Gas effect with the presence of the thermal and calorific imperfections on the Prandtl Meyer function

The authors of this paper develop a computational program to determine the effects of gaseous imperfections on calculations of the Prandtl Meyer function. Which is often applied to minimum length nozzle (MLN) design. The aim is to improve the design parameters of supersonic nozzles when using a gas...

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Bibliographic Details
Published in:Indian journal of physics 2024-06, Vol.98 (7), p.2461-2473
Main Authors: Bengherbia, N, Salhi, M, Roudane, M
Format: Article
Language:English
Subjects:
Aerospace industry
Astrophysics and Astroparticles
Defects
Design improvements
Design parameters
Equations of state
Flammable gases
Gases
Ideal gas
Intermolecular forces
Mach number
Original Paper
Physics
Physics and Astronomy
Propulsion systems
Real gases
Stagnation temperature
Supersonic nozzles
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Summary:The authors of this paper develop a computational program to determine the effects of gaseous imperfections on calculations of the Prandtl Meyer function. Which is often applied to minimum length nozzle (MLN) design. The aim is to improve the design parameters of supersonic nozzles when using a gas propellant for cold propulsion or heated thruster systems under a high pressure and temperature. We considered H 2 , O 2 , Cl 2 , N 2 , CO, NO, and air to this end. The Prandtl–Meyer function depends on the stagnation temperature, pressure, Mach number, and the gas used as non-flammable fuel. As values of the parameters of stagnation of the gases increased, their specific heats as well and ratio began to vary, and the ideal gas began behaving as a real gas. This can be explained by Berthelot’s correction of the terms of the equation of state related to a perfect gas, because the co-volume and intermolecular forces of attraction of the gas influenced system. We calculated differences in values of the Prandtl–Meyer function for different gases and air. The results showed that the use of H 2 , N 2 , and CO led to a significant reduction in the weight, length, and volume of the MLN, and it yielded better performance in terms of the manufacture of aerospace propulsion systems that can attain the maximum thrust than when air was used. The performance of the system when the above gases were used was 16% better than when air was used.
ISSN:0973-1458
0974-9845
DOI:10.1007/s12648-023-03004-3