Experimental Investigation on the Influence of Yaw Angle on the Inlet Performance at Mach 7

Hohn, Oliver M.; Gülhan, Ali; Höhe, Linder

doi:10.2514/6.2010-938

Cited by 12 publications

(17 citation statements)

References 8 publications

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“…It should be noted here, that this can impact the results, as previous investigations showed that hysteresis effects can influence the results [49]. As Figure 17 shows, the total pressure losses are strongly increased by the angle of yaw, as the sidewall shock on the luv-ward side becomes much stronger.…”

Section: Angle Of Yawmentioning

confidence: 79%

“…For the vertical profiles, accuracy is much lower, as the pressure values have to be interpolated between the nearest pressure probes. Assuming a 10% variation of the static pressure at a Pitot tube from the interpolated value, it gives an accuracy of around ±6% for the Mach number determination [49]. For those experiments, where an angle of yaw was applied, the flowfield naturally is not symmetrical anymore, and the pressures had to be interpolated for the horizontal profiles as well, with the consequent reduced accuracy.…”

Section: A Pressure Measurements and Calculation Of Mach-numbermentioning

confidence: 99%

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Analysis of a Three-Dimensional, High Pressure Ratio Scramjet Inlet with Variable Internal Contraction

Hohn¹,

Gülhan²

2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

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We conducted an extensive experimental examination of the operational behavior of a three-dimensional scramjet inlet featuring a movable cowl to adapt the internal contraction according to the respective operation conditions. The experiments were conducted in the H2K wind tunnel of the DLR Cologne at Mach 7. The parameters investigated include different flight path angles (both angle of attack and angle of yaw), internal contraction ratio and Reynolds number. The critical internal contraction for inlet starting was found to agree well with common relations for starting of 3D-inlets. With increasing internal contraction, the inlet performance was found to improve and the inlet operated more stable. It was successfully tested for angles of attack up to ± 6° and angles of yaw up to 6°. Reynolds-Number had rather small effects on the performance and starting behavior of the inlet. Infraredthermography also gave some insight into the flow structure in the external part of the inlet.

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Section: Angle Of Yawmentioning

confidence: 79%

Section: A Pressure Measurements and Calculation Of Mach-numbermentioning

confidence: 99%

Analysis of a Three-Dimensional, High Pressure Ratio Scramjet Inlet with Variable Internal Contraction

Hohn¹,

Gülhan²

2012

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

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“…The summaries of calculative results for GK01 model are displayed in Figure 1, where the experimental data is chosen from Hohn and Gulhan. 26 The comparison results between five turbulence models can be seen in Figure 1 The grid sensitivity has also been performed. Here, the turbulence model was specified as the SST k-o model which has been proved that it can predict the flowfield with high accuracy.…”

Section: Numerical Simulation Methodsmentioning

confidence: 99%

“…1,[10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26] Liou and Benson 18 presented optimization results of bleeding system for supersonic inlet. Chang and Fan 19 studied the effect of the bleeding on the unstart/restart characteristics, and the effects of bleeding on the performance parameter was taken into consideration as well.…”

Section: Introductionmentioning

confidence: 99%

Comparison research of two different improved methods in the 2D hypersonic inlet’s design

Yang

Luo

Huang

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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The article mainly employed the numerical simulation method to conduct the 2D hypersonic inlet performance research. In this study, the numerical simulation method that includes a two-equation turbulence model was validated through the test case firstly. For the purpose of oppressing unstart phenomena, extending operating range and improving comprehensive performance of the inlet, the bleeding system and isentropic expansion arc surface were applied to the inlet, respectively. Different kinds of configurations were designed through changing the length of the bleeding or changing the radius of the arc surface. The influence of the bleeding and isentropic expansion arc surface on the 2D hypersonic inlet was analyzed systematically based on different objective parameters. The calculative results show that the bleeding system with appropriate value of the length can improve comprehensive performance of hypersonic inlet remarkably either on the design point or the off-design points, though it has a very small negative impact on the inlet in terms of the mass flow ratio coefficient. As for isentropic expansion arc surface, it can improve the inlet's performance at the design point on the conditions that the radius of isentropic expansion arc surface has an appropriate value. But it has much more disadvantages over the basic configuration reversely when it comes to the off-design conditions or the large size of the radius of isentropic expansion arc surface.

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“…Only in a few studies the pressure and heat transfer coefficient distributions within an air-inlet were investigated [6,8,14,21]. Some additional possibilities for studying the heat transfer and the flow structure within an air-inlet appeared thanks to the application of panoramic investigation methods based on the use of luminescent coatings and transparent air-inlet walls.…”

mentioning

confidence: 99%

Leading edge bluntness effect on the flow in a model air-inlet

et al. 2014

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Flow in an idealized air-inlet with plane walls and a rectangular cross-section is experimentally investigated. The air-inlet is mounted on a plate, at a distance well removed from its leading edge. The experiments were conducted in a Ludwig tube at M ∞ = 5 and Re ∞L = 23 × 10 6 and 13 × 10 6 . A panoramic (optical) technique of measuring the heat transfer coefficient is for the first time applied to study the internal flow in an air-inlet. The data on the effect of the bluntness of the leading edges of the plate and the air-inlet cowl on the heat transfer coefficient distribution and the flow structure within the air-inlet are obtained. It is shown that in an air-inlet with large channel constriction an even small bluntness of the plate or the cowl can lead to global changes in the flow structure.

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Experimental Investigation on the Influence of Yaw Angle on the Inlet Performance at Mach 7

Cited by 12 publications

References 8 publications

Analysis of a Three-Dimensional, High Pressure Ratio Scramjet Inlet with Variable Internal Contraction

Analysis of a Three-Dimensional, High Pressure Ratio Scramjet Inlet with Variable Internal Contraction

Comparison research of two different improved methods in the 2D hypersonic inlet’s design

Leading edge bluntness effect on the flow in a model air-inlet

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