2018 Vol. 32, No. 6

Column of Research on Hypersonic Aerodynamics and Aerothermodynamics
Review of hypersonic boundary layer transition induced by roughness elements
Dong Hao, Liu Shicheng, Cheng Keming
2018, 32(6): 1-15. doi: 10.11729/syltlx20180167
Abstract(509) HTML (132) PDF(57)
Abstract:
Hypersonic boundary layer transition plays an important role in aerodynamic design of hypersonic vehicles. Transition control is always one of the main purposes of the transition research. In the hypersonic flow, the roughness element is used to control the boundary layer transition. Firstly, this paper reviews the latest researches in hypersonic boundary layer transition control by various types of roughness elements in recent years. Then, from the perspective of the receptivity of the roughness elements to the hypersonic boundary layer and the crossflow stability, the role of the roughness element in the study of the hypersonic boundary layer transition mechanism is introduced based on the effect of the roughness element on hypersonic boundary layer transition. The application of the oil film interferometry technique in the study of hypersonic boundary layer transition induced by roughness elements in the hypersonic wind tunnel of Nanjing University of Aeronautics and Astronautics (NHW) is also briefly introduced. Finally, the existing problems in hypersonic boundary layer transition are discussed, and the future research trend is also prospected.
An overview of waverider design concept in airframe-inlet integration methodology for air-breathing hypersonic vehicles
Ding Feng, Liu Jun, Shen Chibing, Liu Zhen, Chen Shaohua, Huang Wei
2018, 32(6): 16-26. doi: 10.11729/syltlx20180080
Abstract(691) HTML (240) PDF(51)
Abstract:
As a waverider can possess high lift-to-drag ratio characteristics as well as an ideal pre-compression surface of the inlet system, it has become one of the most promising designs for air-breathing hypersonic vehicles. There are two classes of general methodologies for utilizing the waverider concept in a hypersonic vehicle design. In the first class, the waverider is used only as the forebody of a vehicle, and it behaves as the pre-compression surface to efficiently provide the inlet system with the required compression flow field. In the second class, in order to take advantage of the waverider's high lift-to-drag ratio characteristics as well as the ideal pre-compression surface for the engine, the waverider design is used as the basis for the design of the entire vehicle, and the engine is generated within the pristine waverider definition while maintains the bow shock wave attaching to the leading edge. In this paper, the waverider applications by the domestic and overseas scholars in the airframe-inlet integration methodology for the air-breathing hypersonic vehicles are reviewed and classified. The idea for the design of a waverider-derived hypersonic vehicle can be summarized as follows:the modeling of the basic flow is used to design the waverider along the stream direction, and the osculating theory or the geometric design method is used to design the waverider along the spanwise direction.
Support interference and correction of cold-flow force test for air-breathing hypersonic vehicle in wind tunnel
Wang Xiaopeng, Zhang Chen'an, Liu Chunfeng, Wang Famin, Ye Zhengyin
2018, 32(6): 27-33. doi: 10.11729/syltlx20180116
Abstract(116) HTML (81) PDF(8)
Abstract:
The supporting mechanism greatly influences the aerodynamic force measurement of the air-breathing hypersonic flight vehicles in wind tunnel tests. In this paper, the supporting interference is studied by both wind tunnel experiments and CFD. First, an integrated vehicle is developed based on the wedge-elliptical cone waverider configuration method. Three types of supporting mechanisms are adopted to conduct the force measurement at Mach 4 and 6 in the hypersonic wind tunnel, with the rear sting mount, the back blade mount, and the back blade mount + dummy rear sting mount. And, a correction method is adopted here to account for the supporting interference. With this method, the interference increments due to the supporting mechanism can be eliminated from the results obtained from the rear sting mount. The result shows that all the supporting mechanisms have an influence on the aerodynamic force and the rear sting mount is more suitable to be used as the supporting mechanism with a less influence in contrast with the back blade and the back blade mount + dummy rear sting mount. In addition, it is recommended to use the correction method to improve the measurement accuracy of the experiment data.
Improvement of heat insulation structure in the slug calorimeter and test analysis
Zhu Xinxin, Yang Qingtao, Wang Hui, Yang Kai, Zhu Tao
2018, 32(6): 34-40. doi: 10.11729/syltlx20180071
Abstract(326) HTML (146) PDF(20)
Abstract:
The heat insulation structure of the slug calorimeter was improved in order to enhance the measurement accuracy. The insulating sleeve with hollow structure was designed, which could excessively decrease the unstable lateral heat transfer. By designing package shell structure matched with the slug calorimeter, the heat insulation structure and heat transfer characteristics in calibration could be kept in the heat flux measurement. Numerical calculation analysis was given, which illustrates the validation of the improvement method. Based on the numerical calculation, the size of the slug calorimeter components was optimized. Then the calibration experiment was carried out. The results show that the test accuracy and precision of the slug calorimeter are improved greatly. Finally, the wind tunnel test was carried out. The test results show that the repeatability accuracy of the slug calorimeter is less than 3%. The deviation of measurement values from different slug calorimeters is less than 3% in the same fluid field. The deviation of measurement values between the slug calorimeter and the Gardon gage is less than 4% in the same fluid field.
Stability and transition prediction of the hypersonic plate boundary layers for wall temperature distribution
Liu Lu, Cao Wei
2018, 32(6): 41-48. doi: 10.11729/syltlx20180107
Abstract(139) HTML (74) PDF(14)
Abstract:
The transition prediction of the hypersonic boundary layer on a flat plate is investigated by using the eN method under three different wall conditions including the isothermal, adiabatic and wall temperature distribution conditions. The gas parameters are taken as the corresponding air parameters at the height of 30km with the incoming flow Mach numbers 4.5, 6.0 and 7.0. The calculation results are given and analyzed for four different cases of the wall temperature distribution. The initial disturbance amplitude is estimated to be 0.3‰. The transition is assumed to begin when the disturbance amplitude grows up to 1.5%. It can be seen that the transition location is most close to the leading edge in the case of the isothermal wall condition, and the transition location would move forward as the incoming flow Mach number increases. However, it would move backward as the incoming flow Mach number increases under the adiabatic wall condition. In the case of the wall temperature distribution condition, the transition location moves forward as the incoming flow Mach number increases. It is also found that the higher the wall temperature is, the further backward the transition location is (whereas, at Mach number 7.0, the result is different). In the adiabatic wall cases at the incoming flow Mach numbers 4.5 and 6.0, the transition locations are determined by the first mode waves, whereas the transition locations for the other cases are determined by the second mode waves.
Fundamental Research and Application
Scope effects of terrain models on wind properties design of a bridge located at mountainous area
Liu Liyang, Zhang Zhitian, Wang Zhixiong, Wang Lei
2018, 32(6): 49-54. doi: 10.11729/syltlx20170140
Abstract(150) HTML (103) PDF(5)
Abstract:
Aiming at the wind properties design of a bridge over a deep-cutting valley, 4 terrain models of different scopes are made for wind tunnel investigation, according to the scale ratio of 1:1000. The actual terrain areas covered by the four models are 25, 20, 9 and 1 square kilometers, resepectively. Moreover, the scope of the terrain models is normalized by the characterized dimension of the valley. In the wind tunnel experiment, the mean wind velocity, wind angles of attack and turbulence properties are measured with the wind direction that approximately parallel to the valley. The results indicate that, for the mean wind velocities and wind angles of attack, stable results are obtained when nondimensionalized distance from the bridge site to SE direction in the terrain model is greater than 2.2. For turbulence intensities at the bridge deck height, the two models whose nondimensionalized distance to SE direction is larger than 3.7 result in stable outcomes. However, the profiles of turbulence intensity differ significantly among the 4 models, which indicate that the scope of the models are not large enough as far as the profiles of turbulence intensity are concerned. Terrain model tests[KG(-0.14mm]have been adopted extensively for the wind-resistant design of long-span bridges which ocated at the mountainous terrain. The investigation of this study indicates qualitatively that the scope of a terrain model for this kind of task should be cautiously selected.
Research on aerodynamic forces of a cantilevered circular cylinder in a laminar flow and a uniform turbulent flow
Bian Rong, Lou Wenjuan, Li Hang, Zhang Ligang, Zhao Xiashuang
2018, 32(6): 55-60. doi: 10.11729/syltlx20180103
Abstract(174) HTML (133) PDF(8)
Abstract:
The flow around a cantilevered circular cylinder with an aspect ratio of 2 in a smooth laminar flow and a uniform turbulent flow (Iu=9.5%) is studied experimentally to investigate the aerodynamic forces, including drag coefficients, mean pressure distributions and fluctuating pressure distributions, in the flow from the subcritical to supercritical regime with a high turbulence intensity. The freestream velocity ranges from 5~20m/s, corresponding to Reynolds numbers in the range of 1.73×105 to 6.90×105. The results in the smooth laminar flow indicate that:(1) in the critical regime, the step-like drop of the mean drag coefficient grows larger with the increase of aspect ratios; in the supercritical regime, the mean drag coefficient decreases with the increase of aspect ratios; in the subcritical regime, the peak values of the fluctuating pressure locates at the angle of 70° and moves backward to 110°~115° in the supercritical regime. Sharp peaks occur in the fluctuating pressure distributions at supercritical Reynolds numbers. (2) the results in the uniform turbulent flow show that the peak values of fluctuating pressure occur at the same angles as those in the smooth laminar flow at supercritical Reynolds numbers and change little with the change of Reynolds numbers.
Development of a six-component wind tunnel balance with lower interference on axial force measurement
Yan Wanfang, Jiang Kun, Zhang Jiang
2018, 32(6): 61-67. doi: 10.11729/syltlx20180082
Abstract(574) HTML (245) PDF(57)
Abstract:
The demand of the higher measurement precision and accuracy of a strain-gauge balance is proposed with the development of the wind tunnel experiment, especially for the axial force measurement. A six-component wind tunnel balance with lower interference on axial force is developed in this paper, aiming to obtain a higher precision and accuracy on the axial force measurement. A promising new type of axial force component structure is developed and the finite element method (FEM) is employed to optimize the structure of the design. The axial component design, different from a traditional one, eliminates the interference strain output on axial component from the other aerodynamic forces by placing the axial component in the position of the balance design center with the balance axis just passing through it. In addition, the interference strain output is also eliminated by setting a rectangular "hinge" between the measurement beams of the axial component as well as making the measurement beams offset from the design center along the balance axis. Furthermore, the strain-stress condition of the strain-gauge of axial component performs more satisfying, which improves the stability and the lifetime of the balance. The results of balance calibration and the standard model test show that there is almost no interference on the axial force, and the balance has an approving high precision and accuracy on the axial force measurement, which can meet the high measurement requirement of the modern wind tunnel experiment.
Measuring Technique
Primary study of large-field focusing schlieren technique based on tiled light sources
Xie Aimin, Bu Shaoqing, Luo Jinyang
2018, 32(6): 68-73. doi: 10.11729/syltlx20180012
Abstract(273) HTML (113) PDF(27)
Abstract:
With the development of wind tunnel test techniques, the size of the model is increasing, and the large-field flow visualization is becoming more and more important. Traditional schlieren and other flow visualization techniques are limited by the size of optical elements, and the field of view is difficult to exceed 1.0 meter. On the basis of the focusing schlieren technique, the Fresnel lens are replaced by the tiled LED light sources or other light sources, and the field of view can easily exceed 1.5 meter. After solving the problem of uniform illumination and heat dissipation of light sources, a principle device with 150mm field of view is set up, and the focusing schlieren images of the candle flame and the hot air flow field are clearly obtained. At the same time, multiple focusing lenses can be placed in this type of focusing schlieren system to show larger field of view or different sections. For the large field of view, it is necessary to increase the utilization efficiency of the light sources by the method of, for example, adding convergent lens at the rear end of the light source.
Thermal property measuring techniques of thin-film heat flux sensors based on pulse-heating method
Zhang Hong'an, Huang Jianhong, Qin Feng, Zhang Kouli, Kong Rongzong, Liu Jichun
2018, 32(6): 74-78, 93. doi: 10.11729/syltlx20170120
Abstract(163) HTML (91) PDF(9)
Abstract:
The thermal property measurement of thin-film heat flux sensors with high precision is very important to reduce the uncertainty of heat flow tests in shock tunnels. As the integrating sphere can gather the reflection laser with high uniformity, a method of direct calibration of thermal parameters is proposed, which adopts heating the substrate surface of the thin-film heat flux sensor by using a pulse heating device. Consequently, a pulse heating device is developed, and its components and working principle are also introduced in details. The pulse heating device can preferably simulate the heating process of the thin-film heat flux sensor in the impulse wind tunnel, and accurately calibrate the heat flow value and the thermal parameters. The results indicate that, the pulse heating device has the advantages of convenient operation, simple sample preparation and high accuracy, and can also preferably simulate the environment that the thin-film heat flux sensor experienced in the impulse wind tunnel, thus reducing the uncertainty of the heat flow test.
Experimental Equipment and Method
The validity analysis of ground simulation test for non-ablative thermal protection materials
Wang Guolin, Meng Songhe, Jin Hua
2018, 32(6): 79-87. doi: 10.11729/syltlx20180122
Abstract(71) HTML (89) PDF(7)
Abstract:
The aerodynamic heat load on the surface of the non-ablative thermal protection materials which served in the chemical non-equilibrium flow field, is controlled by the coupling of chemical non-equilibrium degree of flow field and the surface catalytic reaction of the materials. If the coupled effect is neglected in the performance simulation, the effective service performance cannot be obtained through the ground simulation test. Therefore, according to the stagnation-point heat flux relationship within the boundary layer of the blunt body supersonic vehicle, the present paper analyzes the principal flow field parameters, the characteristics of high-enthalpy supersonic field provided by ground simulation equipment, and the differences between ground and flight environments. The validity of the Three-Parameter-Simulation method is analyzed by the CFD simulation. A Four-Parameter-Simulation method is presented for analyzing the heat transfer of the chemical non-equilibrium stagnation-point boundary layer. Besides, the properties of the thermal protection materials is analyzed and a preliminary solution is proposed when the dissociation enthalpy in the Four-Parameter-Simulation is unable to be simulated.
General performance of 0.6m continuous transonic wind tunnel
Liao Daxiong, Chen Jiming, Zheng Juan, Chen Qin, Pei Haitao, Wu Shenghao
2018, 32(6): 88-93. doi: 10.11729/syltlx20170086
Abstract(295) HTML (143) PDF(23)
Abstract:
The 0.6m continuous transonic wind tunnel of CARDC, a circling wind tunnel, use dry air in variable density as working medium. The major components of the wind tunnel include broad-performance compressor, semi-flexible nozzle, lower-noise test section, re-entry flaps and slots, heat-exchange system and the second throat with wall flaps and center body. In order to get the general performance and the secure running boundary of the wind tunnel, the general performance calibration is carried out. Calibration results indicate that the general performances and each section of the wind tunnel agree well with the requirements. The compressor, heat-exchange system and other auxiliary equipments are all in working order. The range of total pressure in settling chamber is 15~250kPa and the control precision of the total pressure is better than 0.2%. The Mach number in the test section is in the range of 0.144~1.640 and the control precision of the Mach number is better than 0.002. The flow qualities such as the fluctuation of Mach number distribution have met the requirements(Ma ≤ 1.0, σMa < 0.002;1.0 < Ma ≤ 1.6, σMa < 0.008). When the Mach number is greater than 0.5, the flow fluctuation coefficient which is used to represent the noise level is below 0.8%. The design scheme's feasibility of the 0.6m continuous transonic wind tunnel is fully verified by the debugging results, which provide scientific guidance for the development of the large-scale continuous transonic wind tunnel.
2018, 32(6): 94-100.
Abstract(55) PDF(6)
Abstract: