ESDU 88025
Derivation of primary airdata 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 airbreathing 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 RankineHugoniot relationships to derive the required data. ESDUpac A8825 gives as three files a more extensive range of properties than those presented graphically.Indexed under:
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Data Item ESDU 88025  

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ESDUpac A8825 
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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 reentry trajectories 