Effects of Ridge Configuration on the Performance of Integrated inlets

Gouping, Huang; Saheby, Eiman B.; Akhlaghi, Mahdi; Zhang, Yu

doi:10.2514/6.2016-4608

Cited by 3 publications

(2 citation statements)

References 5 publications

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“…In the previous study [12], the diffuser duct had higher curvature that resulted in some local flow separations after the bend when the inlet was integrated (or reinforced) with the ridge. Such a pattern was experienced when the Mach number exceeded 0.50.…”

Section: International Journal Of Aerospace Engineeringmentioning

confidence: 90%

Propulsive Efficiency of Ridge/Inlet Configuration

Huang

Saheby

Hays

2018

International Journal of Aerospace Engineering

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Controlling and directing the boundary layer on the surfaces of a flight vehicle are two of the most demanding challenges in advanced aerodynamic designs. The design of highly integrated and submerged inlets with a large offset between the entrance and compressor face is particularly challenging because of the need for controlling or reducing the adverse effects of the boundary layer on propulsive efficiency. S-duct diffusers are used widely in flight vehicles when the compressor face needs to be hidden, and their performance is generally sensitive to the quality of ingested boundary layer from the fuselage. Passive or active flow control mechanisms are needed to prevent flow separations at the bends. In this paper, a new method is presented for optimal inlet/body integration based on a pair of ridges ahead of the inlet and its effects on the performance of a semicircular S-duct inlet integrated on a flat surface using CFD. In this design, the ridge changes an inefficient inlet concept to one with acceptable performance. The new method of integration is practicable for top-mounted inlet configurations where the use of diverters and other mechanisms results in higher amounts of drag, weight, and complexity.

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Section: International Journal Of Aerospace Engineeringmentioning

confidence: 90%

Propulsive Efficiency of Ridge/Inlet Configuration

Huang

Saheby

Hays

2018

International Journal of Aerospace Engineering

Self Cite

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“…The submerged inlet uses a long inclined plate with a very small angle of inclination (about 7 • ) to introduce air into the inlet, but the intake volume of the inlet is small and the total pressure recovery coefficient is low [20][21][22][23][24][25]. Subsequently, a large number of researchers carried out in-depth research on the intake mechanism [26,27], optimization design method [28][29][30], internal flow characteristics [31][32][33], and flow control method [34][35][36][37] of the submerged inlet. Now the performance of the submerged inlet can basically meet the engineering application requirements.…”

Section: Introductionmentioning

confidence: 99%

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Zhang

2023

Applied Sciences

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Submerged inlet has been widely used in UAVs and cruise missiles due to its good stealth characteristics, but it also brings the disadvantage of poor aerodynamic characteristics. Especially in large maneuvering flight, the flow field near the fuselage has a strong unsteady effect, and the total pressure recovery coefficient and distortion characteristics have deteriorated sharply. In order to investigate the steady and transient aerodynamic characteristics of the submerged inlet in large maneuver flight and improve its maneuver envelope, a design scheme of a distributed submerged inlet for large maneuver flight is proposed in this paper. Taking a cruise missile as the research object, the steady and transient analysis of the conventional submerged inlet and the distributed submerged inlet is carried out using CFD numerical method. The results show that the distributed submerged inlet can significantly improve the inlet performance and enhance the sideslip limit of the submerged inlet during large sideslip maneuver flight. When the sideslip angle is 30°, compared with the conventional submerged inlet configuration, the outlet total pressure recovery coefficient of the distributed submerged inlet configuration is increased by 44.2%, and the total pressure distortion index is reduced by 66.3%.

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Study on Aerodynamic Design of the Front Auxiliary Inlet

Zhang

2023

Aerospace

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Submerged inlets have been widely used in advanced aircraft due to their excellent stealth characteristics, but they also suffer from poor aerodynamic performance. To improve the aerodynamic efficiency while maintaining stealth capabilities, this paper proposes a design scheme for a front auxiliary inlet with an inlet grille. The front auxiliary inlet is connected to the main inlet to form a composite inlet system. The low-energy upstream airflow that accumulates at the inlet is guided by the front auxiliary inlet to flow into the mainstream, resulting in a stable and high-quality airflow. A certain type of cruise missile was used as the research subject, and intake systems with and without front auxiliary inlets were constructed to compare the inlet performance of the two configurations using the CFD method. Additionally, a sensitivity analysis of the main design parameters of the front auxiliary inlet was carried out. The study reveals that a reasonable design of the front auxiliary inlet can prevent low-energy airflow, which accumulates on the missile body surface, from directly entering the inlet. Moreover, the front auxiliary inlet can inject additional mechanical energy into the low-energy airflow, inhibit airflow separation, and improve the uniformity of the flow field. Under cruise conditions, the total pressure recovery coefficient of the front auxiliary inlet configuration increased by 12.39% compared to the model without a front auxiliary inlet configuration. Furthermore, the total pressure distortion index was reduced by 47.24%.

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Effects of Ridge Configuration on the Performance of Integrated inlets

Cited by 3 publications

References 5 publications

Propulsive Efficiency of Ridge/Inlet Configuration

Propulsive Efficiency of Ridge/Inlet Configuration

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Study on Aerodynamic Design of the Front Auxiliary Inlet

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