ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities最新文献_第2页

Further developments of pressure sensitive paint (OPMS) for non flat models in steady transonic flow and unsteady conditions 跨声速和非定常条件下非平面模型压敏涂料的进一步发展

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519464

R. Engler

引用次数: 18

High intensity acoustic testing of flight structures 飞行结构的高强度声学测试

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519481

R. Shimovetz, K. Wentz

{"title":"High intensity acoustic testing of flight structures","authors":"R. Shimovetz, K. Wentz","doi":"10.1109/ICIASF.1995.519481","DOIUrl":"https://doi.org/10.1109/ICIASF.1995.519481","url":null,"abstract":"High intensity acoustic testing has been an important part of Air Force technology for nearly thirty years. With the advent of jet aircraft in the 1950s, acoustic fatigue of aircraft structures became a significant problem. In the 1960s the Wright Laboratory constructed the first large acoustic fatigue test facilities in the United States, and the laboratory has been a dominant factor in high-intensity acoustic testing since that time. In addition to fatigue of jet aircraft structures, other severe acoustic environments have been identified. Of particular importance are the acoustic environments of missiles in captive carry on fighter aircraft, and the high-temperature acoustic environments of blown flaps, hypersonic structures, and engine exhaust structures of stealthy aircraft. This paper describes the causes of these intense dynamic environments and some of the new facilities designed for testing structures subjected to these dynamic loads. The Wright Laboratory facilities now include three new chambers: (1) a sub-element acoustic chamber for testing structural panels up to 12\"/spl times/18\" [0.30/spl times/0.46 m], (2) a combined environment acoustic chamber for panels up to 4'/spl times/4' [1.23/spl times/1.23 m], both at acoustic levels of 175-180 dB and heat fluxes of 50 to several hundred Btu per square foot per second [5000 W/m/sup 2/], and (3) a random fatigue chamber for vibration testing of structural coupons up to 3\"/spl times/7\" [0.8-0.0.2 m] at temperatures from -250/spl deg/F to +2700/spl deg/F [120/spl deg/C-1470/spl deg/C] at atmospheric or lower pressures in the present of hydrogen and helium gases.","PeriodicalId":339620,"journal":{"name":"ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116906861","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

3 component LDV for near wall measurements on a multi-element high lift airfoil configuration 3组件LDV近壁测量多元素高升力翼型配置

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519486

U. Seelhorst, K. Butefisch, M. Weiland

{"title":"3 component LDV for near wall measurements on a multi-element high lift airfoil configuration","authors":"U. Seelhorst, K. Butefisch, M. Weiland","doi":"10.1109/ICIASF.1995.519486","DOIUrl":"https://doi.org/10.1109/ICIASF.1995.519486","url":null,"abstract":"Flow field investigations in the near wall region of a high lift wing configuration have been performed by means of a 3D laser-Doppler velocimeter with a working distance of 3.5 m. The measurements were conducted on a 1:7.5 AIRBUS A321 model of Daimler-Benz Deutsche Aerospace (DASA) in the closed 6 m/spl times/8 m test section of the Deutsch-Niederlandischer Windkanal (DNW), The Netherlands. Due to motions and vibrations of the model with amplitudes in the range of a factor of 15 greater than the required spatial resolution, a simultaneous acquisition of the translatoric parameters was indispensable to convert the obtained velocity data measured in a wind tunnel fixed co-ordinate system into a model fixed co-ordinate system. As a result of the applied procedure velocity, turbulence, and shear stress data also close to the wall could be measured very accurately even though the model could not be held fixed in space. Valuable results on the three dimensionality of the flow field and the behaviour and the structure of the separation bubble in the wing shroud have been obtained.","PeriodicalId":339620,"journal":{"name":"ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131057253","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 5

A combined holographic interferometer and laser-schlieren system applied to high temperature, high velocity flows 一种用于高温、高速流动的全息干涉仪和激光纹影组合系统

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519118

D. Kastell, G. Eitelberg

{"title":"A combined holographic interferometer and laser-schlieren system applied to high temperature, high velocity flows","authors":"D. Kastell, G. Eitelberg","doi":"10.1109/ICIASF.1995.519118","DOIUrl":"https://doi.org/10.1109/ICIASF.1995.519118","url":null,"abstract":"The High Enthalpy tunnel in Gottingen (HEG) is operated by the German Aerospace Research Establishment (DLR). Nominal test conditions of a free stream Mach number of 10, reservoir enthalpies of up to 23 MJ/kg and reservoir pressures of up to 100 MPa make the HEG ideal to study the \"hot\" entry phase of space vehicles. For the flow visualisation in the HEG a holographic interferometer with a 300 mm field of view is set-up. It uses the phase step technique for the evaluation of the holograms. This method enables computerized evaluation of the holograms to create high quality interferograms by increasing the signal to noise ratio. Complete flow field density gradients around two dimensional models can be calculated from the interferograms. Nevertheless for three dimensional models, where the integration length of the light path is too short to obtain a large fringe shift, the exact localisation of the shocks is difficult. To overcome this lack of the holographic interferometric system it has been extended by a laser-schlieren system to obtain simultaneous interferometric and schlieren information. Results that are presented for the hyperboloid flare model demonstrate the feasibility of the combined system. A comparison of laser-schlieren and hologram-schlieren images made for the axisymmetric Electre model show that the resolution of a direct recorded schlieren image is much higher than the latter.","PeriodicalId":339620,"journal":{"name":"ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131394717","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 8

An investigation on the interference of internal six-component wind tunnel balances with FEM 用有限元法研究了内六分量风洞平衡的干扰

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519122

Junnai Zhai, B. Ewald, K. Hufnagel

引用次数: 6

Application of pulse tube for the test of the engines of hypersonic aircraft 脉冲管在高超声速飞机发动机试验中的应用

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519482

A. Latypov, M. I. Yaroslavtsev, V. Zudov

引用次数: 2

A mathematical model and experimental investigation on increasing starting altitude of turbine engine 提高涡轮发动机起动高度的数学模型及试验研究

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519134

Ning Xing-qiang, Lin Wen

{"title":"A mathematical model and experimental investigation on increasing starting altitude of turbine engine","authors":"Ning Xing-qiang, Lin Wen","doi":"10.1109/ICIASF.1995.519134","DOIUrl":"https://doi.org/10.1109/ICIASF.1995.519134","url":null,"abstract":"A theoretical and experimental investigation has been carried out to study the effect of oxygen addition on the altitude ignition performance of a turbine engine. The results show that the injection of oxygen can improve altitude light-up performance significantly. The starting altitude of turbine engine has been increased approximately from 4000 meters to 8000 meters. The light-up flight Mach number has been varied roughly from 0.36 to 0.8. In the theoretical phase of this investigation, the paper has calculated the flow structure of a short-annular reverse-flow combustion chamber of a turbine engine. The combustor created vortices to stabilize combustion by using three jet groups. The SIMPLE (Semi-Implicit Method for Pressures-Linked Equation)and constant viscosity turbulent model were employed to solve the Navier-Stokes equations. The paper has predicted the flow structure. The flow field of calculation shows that the reverse flow vortex at the back of the air inlet tube is more stable. Here can form a combustion zone for fuel addition. In the experimental phase of this investigation, the basic theory of increasing starting altitude has been discussed in detail. An air-borne oxygen supply ignition device (AOSID) has been developed to expand the applied range of the engine. High altitude simulating cell tests and flight tests with mother aircraft for turbine engine equipped with AOSID have also been performed successfully. Subsequently, the results of ignition tests show that AOSID is very beneficial to ignition, especially to high altitude ignition.","PeriodicalId":339620,"journal":{"name":"ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117256038","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Traversing system for full-scale wind tunnel 全尺寸风洞穿越系统

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519474

J. Raagaard

引用次数: 1

The application of PIV (Particle Image Velocimetry) to transonic flow measurements PIV(粒子图像测速)在跨声速流测量中的应用

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519484

P. Bryanston-Cross

引用次数: 4

Investigation of relaxation processes in flow about models in hypersonic wind tunnels of different types 不同类型高超声速风洞模型流动松弛过程的研究

ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities Pub Date : 1995-07-18 DOI: 10.1109/ICIASF.1995.519479

V.I. Alfyorov, G. I. Shcherbakov, A. Rudakova, I. Yegorov, V.N. Skirda, A.S. Bushmin, L.M. Dmitriyev, B.V. Yegorov, Yu.Ye. Markachev, A. N. Morozov, A.A. Orlov

{"title":"Investigation of relaxation processes in flow about models in hypersonic wind tunnels of different types","authors":"V.I. Alfyorov, G. I. Shcherbakov, A. Rudakova, I. Yegorov, V.N. Skirda, A.S. Bushmin, L.M. Dmitriyev, B.V. Yegorov, Yu.Ye. Markachev, A. N. Morozov, A.A. Orlov","doi":"10.1109/ICIASF.1995.519479","DOIUrl":"https://doi.org/10.1109/ICIASF.1995.519479","url":null,"abstract":"The theoretical and experimental results are presented which relate to flows over such simple bodies as a semisphere, a wedge, and a cone investigated in hypersonic wind tunnels of various classes at similar Mach and Reynolds numbers (M=7.0 to 8.0; Re/sub o//spl sime/135 to 210) and at different air flow velocities (790/sup m///sub s/, 2700/sup m///sub s/ and 6000/sup m///sub s/). Hypersonic resistor-type and arc-heating wind tunnels and a hypervelocity MHD-air acceleration wind tunnel, as well as their test equipment are described. Experimental data on pressure distribution on model surfaces, shock wave position and shape were obtained. For visualization purposes, an electron beam was used in the first wind tunnel and filming of natural flow glow was made by using neutral and interference light filters in the second and third wind tunnels. Use was also made of a specially developed shadow device based on the application of an abnormal dispersion effect of resonant emission of Na atoms. The experimental body flow data are compared with respective calculated results obtained by using the VSL theory and the Navier-Stokes equations. The data are in good agreement for the case of a perfect gas and satisfactory for the case of a gas with chemical reactions.","PeriodicalId":339620,"journal":{"name":"ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132684544","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3