ESDU 88025: Derivation of primary air-data parameters for hypersonic flight.

Abstract:

ESDU 88025 gives data and methods of analysis for deriving true airspeed, Mach number, pressure height and ambient air temperature from registered values of total pressure and temperature, and static pressure. The methods apply for Mach numbers between approximately 4 and 10 and for heights up to 65 km (210 000 ft). Such air data are of particular importance where they are used to control an air-breathing propulsion unit. The assumptions and limitations of the methods are clearly stated and explained, and a worked example illustrates the use of graphs and tables for the properties of equilibrium air behind a normal shock which are then used with the Rankine-Hugoniot relationships to derive the required data. ESDUpac A8825 gives as three files a more extensive range of properties than those presented graphically.

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Details:

Data Item ESDU 88025
Format:	PDF with software with interactive graphs
Status:	Amendment (D), 01 May 2008 Published in Release 2008-02
Previous Releases:	ESDU 88025 Amendment C
ISBN:	978 0 85679 657 9

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This Data Item is complemented by the following software:

Programs

Name

Details

ESDUpac A8825

Title	Thermodynamic properties of air in equilibrium
Version	1.0

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This Data Item contains 14 interactive graph(s) as listed below.

Graph	Title
Figure 1	Height and Mach number limits to applicability of Data Item
Figure 2a	Thermodynamic properties of imperfect air in equilibrium state
Figure 2b	Thermodynamic properties of imperfect air in equilibrium state
Figure 2c	Thermodynamic properties of imperfect air in equilibrium state
Figure 3a	Thermodynamic properties of imperfect air in equilibrium state
Figure 3b	Thermodynamic properties of imperfect air in equilibrium state
Figure 3c	Thermodynamic properties of imperfect air in equilibrium state
Figure 4a	Rate of change of log relative pressure with temperature at constant entropy
Figure 4b	Rate of change of log relative pressure with temperature at constant entropy
Figure 4c	Rate of change of log relative pressure with temperature at constant entropy
Figure 5 - Part 1	Empirical correction to density at stagnation conditions behind a normal shock fot alternative calculation proceedure of Section 4.4
Figure 5 - Part 2	Empirical correction to density at stagnation conditions behind a normal shock fot alternative calculation proceedure of Section 4.4
Figure A1	Stagnation gas states
Figure A2	Comparison of Mach number, height boundaries for this item with examples of launch and re-entry trajectories