Design and Performance Evaluation of a Novel Aerospike Nozzle Compared to a Conventional De Laval Nozzle: Numerical and Experimental Study

Ahmet Meram

doi:10.56753/ASREL.2025.1.4

Ahmet Meram, Altan Berdan Minaz

Year : 2025
Vol : 4
Issue : 1
Page : 49-61

DOI : 10.56753/ASREL.2025.1.4

In this study, a uniquely designed aerospike rocket nozzle was developed, and its performance was compared both numerically and experimentally with that of a conventional De Laval rocket nozzle. Nozzles are critical components of rocket engines, responsible for accelerating and directing the high-energy exhaust gases generated in the combustion chamber to produce thrust. The geometry and aerodynamic characteristics of a nozzle significantly influence the overall efficiency, fuel consumption, and mission success of a rocket system. The type of nozzle used in a rocket engine varies depending on the mission profile, atmospheric conditions, and altitude range. Among the most widely used nozzle types are the De Laval and aerospike nozzles. While De Laval nozzles are optimized for specific altitude conditions with fixed geometries, aerospike nozzles can adapt to changing ambient pressures, maintaining high aerodynamic efficiency over a wide range of altitudes. This makes them particularly suitable for Single Stage to Orbit (SSTO) missions. Due to their altitude-compensating nature, aerospike nozzles provide more efficient thrust and reduced fuel consumption, especially at lower altitudes where environmental pressure varies significantly. In this research, both nozzle types were evaluated under identical conditions, including the same combustion chamber and propellant. Numerical analyses were conducted using ANSYS Fluent software to simulate pressure, temperature, and velocity distributions within each nozzle. Mesh structures, boundary conditions, and turbulence models were carefully selected to improve the accuracy of the simulations. Based on the numerical results, performance trends of each nozzle design were assessed, followed by experimental testing in a laboratory environment. Experimental measurements included thrust force, exhaust gas velocity, and temperature, which were then compared with the numerical data. The findings revealed a strong correlation between simulation and experimental results.

Cite this Article As : Minaz, A.B., & Meram, A. (2025). Design and Performance evaluation of a novel aerospike nozzle compared to a conventional de laval nozzle: Numerical and experimental study. Aerospace Research Letters (ASREL), 4(1), 49-61. https://doi.org/10.56753/ASREL.2025.1.4

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Design and Performance Evaluation of a Novel Aerospike Nozzle Compared to a Conventional De Laval Nozzle: Numerical and Experimental Study, Research Article,
2025, Vol. 4 (1)

Received : 30.05.2025, Accepted : 12.06.2025 , Published Online : 30.06.2025