scholarly journals КОМПЛЕКСНИЙ МЕТОД РОЗРАХУНКУ ОПОРУ ТЕРТЯ І ТЕПЛООБМІНУ НА ПОВЕРХНІ ЛЬОТНИХ ОСЕСИМЕТРИЧНИХ ОБ’ЄКТІВ ПРИ ПОЛЬОТІ ПО ТРАЄКТОРІЇ З НАЯВНІСТЮ В ПРИСТІННОМУ ПРИКОРДОННОМУ ШАРІ НЕІЗОТЕРМІЧНОСТІ, СТИСЛИВОСТІ, ЛАМІНАРНО-ТУРБУЛЕНТНОГО ПЕРЕХОДУ ТА РЕЛАМІНАРІЗАЦІЇ

2018 ◽  
pp. 4-28
Author(s):  
Анатолій Михайлович Павлюченко ◽  
Олександр Миколайович Шийко
Keyword(s):  
Boundary Layer ◽  
Aerodynamic Resistance ◽  
Aerodynamic Heating ◽  
Calculation Of Parameters ◽  
Theory Of Flow ◽  
Turbulent Transition ◽  
Linearized Theory ◽  
The Moment ◽  
Axisymmetric Bodies ◽  
Laminar Turbulent Transition

The complex method of calculation of aerodynamic resistance of friction and heating on the surface of flight axisymmetric bodies of rotation like a jet uncontrollable shell is developed. The method allows to carry out calculations from the moment of start to landing in limits to-, a trance- and supersonic speeds of flight. Range of speeds corresponds to М∞ ≤ 3,0 Mach numbers. When calculating the phenomena of a non-isothermicity, compressibility, laminar-turbulenttransition and a relaminarization which occur on streamline surfaces when flying on a trajectory are considered. The method is based on use of the asymptotic theory ofa wall turbulent boundary layer ofS.S. Kutateladze and A. І. Leontyeva in combination with results of the linearized theory of flow of bodies of rotation, the theory of turbulent spots of Emmons of a transitionalboundary layer and data on Reynolds numbers of the beginning of laminar-turbulenttransition received by results of flight experiments. On the basis of the carried-out calculations of parameters of a stream on a streamline surface of a shell when flying on a trajectory from the moment of start to landing in limits to-, a trance- and supersonic speeds of flight with use of the boundary numbers of laminar-turbulent transitionreceived in flight experiments it is established that flow of a considerable part of a surface of a shell happens in the conditions of laminar-turbulent transition and a relaminarization which occupy an essential part of the general time of flight. Existence of a reverse of laminar-turbulent transition is established by a settlement way. The analysis of values of temperature on a surface of a head part of a rocket when flying on a settlement trajectory has shown that for rather short period there is an aerodynamic heating of a surface which significantly influences the aerodynamic resistance of friction by a non-isothermicity in a wall boundary layer. The conclusion is drawn that the linearized theory of calculations of flow of rather thin bodies of rotation can be used for calculation of parameters on external border of boundary layer of axisymmetric bodies of rotation like a jet uncontrollable shell in limits to-, a trance- and supersonic speeds of flight for the purpose of account longitudinal to pressure gradient when calculating friction and heating. Use of the linearized theory of flow for calculation of parameters on external border of boundary layer in limits to-, a trance- and supersonic speeds of flight allows to create a "fast" algorithm of calculation of resistance of friction and heating taking into account a longitudinal gradient of pressure existing on the streamline surfaces of axisymmetric bodies of rotation. Numerical results of calculations of parameters of a nonviscous current on external border of boundary layerfor the linearized theory, coefficient of a intermittency, temperature of heating of a surface of a shell and resistance of friction from the start moment before landing are given

INFLUENCE OF THE PLATE LEADING-EDGE SHAPE AND THICKNESS ON THE BOUNDARY LAYER LAMINAR-TURBULENT TRANSITION IN HYPERSONIC FLOW

2019 ◽  
Vol 50 (5) ◽  
pp. 461-481
Author(s):  
Sergei Vasilyevich Aleksandrov ◽  
Evgeniya Andreevna Aleksandrova ◽  
Volf Ya. Borovoy ◽  
Andrey Vyacheslavovich Gubernatenko ◽  
Vladimir Evguenyevich Mosharov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Hypersonic Flow ◽  
Leading Edge ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Review: Laminar-to-Turbulent Transition of Three-Dimensional Boundary Layers on Rotating Bodies

1994 ◽  
Vol 116 (2) ◽  
pp. 200-211 ◽  
Author(s):  
Ryoji Kobayashi
Keyword(s):  
Boundary Layer ◽  
Boundary Layers ◽  
Three Dimensional ◽  
Speed Ratio ◽  
Stream Velocity ◽  
Turbulent Transition ◽  
Centrifugal Instability ◽  
Crossflow Instability ◽  
Dimensional Boundary ◽  
Axisymmetric Bodies

The laminar-turbulent transition of three-dimensional boundary layers is critically reviewed for some typical axisymmetric bodies rotating in still fluid or in axial flow. The flow structures of the transition regions are visualized. The transition phenomena are driven by the compound of the Tollmien-Schlichting instability, the crossflow instability, and the centrifugal instability. Experimental evidence is provided relating the critical and transition Reynolds numbers, defined in terms of the local velocity and the boundary layer momentum thickness, to the local rotational speed ratio, defined as the ratio of the circumferential speed to the free-stream velocity at the outer edge of the boundary layer, for the rotating disk, the rotating cone, the rotating sphere and other rotating axisymmetric bodies. It is shown that the cross-sectional structure of spiral vortices appearing in the transition regions and the flow pattern of the following secondary instability in the case of the crossflow instability are clearly different than those in the case of the centrifugal instability.

Investigation of Formation and Development of Stationary and Secondary Disturbances in the Favourable Pressure Gradient Area on the Swept Wing

2013 ◽  
Vol 8 (2) ◽  
pp. 55-69
Author(s):  
Stepan Tolkachev ◽  
Vasily Gorev ◽  
Viktor Kozlov
Keyword(s):  
Boundary Layer ◽  
Roughness Element ◽  
Swept Wing ◽  
Liquid Crystal Thermography ◽  
Natural Case ◽  
Turbulent Transition ◽  
Stage Transition ◽  
The Moment ◽  
Combined Technique ◽  
Attachment Line

In this work the combined technique of liquid-crystal thermography and thermoanemometry measurements is used to trace the stationary disturbance development from the moment of formation to the nonlinear stage transition. It has been shown that the pair of stationary vortices are formed after the cylindrical roughness element. These vortices modify a boundary layer and destabilize it. There is the area of maximal receptivity to the roughness location, which in the experiment was distant from the attachment line. If the stationary disturbance has enough magnitude in its core the secondary disturbances excite and lead to the laminar-turbulent transition. Secondary disturbances are sensitive to the acoustics and achieve the magnitude in hundred times higher than for the natural case

scholarly journals Investigation of Laminar–Turbulent Transition on a Rotating Wind-Turbine Blade of Multimegawatt Class with Thermography and Microphone Array

Energies ◽  
2019 ◽  
Vol 12 (11) ◽  
pp. 2102 ◽  
Author(s):  
Torben Reichstein ◽  
Alois Peter Schaffarczyk ◽  
Christoph Dollinger ◽  
Nicolas Balaresque ◽  
Erich Schülein ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Wind Turbine ◽  
Microphone Array ◽  
Suction Side ◽  
Flow Transition ◽  
Turbulent Transition ◽  
Start Up ◽  
Open Question ◽  
Laminar Turbulent Transition

Knowledge about laminar–turbulent transition on operating multi megawatt wind turbine (WT) blades needs sophisticated equipment like hot films or microphone arrays. Contrarily, thermographic pictures can easily be taken from the ground, and temperature differences indicate different states of the boundary layer. Accuracy, however, is still an open question, so that an aerodynamic glove, known from experimental research on airplanes, was used to classify the boundary-layer state of a 2 megawatt WT blade operating in the northern part of Schleswig-Holstein, Germany. State-of-the-art equipment for measuring static surface pressure was used for monitoring lift distribution. To distinguish the laminar and turbulent parts of the boundary layer (suction side only), 48 microphones were applied together with ground-based thermographic cameras from two teams. Additionally, an optical camera mounted on the hub was used to survey vibrations. During start-up (SU) (from 0 to 9 rpm), extended but irregularly shaped regions of a laminar-boundary layer were observed that had the same extension measured both with microphones and thermography. When an approximately constant rotor rotation (9 rpm corresponding to approximately 6 m/s wind speed) was achieved, flow transition was visible at the expected position of 40% chord length on the rotor blade, which was fouled with dense turbulent wedges, and an almost complete turbulent state on the glove was detected. In all observations, quantitative determination of flow-transition positions from thermography and microphones agreed well within their accuracy of less than 1%.

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