TAILIEUCHUNG - Thermodynamics Interaction Studies Solids, Liquids and Gases 2011 Part 10

Tham khảo tài liệu 'thermodynamics interaction studies solids, liquids and gases 2011 part 10', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | 440 Thermodynamics - Interaction Studies - Solids Liquids and Gases Curve 1 Error compared to HT model for T0 3000 K Curve 2 Error compared to HT model for T0 2000 K Curve 3 Error compared to HT model for To 1000 K Exit Mach number a Temperature ratio. b Density ratio. c Critical sections ratio. d Thrust coefficient. Fig. 17. Variation of the relative error given by supersonic parameters of PG versus Mach number. Results for the supersonic nozzle application Figure 18 presents the variation of the Mach number through the nozzle for To 1000 K 2000 K and 3000 K including the case of perfect gas presented by curve 4. The example is selected for Ms for the PG model. If To is taken into account we will see a fall in Mach number of the dimensioned nozzle in comparison with the PG model. The more is the temperature To the more it is this fall. Consequently the thermodynamics parameters force to design the nozzle with different dimensions than it is predicted by use the PG model. It should be noticed that the difference becomes considerable if the value To exceeds 1000 K. Figure 19 present the correction of the Mach number of nozzle giving exit Mach number Ms dimensioned on the basis of the PG model for various values of To One can see that the curves confound until Mach number MS for the whole range of To From this value the difference between the three curves 1 2 and 3 start to increase. The curves 3 and 4 are almost confounded whatever the Mach number if the value of To is lower than 1000 K. For example if the nozzle delivers a Mach number MS at the exit section on the assumption of the PG model the HT model gives Mach number equal to Ms and for To 1000 K 2000 K and 3000 K respectively. The numerical values of the correction of the exit Mach number of the nozzle are presented in the table 10. 441 Effect of Stagnation Temperature on Supersonic Flow Parameters with Application for Air in Nozzles 4 J 2 HT rs 3000 K HT ĩo

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