LAPSE:2020.0353
Published Article
LAPSE:2020.0353
Effects of Wall Ventilation on the Shock-wave/Viscous-Layer Interactions in a Mach 2.2 Intake
Humrutha Gunasekaran, Thillaikumar Thangaraj, Tamal Jana, Mrinal Kaushik
April 14, 2020
In order to achieve proficient combustion with the present technologies, the flow through an aircraft intake operating at supersonic and hypersonic Mach numbers must be decelerated to a low-subsonic level before entering the combustion chamber. High-speed intakes are generally designed to act as a flow compressor even in the absence of mechanical compressors. The reduction in flow velocity is essentially achieved by generating a series of oblique as well as normal shock waves in the external ramp region and also in the internal isolator region of the intake. Thus, these intakes are also referred to as mixed-compression intakes. Nevertheless, the benefits of shock-generated compression do not arise independently but with enormous losses because of the shockwave and boundary layer interactions (SBLIs). These interactions should be manipulated to minimize or alleviate the losses. In the present investigation a wall ventilation using a new cavity configuration (having a cross-section similar to a truncated rectangle with the top wall covered by a thin perforated surface is deployed underneath the cowl-shock impinging point of the Mach 2.2 mixed-compression intake. The intake is tested for four different contraction ratios of 1.16, 1.19, 1.22, and 1.25, with emphasis on the effect of porosity, which is varied at 10.6%, 15.7%, 18.8%, and 22.5%. The introduction of porosity on the surface covering the cavity has been proved to be beneficial in decreasing the wall static pressure substantially as compared to the plain intake. A maximum of approximately 24.2% in the reduction in pressure at the upstream proximal location of 0.48 L is achieved in the case of the wall-ventilated intake with 18.8% porosity, at the contraction ratio of 1.19. The Schlieren density field images confirm the efficacy of the 18.8% ventilation in stretching the shock trains and in decreasing the separation length. At the contraction ratios of 1.19, 1.22, and 1.25 (‘dual-mode’ contraction ratios), the controlled intakes with higher porosity reduce the pressure gradients across the shockwaves and thereby yields an ‘intake-start’ condition. However, for the uncontrolled intake, the ‘unstart’ condition emerges due to the formation of a normal shock at the cowl lip. Additionally, the cowl shock in the ‘unstart’ intake is shifted upstream because of higher downstream pressure.
Keywords
boundary layer, cavity, porosity, Schlieren flow visualization technique, shock wave, static pressure, wall ventilation
Subject
Suggested Citation
Gunasekaran H, Thangaraj T, Jana T, Kaushik M. Effects of Wall Ventilation on the Shock-wave/Viscous-Layer Interactions in a Mach 2.2 Intake. (2020). LAPSE:2020.0353
Author Affiliations
Gunasekaran H: Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur 721302, India
Thangaraj T: Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur 721302, India
Jana T: Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur 721302, India
Kaushik M: Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur 721302, India [ORCID]
Journal Name
Processes
Volume
8
Issue
2
Article Number
E208
Year
2020
Publication Date
2020-02-08
Published Version
ISSN
2227-9717
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PII: pr8020208, Publication Type: Journal Article
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LAPSE:2020.0353
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doi:10.3390/pr8020208
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Apr 14, 2020
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