Slotted flap is one of high lift devices. It considered as a moving part of the airfoil which is used as a control instrument in a form of elevator, rudders and ailerons. The main focus of work is to investigate the effect of flap chord, gap and overlap on aerodynamic characteristic of NACA 24012 airfoil. The model was tested with 20% C, 30% C and 40% C single slotted flaps at zero angle of attack. The dynamic mesh and user defined function is applied to control the flap distance with respect to wing at any position. The simulation was done by solving the governing equations (Continuity, Reynolds Averaging Naveir-Stokes and Energy Equation) in 2-D using Fluent analysis at Reynolds number of 3.1 10 6 .Based on the results presented, larger increment of lift coefficient is obtained with the larger flap chord, but this increase is accompanied by a drag penalty. Furthermore, the loss of lift coefficient associated with larger extending flap at 3% C had a very detrimental effect on the attainable lift coefficient. The simulation result also shows that an optimum gap is 1% C in order to derive the maximum lift capability from the flap model. The code is validated against field measurements to show how close the CFD model simulates the reality.
In this paper, an investigation of using corrugated passages instead of circular crosssection passages was achieved in conditions simulate the case in the gas turbine blade coolingusing ANSYS Fluent version (14.5) with Boundary conditions: inlet coolant air temperature of300 K with different air flow Reynolds numbers (191000, 286000 and 382000). Thesurrounding constant hot air temperatures was (1700 K). The numerical simulations was done bysolving the governing equations (Continuity, Reynolds Averaging Navier-stokes and Energyequation) using (k-ε) model in three dimensions by using the FLUENT version (14.5). Thepresent case was simulated by using corrugated passage of 3 m long, internal diameter of 0.3 m,0.01 m groove height and wall thickness of 0.01 m, was compared with circular cross sectionpipe for the same length, diameter and thickness. The temperature, velocity distributioncontours, cooling air temperature distribution, the inner wall surface temperature, and thermalperformance factor at the two passages centerline are presented in this paper. The coolant airtemperature at the corrugated passage centerline was higher than that for circular one by(12.3%), the temperature distribution for the inner wall surface for the corrugated passage islower than circular one by (4.88 %). The coolant air flow velocity seems to be accelerated anddecelerated through the corrugated passage, so it was shown that the thermal performance factoralong the corrugated passage is larger than 1, this is due to the fact that the corrugated wallscreate turbulent conditions and increasing thermal surface area, and thus increasing heat transfercoefficient than the circular case.
Viscometers have multiple major applications in various areas of engineering, as the fluid flow is inherently connected to the properties of fluid viscosity. This paper substantively examines the fluid flow state over a capillary viscometer to examine the stability of such flow under the effects of various geometries (variations in tube length and cylinder base shape) of capillary viscometer, using a simulation model improved by means of the application of finite element software in Ansys 16 to depict the flow in the capillary viscometer. In this work, experimental measures were utilised and implemented to evaluate various fluid properties and to observe the effects of the geometrical shapes of the viscometer on the flow properties (pressure, velocity, and temperature) and the effect of fluid type on the vortex and fluid circulation during flow.
This work aimed to improve the heat transfer process in motor engine cylinders by adding eight fins with different shapes around such a cylinder. This process was carried out numerically Fluent software (Ansys 19.0) for different Reynolds numbers (4, 6, and 8 × 104) under constant heat flux (6, 12, 25 kw/m2). The metal used for the fin bodies was aluminium alloy, with a thermal conductivity of 237 W/m-k. Four types of fin, square, circular, elliptical, and air foil, all with the same thickness (5 mm), pitch, gap between each fin (3 mm), and surface area (0.0745 m2) were investigated. The working fluid used was air. The results indicated that the best case was seen in the cylinder with square fins, which obtained the highest value of heat transfer coefficient. The results also indicated that, more generally, the rate of the heat transfer increases when the Reynolds number increases.
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