2019 Vol. 33, No. 2

Column of Research on Hypersonic Aerodynamics and Aerothermodynamics
Research progress of aerodynamic thermal environment test and measurement technology
Zhu Guangsheng, Nie Chunsheng, Cao Zhanwei, Yuan Ye
2019, 33(2): 1-10. doi: 10.11729/syltlx20180137
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Abstract:
Ground wind tunnel tests and flight tests are the primary means of obtaining pneumatic heating data. In this paper, the development of the domestic hypersonic aerodynamic test and the heat flux measurement technology is analyzed and discussed. Firstly, the shape characteristics, the flight profile, the boundary layer transition and the aerodynamic thermal environment characteristics of the adjacent space hypersonic vehicles are analyzed. On this basis, the wind tunnel test simulation theory of the aerodynamic thermal environment is analyzed, and the domestic application for aerodynamic thermal measurement, wind tunnel test equipment and its simulation capability are introduced, focusing on the analysis of the development and trend of wind tunnel aerodynamic thermal environment measurement technology, including point measurement technology based on sensor measurement and non-contact measurement technology such as phosphorescence heat map technology and infrared heat map technology. Finally, the measurement principle and engineering application of the "built-in" and "embedded" measure-ment technologies are introduced for the flight test thermal environment measurement. The problems faced by the flight test aerodynamic thermal environment measurement are discussed. Both further research and present problems for thermal environment measurement technologies are proposed.
Research on evolution of starting shock in a supersonic nozzle
Wang Chengpeng, Yang Jinfu, Cheng Chuan, Wang Wenshuo, Xu Pei, Yang Xin, Jiao Yun, Cheng Keming
2019, 33(2): 11-16. doi: 10.11729/syltlx20180143
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Abstract:
The starting process of the flow in a Mach 2.7 supersonic nozzle is experimentally investigated. The starting shock moves from the throat to the exit of the nozzle when the incoming total pressure is gradually increased. The flow in the nozzle undergoes the process of normal shock at the throat, normal shock at the expansion duct, oblique shock at the expansion duct, Mach reflection at the exit of the nozzle, regular reflection at the exit of the nozzle and the design conditions. The transformation from the Mach reflection to the regular reflection is observed based on the experimental result of schlieren and PIV. The three-dimensional flow structure of the leading shocks of the shock train has been rebuilt by using the schlieren image system and the shear-sensitive liquid crystal technology.
Study on fast/slow reaction mechanism of carbon-based material oxidation in high speed stream of dissociated air
Guo Yijun, Zhou Shuguang, Zeng Lei, Liu Xiao, Dai Guangyue, Qiu Bo
2019, 33(2): 17-22, 101. doi: 10.11729/syltlx20180128
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Abstract:
Based upon our previous research on the single/dual platforms theory for carbon-based material oxidation, it has been found that the generally accepted "slow" reaction model which was presented by Scala in 1962 and has been widely used till now for over fifty years does not exist, while the deserted "fast" reaction model really exists and is of great value in application. Theoretical analysis shows that the "slow" reaction appears only at the boundary-layer-diffusion-rate controlled regime, In this regime, the ablation rate has no business with the chemical reaction rates, so it is a fictitious reaction model and has no physical meanings, although the results from it may be in agreement well with test results. The products of the heterogeneous reactions of carbon with oxygen are CO and CO2, but CO2 is usually neglected when the surface temperature is higher than 1000K in many literatures. However, from theoretical analysis, author find that CO2 plays an important role in spanning the reaction range from the reaction-rate controlled regime to the diffusion controlled oxidation regime, and can't be ignored. It has been shown that for the ablation of carbon-based materials in a high speed stream of dissociated air, the "fast" reaction must be used with both products of CO2 and CO at the same time. There are two different platforms in the diffusion controlled regime. The first platform results from reactions of the predominant CO2 product, and the other is due to the predominant CO product reactions. With the increases of the surface temperature, the ratio of the mass fraction of CO to CO2 at the surface rises rapidly from zero to infinity, which causes the oxidation process to change automatically from the nominated "fast" reaction to the so called "slow" reaction lines. The dual platform theory has been confirmed by several experimental results.
Simulating hypersonic projectile launching process in the ballistic range by Adaptive Discontinuity Fitting solver technique
Chang Siyuan, Zou Dongyang, Liu Jun
2019, 33(2): 23-29. doi: 10.11729/syltlx20180104
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Abstract:
The free flight ballistic range is an important ground test method for the study of hypersonic vehicles. After the accelerated launch, the projectile is separated from the sabots in the range tank. The actual flying posture of the projectile is affected by many factors occurring in the processes of model acceleration and separation. Therefore, it is helpful to operate the experiment by developing simulation techniques for ballistic range tests. Considering the above processes, a set of numerical simulation algorithms is built. More specifically, the unstructured dynamic grid technique and Adaptive Discontinuity Fitting solver(ADFs) are used to track the motion of the projectile and sabots, and the cell-centered finite volume method is utilized to update the flow field.
Fundamental Research and Application
The statistics of velocity and temperature fluctuations in axisymmetric laminar-to-turbulent transitions
Zhang Ruoling, Le Jialing
2019, 33(2): 30-42. doi: 10.11729/syltlx20180117
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Abstract:
The procedures for studying continuous phase transitions of thermodynamic equilibrium systems are extended to discuss the laminar-to-turbulent transitional flows in circular tubes. The flow in the transition range is treated as a composition of the laminar and turbulent flows assuming that the radial fluctuating velocity has the same value as that of the fully turbulent flow. The composite ratio of the turbulent flow is used as an order parameter to define the composite flow. The fluctuations of the composite ratios are introduced, and the criterion of minimum entropy production is used to derive an equation which can describe the transition behaviors. The convective heat transfer characteristics in the transition range in a heated circular tube are also discussed adopting the same procedures. Similar and separate processes for the transitions of the flow and convective heat transfer types are allowed in the heated circular tube. The macroscopic fluctuations in the transition range show both probabilistic and deterministic characteristics simultaneously. The agreements with measurements are given including those obtained in flow and heat transfer experiments.
Effects of end condition on aerodynamic force distribution on a skewed circular cylinder
Ma Wenyong, Wang Guanya, Zheng Xi, Chen Tie, Li Zhi, Zhang Chengyuan, Fang Pingzhi
2019, 33(2): 43-50. doi: 10.11729/syltlx20180050
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Abstract:
The change of the end conditions has significant influences on the aerodynamic forces when a finite length cylinder is tested in the wind tunnel for its aerodynamic forces. In the present study, the characteristics of aerodynamic forces on an oblique cylinder with various end conditions at Reynolds number of 6.43×104 are studied through a rigid model pressure test in a wind tunnel. Using the wind pressure distribution along the length of the cylinder, the effects of end conditions on aerodynamic forces on the oblique circular cylinder are revealed. The results show that the wind pressure on the oblique cylinder could be classified into three states along the length of the cylinder, that the state near the upstream end plate, the state at the middle and the state near the downstream end plate. The wind pressure on the leeward near upstream end plate has a significant variation (convex) due to the existence of the horseshoe vortex. The existence of the end plates significantly influences the strength of the horseshoe vortex. At the middle state, the wind pressure on the leeward varies alternately along the length, which is probably induced by the motion of the horseshoe vortex through the axial flow. The end conditions also influence the amplitude of the alternative wind pressure at the leeward and the local drag coefficient on the cylinder. Near the downstream end plate state, wind pressure on the windward and leeward varies sharply when the downstream end plate is closed. The downstream end plate has a more significant influence on the wind pressure distribution at the windward than at the leeward.
Schlieren visualization of hypersonic boundary layer transition on a circular cone
Chen Suyu, Chang Yu, Li Qiang, Jiang Tao, Zhang Kouli
2019, 33(2): 51-56. doi: 10.11729/syltlx20180061
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Abstract:
To develop the experimental technique for investigating the hypersonic boundary layer transition, schlieren visualization is used to study the characteristics of the boundary layer transition in the FD-14 shock tunnel at the Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center(CARDC). The test model is a 7° half-angle blunt cone with two different nosetip radiuses, 2.0 and 0.5mm, respectively. The nominal Mach numbers are 8 and 10 and the unit Renolds number varies from 1.6×107 to 4.4×107 m-1. The high-speed camera's frame frequency is 20kHz. Structures of the second mode instability waves and turbulent spots are obtained by schlieren visualization and the power spectral density is analyzed based on the gray scale distribution of schlieren images. Results indicate that the wavelength of the second mode wave is nearly twice as large as the boundary layer thickness. Analysis results of the schlieren image sequence show that the propagation speed of the turbulent spot front is higher than that of the turbulent spot tail, and is slightly higher than the velocity of the boundary layer outer edge.
Measuring Technique
High resolution volumetric light field particle image velocimetry with dual plenoptic cameras
Mei Di, Ding Junfei, Shi Shengxian
2019, 33(2): 57-65. doi: 10.11729/syltlx20180165
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Abstract:
Light field particle image velocimetry (LF-PIV) was recently introduced to measure the three-dimension three-component (3D-3C) velocity field with just single camera. The main drawback of this configuration is the decreased measurement accuracy in the out-of-plane dimension due to limited spatial resolution. This work presents a solution with dual-camera arrangement to broaden the viewing angle. Based on multiplicative algebraic reconstruction technique (MART), a novel particle reconstruction algorithm is developed for dual or multiple light field camera PIV system. In addition, the synthetic images of DNS jet data and experimental images of a vortex-ring are utilized to draw a comparison between the velocity measurement results of a single light field camera and dual light field cameras. It is determined that the accuracy of dual-camera configuration in the depth direction has been significantly improved when compared to single light-field camera system.
Volumetric measurements of an adverse-pressure-gradient turbulent boundary layer using single-camera light-field PIV
Zhao Zhou, Ding Junfei, Shi Shengxian
2019, 33(2): 66-71. doi: 10.11729/syltlx20180192
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Abstract:
As a novel volumetric particle image velocimetry technique, Single-Camera Light-Field PIV (LF-PIV) is able to reconstruct three-dimensional flow fields using a single camera. The merits of LF-PIV lie in its concise hardware setup and minimum optical access requirement. Its capability has been proved in many experimental investigations. In this study, LF-PIV is used to measure a self-similar Adverse Pressure Gradient Turbulent Boundary Layer (APG-TBL). Experiments are performed in a large water tunnel at the Laboratory for Turbulence Research in Aerospace and Combustion (LTRAC), Monash University. Twenty independent batches of light-field PIV images are captured for both inner and outer flow, each consisting of 250 instantaneous image pairs. Instantaneous 3D velocity fields are reconstructed with the GPU accelerated DRT-MART and 3D cross-correlation methods and compared with two-dimensional PIV (2D-PIV) results. Preliminary results show that though limited by the experiment conditions and PIV algorithms developed in 2016, similar accuracies to 2D-PIV are achieved near and above the boundary layer. With the volumetric calibration method that compensates optical distortions caused by lens defect and misalignment between the Microlens Array (MLA) and image sensor, the resolution of LF-PIV is greatly improved.
Fabrication and characterization of mesoporous pressure-sensitive luminescent particles for in-flow measurement of pressure and velocity
Gu Feng, Peng Di, Wen Xin, Liu Yingzheng
2019, 33(2): 72-78. doi: 10.11729/syltlx20180180
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Abstract:
A class of micron pressure sensitive fluorescent particles is developed. Porous hollow SiO2 particles and pressure-sensitive fluorescent materials (PtTFPP & Ru(dpp)) are used in these particles. Multifunctional tracer particles are prepared through attaching fluorescent materials to particles by the dip-dye method. Then a new simultaneous pressure and velocity measurement can be developed by combined Particle Image Velocimetry (PIV) technology and Pressure Sensitive Paint (PSP) technology. The signal intensity, the pressure sensitivity, and the pressure response time are measured by the static and dynamic PSP calibration system. Effects of different particle sizes and different materials on properties of pressure sensitive fluorescent particles are studied. The calibration result reveals that the pressure sensitive fluorescent particles have good pressure sensitivity, and the 40~70μs pressure response time is suitable for measuring the transient pressure in the flow field. The tracking ability is analyzed. The 2μm particles have 7.5μs relaxation time which show a qualified tracking ability.
Study of the boundary layer transition detection technique based on TSP
Huang Hui, Xiong Jian, Liu Xiang, Zhu Maolin, Li Yonghong
2019, 33(2): 79-84. doi: 10.11729/syltlx20180144
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Abstract:
By using the natural laminar airfoil RAE5243 as the research object, the TSP(Temperature Sensitive Paint) transition detection technique is studied in the 0.6m transonic and hypersonic wind tunnel in China Aerodynamics Research and Development Center. The transition detection tests of the model's baseline configuration with and without the shock control bump are conducted at Mach number 0.73 and 0.75, respectively. Focusing on the lack of quantitative analysis method, an automatic location algorithm based on the temperature gradient is proposed, which includes the image preprocessing, the transition point positioning and filtration, and the transition location's calculation. The model's temperature distribution and transition location under different test conditions are compared, and the deviations between repeatable transition detection tests' results are very small, which ensure the reliability of the technique. The transition location of the baseline configuration with the shock control bump is behind that of the baseline configuration at the same Mach number. The same model's transition location at Mach number 0.75 is behind that of 0.73. The TSP result and CFD result match well and the tendency is the same.
Experimental Equipment and Method
Airworthiness certification technology about icing wind tunnel test for pneumatic de-icing aircraft
Gao Guochi, Ding Li, Li Baoliang, Wang Zixu, Jiang Yubiao
2019, 33(2): 85-94. doi: 10.11729/syltlx20180067
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Abstract:
Civil aircraft should conduct icing airworthiness certification according to relevant icing airworthiness regulation requirements, so understanding the airworthiness regulations requirements and formulating the effective conformity certification process are the key points of airworthiness certification. Based on an engineering application of icing wind tunnel test for the Y12F aircraft, relative airworthiness documents, latest aircraft icing research results, certification requests and techniques are summarized, such as setting of target test cases, confirmation of facility, transformation of test cases, test model designing and manufacturing, icing wind tunnel testing and so on. The formed airworthiness certification method conducts the certification of Y12F airplane de-icing system effectively, which is accepted by Civil Aviation Administration of China (CAAC) and Federal Aviation Administration (FAA) synchronously, and it lays a good foundation for getting the aircraft certification of CAAC and FAA.
Icing wind tunnel test technology for pneumatic de-icing aircraft
Gao Guochi, Li Baoliang, Ding Li, Wang Zixu, Ni Zhangsong
2019, 33(2): 95-101. doi: 10.11729/syltlx20180064
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Abstract:
Civil aircraft should conduct icing airworthiness certification according to relevant icing airworthiness regulation requirements in order to obtain the type certificate, and icing wind tunnel test is the effective way to get the critical ice shape. Based on an engineering application of icing wind tunnel test for the Y12F aircraft, test techniques are summarized and analyzed, such as the test model design, simulation of the pneumatic de-icing system, test status transformation, test process, ice shape measurement and so on. A typical test result is represented in the end, which indicates that the pneumatic de-icing system could run effectively under the typical maximum icing condition, and ice could be removed during the work cycle of the system. There would be ice accretion during the interval of system running. Ice formed at the leading edge is always smooth, and the thickness of the ice is from 5 to 6mm. There is an obvious ice ridge about 3 to 4mm thick on the upper surface, and three ice ridges about 2 to 4mm thick accrete on the lower surface.