2018 Vol. 32, No. 5

Column of Research on Hypersonic Aerodynamics and Propulsion Integration Technology
Characteristics of the shock train motions caused by transverse injections into the isolator
Li Yiming, Li Zhufei, Yang Jiming, Wu Yingchuan
2018, 32(5): 1-6. doi: 10.11729/syltlx20180023
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Abstract:
Characteristics of the shock train motions in a two-dimensional inlet/isolator were investigated in a shock tunnel with a nominal Mach number of 6. The backpressure that supported the shock train was well controlled by using transverse injections into the isolator. High-speed schlieren and wall pressure measurements were carried out. Results show that the reflected shock waves in the inlet/isolator started flow form the background shock waves. As the transverse injections are opened, the downstream flow is accumulated with the increase of the backpressure and the induce of the shock train in the isolator. When the shock train moves upstream under the influence of the high backpressure, the shape and intensity of the leading shock in the shock train are changed by the background shock waves. Because strong adverse pressure gradients already exist near the incident points of the background shock waves, the leading shock of the shock train at the same side would be enhanced for moving upstream quickly. As the shock train is expelled out of the isolator, the leading shock oscillates near the shoulder for a short duration, until the backpressure is increased further to initiate the inlet buzz. When the backpressure is reduced by switching off the transverse injections, the inlet restarts.
Experimental study of the effects of heating methods on combustion characteristics in a supersonic combustor
Song Wenyan, Wang Yanhua
2018, 32(5): 7-12. doi: 10.11729/syltlx20180014
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Abstract:
Aiming to study the effects of vitiation species on combustion characteristics, comparative tests are conducted in a kerosene fueled supersonic combustor using an electrical heating facility and a methane combustion heating facility. For both clean and vitiated air, the total pressure and total temperature of the combustor entrance in every test are fixed at 820 kPa and 840K, and the Mach number is about 2.0. In comparative tests, combustion luminosities images are obtained using a high speed camera. Based on these images, the kerosene combustion flame-spreading angles are acquired. Experimental results indicate that, compared with the clean air, the combustor peak wall pressure decreases by 3.1%~6.9% with the methane combustion heated airflow, and the flame spreading angle decreases by 7.1%~12.4%.
Research on the force measuring system of hypersonic vehicle in the impulse wind tunnel
Zhang Xiaoqing, Wang Qi, Liu Weixiong, Lyu Jinzhou
2018, 32(5): 13-18. doi: 10.11729/syltlx20180029
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Abstract:
Strong coupling is the salient feature of the hypersonic airbreathing vehicle. Currently the most important research method is the powered experiment of the full system vehicle in impulse combustion wind-tunnel. Firstly, based on the characteristics of the impulse wind tunnel, a fast measurement method of an integrated vehicle wind-tunnel experiment was developed in this paper. The dynamic equation of the force measurement system consisting of the test model and the balance was derived and a structural designation rule was obtained by analyzing the equation. Then, the mode analysis of the force measurement system was conducted through the simulation and the hammering test, and also the vibration signal was monitored by the acceleration sensor. The results show that the frequency of the model system meets the request of the force measurement and the vibration shape is in consistent with hammering test mode. Finally, the impulse combustion wind-tunnel experiment of the powered vehicle was carried out and the result proves that the designed model could meet the request of the impulse combustion wind-tunnel and could acquire the accurate aerodynamic load of the large-scale hypersonic integrated vehicle. All the above investigation proves that it is practical to do the research of the large-scale hypersonic integrated vehicle in the impulse combustion wind-tunnel.
Compared study of performances of combined cycle engines
Song Wenyan, Zhang Dongqing, Lyu Chongyang
2018, 32(5): 19-28. doi: 10.11729/syltlx20180020
Abstract(605) HTML (244) PDF(42)
Abstract:
Performances of different combined cycle engine concepts, including Turbine/Ramjet/Dual-mode Scramjet (TE/RJ/DMSJ), Turbine/Ejector Ramjet/Dual-mode Scramjet(TE/ERJ/DMSJ), Pre-cooled Turbine/Dual-mode Scramjet (PCTE/DMSJ) and Air-turbo-rocket/Dual-mode Scramjet (ATR/DMSJ), are studied. The altitude-velocity characteristics of the combined cycle engines are obtained. Based on the same mission and aerodynamic characteristics of a hypersonic vehicle capable of Ma 6.5 cruise, the range, cruise distance and acceleration time are calculated of the vehicle by using the different combined cycle engines. The results indicate that the TE/RJ/DMSJ has the highest specific impulse among the four kinds of engines. The vehicle has the longest range and acceleration time by using TE/RJ/DMSJ under the same thrust loading and wing loading and it has the shortest range and acceleration time by using ATR/DMSJ.
Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft
Xu Xiaobin, Shu Haifeng, Xie Fei, Wang Xiong, Guo Leitao
2018, 32(5): 29-40. doi: 10.11729/syltlx20180053
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Abstract:
To get accurate wind tunnel test results with high precision for the airframe/propulsion integrated air-breathing hypersonic flight vehicles, reliable wind tunnel test techniques must be developed according to the vehicle's special configuration and structure. To satisfy the requirements of hypersonic wind tunnel tests for those airframe/propulsion integrated vehicles, the flow-through model aerodynamic force measurement technique, rear-jet interference test technique, hinge-moment measurement technique, flow-through model dynamic derivative test technique, and the surface skin-friction measurement technique have been developed in hypersonic wind tunnels of CARDC(China Aerodynamics Research and Development Center), which give massive support to those efforts to get authentic hypersonic wind tunnel test results for the design and evaluation of airframe/propulsion integrated air-breathing hypersonic flight vehicles.
Fundamental Research and Application
Study on the influence of incentive parameters on plasma-enhanced jet mixing
Li Liang, Li Xiuqian, Che Xueke, Zheng Tikai, Li Jinlong, Nie Wansheng
2018, 32(5): 41-47. doi: 10.11729/syltlx20180031
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Abstract:
In order to improve the mixing efficiency of rocket engine propellant and to explore the influence of plasma on the mixing characteristics of single rectangular jet, a plasma jet generation and control system is designed. Particle image velocimetry is used to measure the influence of surface dielectric barrier discharge plasma actuator on single jet mixing. Compared with non-excitation condition, when the excitation voltage is 5, 6 and 7kV, the width and mixing characteristics of jet are enhanced with the increase of voltage, and the maximum attenuation rate of jet centerline speed increases by about 20%; the jet decays and its width increases obviously while the pulse frequency increases; when the excitation voltage and the pulse frequency are fixed and the duty cycle is changed, the width of jet is the largest in the range of 50%~70%, where the decay effect is the strongest.
Numerical simulation and experimental study on the thermal characteristics of composite phase change materials for heat storage
Xiao Guangming, Du Yanxia, Liu Lei, Wei Dong, Yang Xiaofeng, Gui Yewei
2018, 32(5): 48-53. doi: 10.11729/syltlx20170175
Abstract(164) HTML (69) PDF(14)
Abstract:
The composite phase change material (PCM) is a new type of phase change material with the high porosity foam as a thermal conductivity enhancer. It has lots of excellent performances including large amount of latent heat and higher thermal conductivity than pure PCM, which make the device with composite PCM for heat storage to be an efficient thermal management technique for the next generation aircraft. The thermal characteristics of SiC foam filled paraffin waxes were studied in this paper. To simulate the heat transfer of composite PCM, a finite volume technique was used to discretize the heat diffusion equation, and the two-temperature model was employed for the small scale material while the equivalent specific heat method was used for the large scale material. The experimental setup was build up and heat transfer experiments were performed to validate the proposed numerical method. The experimental and numerical results show good agreement, which indicates the effectiveness of the proposed numerical model in this work. Based on the numerical method, the effects of the porosity on the equivalent thermal conductivity, and the effects of the microstructure on the equivalent thermal conductivity could be studied in further work.
Numerical simulation of support interference and distortion effect on flying wing in low speed wind tunnel
Liu Litao, Jin Ling, Zhu Minghong, Li Shiwei, Jiang Kelin
2018, 32(5): 54-60. doi: 10.11729/syltlx20180018
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Abstract:
The flying wing configuration shows high aerodynamic efficiency and nice stealth performance. It represents the future military and civil aircraft development direction. The support interference and local shape deformation effect in the wind tunnel test are extremely complex. There are no general support program and correction method for the flying wing configuration test in the wind tunnel. This paper calculated the sting interference and after-body deformation effect on a calibration model of the small aspect ratio flying wing by numerical simulation method. By comparing with the test results, the numerical simulation results are found to be reasonable and the method is proved to be reliable. This method can be used in support program evaluation and support interference correction for the wind tunnel test. The longitudinal components of force or moment of the sting interference and after-body deformation effect are small compared to the longitudinal components themselves. The lateral-directional components of force or moment of the sting interference can be ignored. The lateral-directional components of force or moment of the after-body deformation effect and the lateral-directional components themselves are of the same order of magnitude.
Experimental study on drag reduction and anti-shearing characteristics of xanthan gum solution with NaCl
Zhu Bo, Zhao Wenbin, Li Mingyi, Yuan Yichao, Yu Wenhui, Li Changfeng
2018, 32(5): 61-66. doi: 10.11729/syltlx20180035
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Abstract:
Experimental study on the drag reduction and the anti-shearing characteristics of xanthan gum(XG) solution with NaCl addition in smooth pipes with diameter of 20mm was conducted. For different mass fractions of XG solution with NaCl addition(XG/NaCl solution), the relationships of the drag reduction efficiency with the flow Reynolds number and the shearing duration time were obtained and compared with the drag reduction and anti-shearing characteristics of XG solution. The results show that the drag reduction percentage of XG/NaCl solution tends to stabilize rapidly with increasing Reynolds number, and it is lower than that of the XG aqueous solution in the low Reynolds number regime, but significantly higher than that of XG aqueous solution in high Reynolds number regime. There exists a best ratio of XG to NaCl for the drag reduction. The XG/NaCl solution has good temperature resistance. In the process of continuous shearing of pump, different mass fractions of XG/NaCl solution all have high resistance to the mechanical degradation.
Measuring Technique
Vision measurement technology of model poses with high accuracy on the 200m free flight ballistic range
Huang Jie, Ke Fawei, Xie Aimin, Li Xin, Song Qiang, Wang Zonghao, Wen Xuezhong, Liu Sen
2018, 32(5): 67-75. doi: 10.11729/syltlx20170139
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Abstract:
In order to obtain the changes of model poses flying at hypervelocity accurately on the free flight ballistic range which was used for identifying the aerodynamic parameters, China Aerodynamics Research and Development Center (CARDC) developed the vision measurement technology of model poses, which combined the mature technologies of the binocular vision location and the front light photo. The binocular measurement stations were installed along the flying direction of model, which would be calibrated and correlated to the same base coordinate before model test. When the model with coded feature points on its surface entered the measurement field, it would be illuminated by the extended laser light beam with the pulse width of smaller than 10ns, meanwhile, the two front light images were obtained by the cameras of the binocular measurement station, then the model poses were obtained by identifying and calculating the coded feature points on its surface. Based on solving the key technologies of filtering the parasitic light in the chamber, homogenizing the exit facular of the front light source, correlating binocular measurement stations to the same base coordinate, dealing the model surface color and fabricating feature points, the vision measurement system of poses with high accuracy on the 200m free flight ballistic range was accomplished. The test on the 20° cone with the length of 165 mm was carried out on the ballistic range, which flew in the chamber with the pressure of 15kPa at the velocity of about 2.7km/s. According to the cone poses at different binocular measurement stations and the sequence time of lasers flashing obtained by the vision measurement system, the drag index and the dynamic derivative of the cone were obtained by identifying, the trends of which were basically in consistency with those of the AEDC G range.
Skin friction measurements using oil film interferometry and Preston tube at subsonic/transonic regime
Liu Zhiyong, Li Jianqiang, Gao Rongzhao, Tao Yang, Liang Jinmin, Zhang Changfeng
2018, 32(5): 76-81. doi: 10.11729/syltlx20180032
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Abstract:
Measurements of skin friction on a flat plate model were conducted in the 0.6m×0.6m subsonic/transonic/supersonic wind tunnel. Oil film interferometry (OFI) and Preston tube technique were applied to obtain the skin friction data at Ma=0.4~0.8. In order to avoid flow separation, an elliptical leading edge was employed. Results indicate that the agreement between OFI and Preston tube is very well. Viscosity of oil film has little influence on the skin friction measurement. When the stream's Mach number or the total pressure changes, the skin friction coefficient decreases along with the increase of the dynamic pressure or the product of Mach number and Reynolds number (Ma·Re). A freckle-like interference pattern was observed at Ma=0.4 and 0.6, and an assumption based on the new pattern was proposed to determine the transition location. According to the oil motion and CFD results, a separation bubble rather than the new pattern appears at Ma=0.8, and it is responsible for the transition of boundary layer.
Experimental Equipment and Method
Measurements on compressor dynamic total pressure with dynamic correction of pneumatic probe
Chen Feng, Zong Youhai, Liu Dongjian, Ma Husheng, Du Wei
2018, 32(5): 82-88. doi: 10.11729/syltlx20180025
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Abstract:
The pressure signals at measurement points are extracted via pneumatic probes and restored by dynamic correction in order to obtain the multi-point dynamic total pressures in the compressor conveniently and safely. The discrete transfer function models are used to correct the measured signals and obtain the real pressures at the measurement points. These models are identified by the downward step input signals and probe response output signals generated by the burst balloon device. It is proved that the method is reliable for the signal dynamic correction within 1000Hz, the phase delay can be eliminated virtually and the tube resonance effect on the signal amplification can be reduced obviously after correction of the probe signal. The measurement results of dynamic total pressure in compressor show that the signal amplitude of blade passing frequency at rotor inlet increases gradually with the decrease of mass flow rate, meanwhile, the broadband disturbance intensity at stator outlet increases and reaches the maximum at the near rotating stall point. In addition, the spike-type rotating stall inception first appears near the tip of the rotor blade leading edge, then expands rapidly to the blade root and develops into a full-span rotating stall cell. The propagation speed of the fully developed stall cell is about 30% of the rotor rotating speed.
Study on calibration of FADS system for air-breathing air-to-air missile
Chen Guangqiang, Dou Xiuxin, Yang Yunjun, Zhou Weijiang, Dou Guohui
2018, 32(5): 89-95. doi: 10.11729/syltlx20170133
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Abstract:
Aiming at the independently developed FADS system of the air-breathing air-to-air missile, the calibration is carried out by FD-12 wind tunnel. The technical characteristics of the wind tunnel calibration test are analyzed. The wind tunnel calibration scheme is proposed to avoid the step shock wave by using the variable length pole, mainly including the pole design, machining and installation of the model and the air tightness detection of the pressure pipe. The second calibration is done in FD-12 wind tunnel.The experimental results show that:in the range of Mach number from 2.0~3.5, the measurement error of FADS system achieves the design goal:the error of the static pressure is less than 490Pa (less than 3%), the error of Ma is less than 0.1, and both errors of the angle of attack and the angle of side slip are less than 0.5°. Compared with the calibration at first time, the errors of the flow parameter measurements are all reduced, especially for the Ma2 status where the maximum relative error of the static pressure decreases from 11.5% to 3.0%, the maximum error of Ma decreases from 0.15 to 0.10, the maximum error of angle of attack decreases from 2.5° to 0.5°, and the maximum error of angle of side slip decreases from 1.2° to 0.5°. The research results can provide technical reference for the design of FADS system.