Numerical investigation of injection angle effects on shock vector control performance

Forghany, F.; Taeibe-Rahni, Mohammad; Asadollahi-Ghohieh, Abdollah; Banazdeh, Afshin

doi:10.1177/0954410017733292

Cited by 8 publications

(5 citation statements)

References 43 publications

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“…SVC demonstrated a vectoring angle of 17.2 • and 17.6 • at NPR = 3 and 4.6. It was reported that the deflection angle increased with moving the injection location upstream and decreased with moving the injection location downstream of the nozzle [4]. At NPR = 4-10 and Secondary Pressure Ratio (SPR) = 1-2, with two different injection locations, the results showed that SPR positively influenced thrust vectoring parameters [5].…”

Section: Introductionmentioning

confidence: 94%

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

et al. 2023

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Modern aircraft and missiles are gradually integrating thrust vector control systems to enhance their military capabilities. Bypass Dual-Throat Nozzle (BDTN) control is a new fluidic thrust vectoring technique capable of achieving superior performance with large vector angles and low thrust loss. In this study, we analyzed the flow characteristics and performance parameters of BDTN by varying the bypass angle, nozzle convergence angle, and bypass width. The flow governing equations are solved according to a finite volume discretization technique of the compressible RANS equations coupled with the Renormalization Group (RNG) k-ϵ turbulence model for Nozzle Pressure Ratio (NPR = 2~10) to capture the significance of under-expanded and over-expanded jets. Results show that by decreasing the bypass angle from 90° to 35°, there is a 6% increase in vectoring angle while the vectoring efficiency is enhanced by 18%. However, a decrease of 3% in the thrust and discharge coefficients is also observed. When the convergence angle was increased from 22° to 37°, vectoring angle, discharge coefficient, and thrust coefficient increased by 2%, 1%, and 0.26%, respectively. Moreover, vectoring efficiency is also enhanced by 8% by reducing the convergence angle from 37° to 22°. Based on the investigated parameters, it is determined that nozzle convergence angle does not significantly influence thrust vectoring performance, however, bypass width and bypass angle have a significant effect on thrust vectoring performance.

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Section: Introductionmentioning

confidence: 94%

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

et al. 2023

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“…The largest deflection angle was achieved when the injection location moved upstream and decreased when it moved downstream. The injection angle also played a vital role in the deflection angle [26]. The effect of secondary flow for an NPR = 4-10 with SPR = 1-2 at two different injection locations was investigated.…”

Section: Effect Of Npr and Sprmentioning

confidence: 99%

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Afridi,

Khan,

Shah

et al. 2023

Energies

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Thrust vectoring innovations are demonstrated ideas that improve the projection of aerospace power with enhanced maneuverability, control effectiveness, survivability, performance, and stealth. Thrust vector control systems following a variety of concepts have been considered for modern aircraft and missiles to enhance their military performance. Short Take-off and Landing (STOL) and control effectiveness at lower aircraft speeds can be achieved by employing Fluidic Thrust Vectoring Control (FTVC). This paper summarizes a range of ideas for FTVC that have been designed and tested both computationally and experimentally to determine the thrust vectoring performance of supersonic propulsion system nozzles. The conventional method of thrust vectoring involves mechanical means to deflect the direction of flow of the exhaust gases, whereas the most recent method involves fluidic-based thrust vectoring techniques. Fluid-based thrust vectoring has the advantages of simplicity and low weight over mechanical-based thrust vectoring, which has complex geometry and adds extra weight to the aircraft. The fluidic vectoring control nozzles are divided into seven categories: shock vector, bypass shock vector, counterflow, co-flow, throat skewing, dual throat, and bypass dual throat nozzle control. This paper provides a summary of each fluidic thrust vectoring technique with its characteristics, design, classification, and different operational criteria developed to date and compares the intrinsic characteristics of each technique. Based on the present literature, it is concluded that among all the fluidic control techniques, the bypass dual-throat nozzle control can achieve better thrust vectoring performance with large vector angles and low thrust loss.

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“…The primary flow then deflects through this shock wave, altering the vector angle and enhancing vector thrust. The effects of the NPR, secondary pressure ratio (SPR), and geometrical parameters on the performance of the SVC nozzle have been explored by a series of experiments and numerical studies [18][19][20][21][22][23][24][25][26][27]. The vector angle of an SVC nozzle increases monotonously in the absence of shock Due to its straightforward installation and implementation, the shock vector control (SVC) method is readily applicable in engineering practice [17].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of the Novel Two-Dimensional Enhanced Shock Vector Nozzle

Shu,

Gao,

Huang

et al. 2024

Aerospace

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Fluid thrust vectoring (FTV) control has obvious advantages in structural quality and stealth performance because of its fast response and light weight. However, improving FTV vector performance will cause a loss in engine performance due to the need to draw airflow from the engine. In order to alleviate the above problems and further improve the vector performance of FTV, a nozzle combined with throat skewing and shock vector control is proposed, and the secondary flow of the nozzle comes from the throat and is injected into the nozzle divergence section. The numerical results indicate that compared with the original configuration, the vector angle and vector efficiency of the new configuration are more linear with the nozzle pressure ratio (NPR), and the vector angle and vector efficiency are improved by 163% and 218%, respectively, while experiencing a maximum reduction in the thrust coefficient of 1.4%. Compared with the only bypass-type shock vector nozzle, the new configuration utilizes the diversion of the two jets to eliminate the reattachment of the separation bubble after the jet and its resulting abrupt change in vector performance, improving the performance while having good control characteristics. Additionally, a sensitivity analysis of the spacing between two jets is also carried out. The spacing between two jets should be increased to make the flow pass through two weaker shock waves to improve the vector performance while ensuring that the separation after the jet is no longer attached.

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Numerical investigation of injection angle effects on shock vector control performance

Cited by 8 publications

References 43 publications

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Aerodynamic Characteristics of the Novel Two-Dimensional Enhanced Shock Vector Nozzle

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