A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling
The performances of two linear aerospike nozzles, generated by truncating the same plug contour at 40% and 20% of its ideal length, are investigated numerically within a two-dimensional approximation and compared with each other. The nozzle geometry is a 2D representation, extracted from the CAD mod...
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MDPI AG
2025-02-01
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| author | Jehangir Hassan Gaetano Maria Di Cicca Michele Ferlauto Roberto Marsilio Emanuele Resta |
| author_facet | Jehangir Hassan Gaetano Maria Di Cicca Michele Ferlauto Roberto Marsilio Emanuele Resta |
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| description | The performances of two linear aerospike nozzles, generated by truncating the same plug contour at 40% and 20% of its ideal length, are investigated numerically within a two-dimensional approximation and compared with each other. The nozzle geometry is a 2D representation, extracted from the CAD model of the actual nozzles under experimental investigation. In the working conditions studied here, the nozzle is throttled differentially, by setting different flow conditions on the upper and lower inlet, with the aim of generating thrust vectoring effects. The performances and flowfield of both aerospikes are investigated for values of the nozzle pressure ratio (<span style="font-variant: small-caps;">npr</span>) ranging from 3.7 up to the design condition (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi mathsize="small">NPR</mi><mo>=</mo><mn>200</mn></mrow></semantics></math></inline-formula>), and for several levels of differential throttling. The CFD approach adopted is based on a two-dimensional RANS flow model. Comparisons between the numerical and experimental data are performed at two nozzle working conditions: without and with differential throttling. The numerical results are in good agreement with the experimental data. Moreover, the numerical simulations of the throttling case have shown a thrust deflection of about 5 degrees, with a differential pressure of approximately 10 percent. |
| format | Article |
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| institution | Kabale University |
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| language | English |
| publishDate | 2025-02-01 |
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| spelling | doaj-art-6fb147e83e6b4193a2c05c4b825650cb2025-08-20T03:40:41ZengMDPI AGAerospace2226-43102025-02-0112320010.3390/aerospace12030200A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential ThrottlingJehangir Hassan0Gaetano Maria Di Cicca1Michele Ferlauto2Roberto Marsilio3Emanuele Resta4Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDepartment of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDepartment of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDepartment of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDepartment of Mechanical and Aerospace Engineering, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyThe performances of two linear aerospike nozzles, generated by truncating the same plug contour at 40% and 20% of its ideal length, are investigated numerically within a two-dimensional approximation and compared with each other. The nozzle geometry is a 2D representation, extracted from the CAD model of the actual nozzles under experimental investigation. In the working conditions studied here, the nozzle is throttled differentially, by setting different flow conditions on the upper and lower inlet, with the aim of generating thrust vectoring effects. The performances and flowfield of both aerospikes are investigated for values of the nozzle pressure ratio (<span style="font-variant: small-caps;">npr</span>) ranging from 3.7 up to the design condition (<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi mathsize="small">NPR</mi><mo>=</mo><mn>200</mn></mrow></semantics></math></inline-formula>), and for several levels of differential throttling. The CFD approach adopted is based on a two-dimensional RANS flow model. Comparisons between the numerical and experimental data are performed at two nozzle working conditions: without and with differential throttling. The numerical results are in good agreement with the experimental data. Moreover, the numerical simulations of the throttling case have shown a thrust deflection of about 5 degrees, with a differential pressure of approximately 10 percent.https://www.mdpi.com/2226-4310/12/3/200aerospike nozzlefluidic thrust vectoringsupersonic nozzlesrocket nozzles |
| spellingShingle | Jehangir Hassan Gaetano Maria Di Cicca Michele Ferlauto Roberto Marsilio Emanuele Resta A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling Aerospace aerospike nozzle fluidic thrust vectoring supersonic nozzles rocket nozzles |
| title | A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling |
| title_full | A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling |
| title_fullStr | A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling |
| title_full_unstemmed | A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling |
| title_short | A Two-Dimensional Analysis of the Flowfield and Performances of Linear Aerospikes During Differential Throttling |
| title_sort | two dimensional analysis of the flowfield and performances of linear aerospikes during differential throttling |
| topic | aerospike nozzle fluidic thrust vectoring supersonic nozzles rocket nozzles |
| url | https://www.mdpi.com/2226-4310/12/3/200 |
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