Performance of Control Jets on Curved Bodies in Supersonic Cross Flows

Grandhi, Raj Kiran; Roy, Arnab

doi:10.2514/1.a34314

Cited by 10 publications

(3 citation statements)

References 30 publications

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“…All walls were treated as adiabatic. The grid independence and basic flow field structure of lateral jets were studied in detail by Grandhi [25].…”

Section: Numerical Methods Validationmentioning

confidence: 99%

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Numerical Study on the Influence of Separation Time Sequence on the Initial Thermal Separation

Ma,

Wang,

2024

Energies

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The process of separating stages is crucial for multistage rockets, directly influencing the success of the launch plan. Different separation timing methods alter the flow field structure within the interlevel zone at separation, influencing the separation of the two-stage rockets. This paper employs the SST k-ω turbulence model to investigate the structure of the flow field and its aerodynamic and motion characteristics under different nozzle baffle opening and separation times, taking into account variable properties, supersonic compressibility, and the upstream–downstream interference. First, we examined the standard flow field structure, considering the engine jet, the lateral jet between stages, and the disturbance from the external supersonic inflow. Then, we discussed the displacement characteristics and axial force coefficient curves of the first and second steps of the separation process. Finally, we explored the impact of baffle opening and separation times on the flow field structure and axial force coefficients of the two stages at the onset of separation. For the flow field structure, a delay in the baffle opening and separation moment led to a gradual increase in downstream and separation regions until they stabilized after a certain range. However, the axial force coefficients displayed different behavior before and after the design point.

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“…All walls were treated as adiabatic. The grid independence and basic flow field structure of lateral jets were studied in detail by Grandhi [25].…”

Section: Numerical Methods Validationmentioning

confidence: 99%

“…The jet inlet is the pressure inlet. All walls were treated as a grid independence and basic flow field structure of lateral jets were studied Grandhi [25]. Figure 2 shows a comparison between actual data and numerical calculations of wall pressure distribution under different jet NPRs.…”

Section: Numerical Methods Validationmentioning

confidence: 99%

Numerical Study on the Influence of Separation Time Sequence on the Initial Thermal Separation

Ma,

Wang,

2024

Energies

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“…The coupling effect causes the force or moment to dramatically vary, resulting in the additional aerodynamic force [25]. Grandihi [26] investigated the effect of the jet difference between a flat plate and a rotating body on pressure distribution and control efficiency. The factors influencing jet control efficiency were investigated, and it was discovered that increasing the jet pressure ratio improves control efficiency [27].…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle

et al. 2023

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A new idea of nosebleed air jets with strong coupled internal and external flow is put forward using the lateral jet control principle to improve the maneuverability and fast reaction capabilities of hypersonic vehicles. The hypersonic vehicle’s nose stagnant high-pressure and high-temperature gas is utilized as the drive source for long-term jet control. The significant coupled jet interaction of the internal and external flow changes the aerodynamic characteristics. As a result, the structure is basic and does not rely on any external source to achieve flight attitude control. The complicated flow characteristics of the nosebleed jet in supersonic crossflow surrounding the vehicle were numerically and experimentally investigated. The jet interaction characteristics and the aerodynamic characteristic changes generated by the nosebleed air jet are verified by comparing the flow field with and without the jet. Results indicate that the nosebleed air jet alters the center-of-pressure coefficient, which is subsequently coupled with the interference aerodynamic force. This results in a variation in pitch moment. The jet decreases the pitching moment coefficient when compared with the case without a jet. It is probable that combining nosebleed air jets with model centroid adjustment yields an optimal trim angle of attack.

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Numerical investigation of vented plume into a supersonic flow in the early stage of rocket hot separation

Chen

Cai

et al. 2020

Aerospace Science and Technology

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Performance of Control Jets on Curved Bodies in Supersonic Cross Flows

Cited by 10 publications

References 30 publications

Numerical Study on the Influence of Separation Time Sequence on the Initial Thermal Separation

Numerical Study on the Influence of Separation Time Sequence on the Initial Thermal Separation

Numerical and Experimental Investigation on Nosebleed Air Jet Control for Hypersonic Vehicle

Numerical investigation of vented plume into a supersonic flow in the early stage of rocket hot separation

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