Dual Injection in Supersonic Crossflow: Analysis Jet Shear Layer from Schlieren Images

Jan Siemen Smink; Harry W.M. Hoeijmakers; Cornelis H. Venner

doi:10.2514/1.J061843

Dual Injection in Supersonic Crossflow: Analysis Jet Shear Layer from Schlieren Images

Jan Siemen Smink, Harry W.M. Hoeijmakers, Cornelis H. Venner

Engineering Fluid Dynamics

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Abstract

In supersonic-combustion ramjets (scramjets), fuel is injected, which should mix rapidly with the supersonic crossflow to minimize the length of the scramjet. Tandem dual-jet injection has shown improved mixing performance over single-jet injection. However, experiments on tandem dual-jet injection have not addressed the jet shear layer, in which the mixing occurs, yet. The present study investigates the jet shear layer, as well as the bow shocks in front of the jets, in a continuous air-indraft supersonic wind tunnel at Mach number 1.55. A schlieren setup has been used for visualizing the flow features. A largely automated algorithm for processing schlieren images has been developed to determine the location of the upper boundary of the jet shear layer. The penetration of the jet is studied as a function of 1) J, the ratio of the momentum of the jet and that of the crossflow, and 2) the dimensionless distance S between the dual-jets. An empirical similarity relation has been established for the time-averaged location of the jet upper shear layer as function of J and S, covering the investigated conditions (J ∈ 2.8;3.8;4.8, S ∈ 0∶9.87). This empirical similarity relation provides S_opt, the spacing for maximal penetration of the jets as function of J.

Original language	English
Pages (from-to)	6277-6288
Number of pages	12
Journal	AIAA journal
Volume	60
Issue number	11
Early online date	9 Sept 2022
DOIs	https://doi.org/10.2514/1.J061843
Publication status	Published - Nov 2022

Keywords

22/3 OA procedure

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10.2514/1.J061843

ArticleFinal published version, 11.5 MBLicence: Taverne

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title = "Dual Injection in Supersonic Crossflow: Analysis Jet Shear Layer from Schlieren Images",

abstract = "In supersonic-combustion ramjets (scramjets), fuel is injected, which should mix rapidly with the supersonic crossflow to minimize the length of the scramjet. Tandem dual-jet injection has shown improved mixing performance over single-jet injection. However, experiments on tandem dual-jet injection have not addressed the jet shear layer, in which the mixing occurs, yet. The present study investigates the jet shear layer, as well as the bow shocks in front of the jets, in a continuous air-indraft supersonic wind tunnel at Mach number 1.55. A schlieren setup has been used for visualizing the flow features. A largely automated algorithm for processing schlieren images has been developed to determine the location of the upper boundary of the jet shear layer. The penetration of the jet is studied as a function of 1) J, the ratio of the momentum of the jet and that of the crossflow, and 2) the dimensionless distance S between the dual-jets. An empirical similarity relation has been established for the time-averaged location of the jet upper shear layer as function of J and S, covering the investigated conditions (J ∈ 2.8;3.8;4.8, S ∈ 0∶9.87). This empirical similarity relation provides Sopt, the spacing for maximal penetration of the jets as function of J.",

keywords = "22/3 OA procedure",

author = "Smink, \{Jan Siemen\} and Hoeijmakers, \{Harry W.M.\} and Venner, \{Cornelis H.\}",

note = "Funding Information: The authors would like to thank W. Lette for his technical support with the experimental setup and during the measurements. Also, the authors are grateful for the Vertical-Cavity-Surface-Emitting Laser light source manufactured by F.B. Segerink from the Optical Sciences group at the University of Twente. Publisher Copyright: {\textcopyright} 2022 by the authors.",

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T2 - Analysis Jet Shear Layer from Schlieren Images

AU - Smink, Jan Siemen

AU - Hoeijmakers, Harry W.M.

AU - Venner, Cornelis H.

N1 - Funding Information: The authors would like to thank W. Lette for his technical support with the experimental setup and during the measurements. Also, the authors are grateful for the Vertical-Cavity-Surface-Emitting Laser light source manufactured by F.B. Segerink from the Optical Sciences group at the University of Twente. Publisher Copyright: © 2022 by the authors.

PY - 2022/11

Y1 - 2022/11

N2 - In supersonic-combustion ramjets (scramjets), fuel is injected, which should mix rapidly with the supersonic crossflow to minimize the length of the scramjet. Tandem dual-jet injection has shown improved mixing performance over single-jet injection. However, experiments on tandem dual-jet injection have not addressed the jet shear layer, in which the mixing occurs, yet. The present study investigates the jet shear layer, as well as the bow shocks in front of the jets, in a continuous air-indraft supersonic wind tunnel at Mach number 1.55. A schlieren setup has been used for visualizing the flow features. A largely automated algorithm for processing schlieren images has been developed to determine the location of the upper boundary of the jet shear layer. The penetration of the jet is studied as a function of 1) J, the ratio of the momentum of the jet and that of the crossflow, and 2) the dimensionless distance S between the dual-jets. An empirical similarity relation has been established for the time-averaged location of the jet upper shear layer as function of J and S, covering the investigated conditions (J ∈ 2.8;3.8;4.8, S ∈ 0∶9.87). This empirical similarity relation provides Sopt, the spacing for maximal penetration of the jets as function of J.

AB - In supersonic-combustion ramjets (scramjets), fuel is injected, which should mix rapidly with the supersonic crossflow to minimize the length of the scramjet. Tandem dual-jet injection has shown improved mixing performance over single-jet injection. However, experiments on tandem dual-jet injection have not addressed the jet shear layer, in which the mixing occurs, yet. The present study investigates the jet shear layer, as well as the bow shocks in front of the jets, in a continuous air-indraft supersonic wind tunnel at Mach number 1.55. A schlieren setup has been used for visualizing the flow features. A largely automated algorithm for processing schlieren images has been developed to determine the location of the upper boundary of the jet shear layer. The penetration of the jet is studied as a function of 1) J, the ratio of the momentum of the jet and that of the crossflow, and 2) the dimensionless distance S between the dual-jets. An empirical similarity relation has been established for the time-averaged location of the jet upper shear layer as function of J and S, covering the investigated conditions (J ∈ 2.8;3.8;4.8, S ∈ 0∶9.87). This empirical similarity relation provides Sopt, the spacing for maximal penetration of the jets as function of J.

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Dual Injection in Supersonic Crossflow: Analysis Jet Shear Layer from Schlieren Images

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