Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method
The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the...
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| Format: | Article |
| Language: | English |
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MDPI AG
2021-12-01
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| Series: | Fluids |
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| Online Access: | https://www.mdpi.com/2311-5521/6/12/441 |
| _version_ | 1827672536250318848 |
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| author | Emanuele Resta Roberto Marsilio Michele Ferlauto |
| author_facet | Emanuele Resta Roberto Marsilio Michele Ferlauto |
| author_sort | Emanuele Resta |
| collection | DOAJ |
| description | The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very complex structures that interact with the external flow. In the present work, the experimental data on a nozzle designed and tested for a supersonic cruise aircraft are used for validating the numerical tool at different flight Mach numbers and nozzle pressure ratios. Then, an optimal position for the slot is sought and the fully 3D flow at flight Mach number <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mo>∞</mo></msub><mo>=</mo><mn>0.9</mn></mrow></semantics></math></inline-formula> is investigated numerically for different values of the SVC forcing. |
| first_indexed | 2024-03-10T04:09:43Z |
| format | Article |
| id | doaj.art-f4717813692844f69133b1e635d1df90 |
| institution | Directory Open Access Journal |
| issn | 2311-5521 |
| language | English |
| last_indexed | 2024-03-10T04:09:43Z |
| publishDate | 2021-12-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Fluids |
| spelling | doaj.art-f4717813692844f69133b1e635d1df902023-11-23T08:15:33ZengMDPI AGFluids2311-55212021-12-0161244110.3390/fluids6120441Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control MethodEmanuele Resta0Roberto Marsilio1Michele Ferlauto2Department 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 application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very complex structures that interact with the external flow. In the present work, the experimental data on a nozzle designed and tested for a supersonic cruise aircraft are used for validating the numerical tool at different flight Mach numbers and nozzle pressure ratios. Then, an optimal position for the slot is sought and the fully 3D flow at flight Mach number <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><msub><mi>M</mi><mo>∞</mo></msub><mo>=</mo><mn>0.9</mn></mrow></semantics></math></inline-formula> is investigated numerically for different values of the SVC forcing.https://www.mdpi.com/2311-5521/6/12/441thrust vectoringshock-vector control methodactive flow controlsupersonic nozzle |
| spellingShingle | Emanuele Resta Roberto Marsilio Michele Ferlauto Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method Fluids thrust vectoring shock-vector control method active flow control supersonic nozzle |
| title | Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method |
| title_full | Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method |
| title_fullStr | Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method |
| title_full_unstemmed | Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method |
| title_short | Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method |
| title_sort | thrust vectoring of a fixed axisymmetric supersonic nozzle using the shock vector control method |
| topic | thrust vectoring shock-vector control method active flow control supersonic nozzle |
| url | https://www.mdpi.com/2311-5521/6/12/441 |
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