Available Energy
  4.2 Methods of Graphical Representations
5 REAL GAS CHARACTERISTICS
  5.1 Van der Waals Equation
  5.2 Beattie-Bridgeman
  5.3 Generalized Reduced Coordinate System
  5.4 Change of Phase
  5.5 Triple Point and Triple Line
  5.6 Latent Heat
  5.7 Critical Point
6 THERMODYNAMICS OF HIGH-VELOCITY GAS FLOWS
  6.1 Introduction
  6.2 Steady-Flow Energy Equation
  6.3 Sonic Velocity and Mach number
  6.4 One-Dimensional Energy Equation for Steady Flow
       Without Heat Transfer
  6.5 Total Temperature, Static Temperature, Velocity,
       and Mach Number Relations
  6.6 Pressure Ration, Density Ration, and Mach Number
       Relations
  6.7 Continuity Relations
  6.8 Illustrative Examples
  6.9 Forces on Internal Flow Passages
  6.10 General Duct Flow
  6.11 Constant Area Duct Flow With Heat Transfer And
       No Friction
  6.12 Constant Area Duct Flow With Friction and No
       Heat Transfer
  6.13 Constant Area Duct Flow With Heat Transfer And
       Friction
  6.14 Mach Waves and Prandtl-Meyer Flow
  6.15 Normal, Oblique, and Conical Shock Waves
  6.16 Subsonic Diffusers
  6.17 Auxiliary Inlets and Diffusers
  6.18 Auxiliary Outlets
  6.19 Supersonic Nozzles and Sonic Venturis
  6.20 Duct Component Losses in Compressible Flow
  6.21 Real Gas Effects
7 REFERENCES

Contains fluid flow which can be treated as isothermal, subsonic and incompressible.

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. At higher velocities and for large loss coefficients (Kt and 4fL/D), compressible flow analysis should be used.