Analysis on Transverse Secondary Injection Penetration Into Confined Supersonic Flow PDF Download
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Author: Jain-Ming Wu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 13
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Book Description
Author: Jain-Ming Wu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 13
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1000
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Book Description
Author: Mark P. Wilson
Publisher:
ISBN: 9781423583189
Category : Airplanes
Languages : en
Pages : 159
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Book Description
In pursuit of more efficient and effective fuel-air mixing for a SCRAMJET combustor, this study was conducted to investigate relative near field enhancements of penetration and mixing of a discrete low-angled (25 deg) injected air jet into a supersonic (M=2.9) cross flow. The enhancements were achieved by injecting the transverse air jet parallel to the compression face of eight different ramp geometries. The jet-ramp interactions created collinear shock structures, baroclinic torque vorticity enhancement, ramp spillage enhanced vorticity, magnus effect penetration enhancement, and increased total pressure loss. Shadowgraph photography was used to identify the shock structures and interactions in the flow field. Measurements of mean flow properties were used to establish the jet plume size, jet plume penetration and to quantify the total pressure loss created by the ramps. Rayleigh-Mie scattering images were used for both qualitative flow field assessments and quantitative analysis of the plume trajectory and mixing rate. Results indicate that up to a 20% increase in penetration height and plume expansion can be achieved by injection over a ramp compared to simple transverse injection. This increase in penetration and mixing incurs up to a 15% loss in total pressure. The most critical geometric aspects that affect the flow are the ramp compression face shape and frontal aspect, and the location and strength of ramp generated expansion.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Author: Kinya Aoyama
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
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Book Description
Author: Kenneth P. Horn
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
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The paper reports a study of normal and lateral spray penetration for small diameter, high pressure, liquid jets issuing at an angle to a uniform supersonic stream. The experimental program described was carried out in a 4-in. by 4-in. blow down supersonic wind tunnel. The flow field is observed by means of a schlieren system, and the spray distribution is indicated by the light scattered by the liquid droplets. The data on normal penetration, in good agreement with data inferred from other investigations, indicate that a single-parameter correlation exists between the properly nondimensionalized penetration height and the injection pressure ratio. Injecting the coolant at a forward angle to the flow produces no substantial change in the penetration height. The data on lateral penetration show the spray width behind the jet to be proportional to the jet diameter with only a weak dependence on the injection pressure ratio. Analytical models proposed by previous investigators are critically examined in light of the results. No single model leads to a proper scaling law for both normal and lateral penetration. (Author).
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 548
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Author: J. C. Hermanson
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 460
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Book Description
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 414
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