Experimental Investigation of the Internal Compression Inside a Hypersonic Intake

Herrmann, Carsten; Koschel, W.

doi:10.2514/6.2002-4130

Cited by 47 publications

(29 citation statements)

References 2 publications

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“…Depending on the combustionchamber static pressure, the flow structure in the isolator varies (Sugiyama et al [10]). For a scramjet compression setup with nonsymmetric inflow conditions to the isolator, the flow structure is visualized (i.e., by Hermann and Koschel [11] and Reinartz et al [12]) for different backpressures. These different structures are investigated and discussed in this paper by means of pitot pressure measurements and static pressure measurements, with the focus on the bleed effects.…”

mentioning

confidence: 99%

Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7

Häberle

Gülhan

2008

Journal of Propulsion and Power

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The current experimental study at Mach 7 was carried out to investigate the viscous flow effects in a scramjet inlet with a fixed geometry operating at Mach 7.5-8. To reduce the risk of inlet unstart, an optional passive boundarylayer bleed was integrated at the throat and tested for different bleed dimensions. The passive bleed significantly reduces the lip-shock-induced separation bubble on the ramp. But the correct location of the bleed gap is important for the reduction of the separation bubble. To investigate the compression behavior, different backpressures were applied and the effects on the internal flow structure were analyzed by means of static pressure along the isolator and pitot pressure profiles at the exit of the isolator. Because the reference configuration has a very small internal contraction ratio to guarantee self-starting, the internal compression ratio was increased in three steps by means of additional sidewall compression along the internal flowpath. This includes internal contraction ratios above the starting limit. This measure led to a significant increase of the static pressure ratio at the end of the isolator. The complex flow structures are explained by means of detailed static and pitot pressure plots. Nomenclature= mass flow, kgs 1 p = pressure, Nm 2 q = dynamic pressure, Nm 2 R = specific gas constant for air 287.15, Jkg 1 K 1 Re = Reynolds number T = temperature, K = calibration value = throttle degree, 1 A mfm;th A 1 0 100% = density, kgm 3 = total pressure recovery Subscripts CC = combustion chamber entry condition mfm = mass flow meter SW = sidewall compression inlays 1 and 2 th = throat t0 = wind-tunnel total conditions w = wall 0 = freestream plane ahead of the inlet 1 = wind-tunnel freestream conditions

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confidence: 99%

Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7

Häberle

Gülhan

2008

Journal of Propulsion and Power

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“…Comparison of a schlieren picture [14,21] without throttling and corresponding Mach number contour lines of the computation is shown in Fig. 3, and it reveals an overall good agreement.…”

Section: Numerical Accuracy Analysismentioning

confidence: 57%

Operation pattern classification of hypersonic inlets

Chang

Bao

et al. 2009

Acta Astronautica

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“…reference [12] reference [10] reference [11] result in this paper Figure 7 Comparison between our result and references Table 1. Parameters of the experimental table in reference [11] and ours parameters of experimental table reference [11] our experimental table It should be noticed that cold flow tunnel is used in reference [11] , but in reference [12] high enthalpy expanding tube is adopted(total enthalpy is 4MJ/kg and inflow mach number is 3.5), and in reference [10] , exit speed of transverse jet is supersonic, not sonic.…”

Section: Strobo Light Monochrome Schlierenmentioning

confidence: 99%

“…Parameters of the experimental table in reference [11] and ours parameters of experimental table reference [11] our experimental table It should be noticed that cold flow tunnel is used in reference [11] , but in reference [12] high enthalpy expanding tube is adopted(total enthalpy is 4MJ/kg and inflow mach number is 3.5), and in reference [10] , exit speed of transverse jet is supersonic, not sonic. Parameters of the experimental table in reference [11] and ours are shown in Table 1.…”

Section: Strobo Light Monochrome Schlierenmentioning

confidence: 99%

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Optical Display of Transverse Jet Flow Field Under Supersonic Inflow

Li¹,

Ye²,

Wang³

2017

MATEC Web Conf.

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Abstract. Optical display and measurement of transverse jet flow field under supersonic inflow is performed with continuous xenon lamp color schlieren, strobo light color schlieren and strobo light monochrome schlieren. Characteristic of fuel transverse jet in scramjet combustion chamber is studied. Results indicate that wave structure can be displayed through images obtained from long time exposure of schlieren, exposure time in dozens of nanoseconds is suitable for the display of turbulent structure, and comparing with color schlieren, amounts of information obtained from monochrome schlieren are few, whose sensitivity is much lower, either.

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Experimental Investigation of the Internal Compression Inside a Hypersonic Intake

Cited by 47 publications

References 2 publications

Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7

Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7

Operation pattern classification of hypersonic inlets

Optical Display of Transverse Jet Flow Field Under Supersonic Inflow

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