The aim of this study is to evaluate the Aerodynamic efficiency of a Savonius vertical-axis wind turbine. The approach used relies on resolving the Unsteady Reynolds Averaged Navier-Stokes equations (URANS), the turbulence being modeled by the k-ω SST model. The flow around the wind turbine is simulated using the arbitrary sliding interfaces technique. First, the study investigates the impact of blade shape on wind turbine efficiency by examining seven Savonius rotors constructed with distinct blade configurations. The results indicate that the highest Aerodynamic performance is provided by the rotor with the elliptical blades, with a notable increase in the power coefficient of about 80% in comparison to the classic semi-circular profile. To further enhance the efficiency of the Savonius wind turbine, a twin-rotor configuration using the elliptical blades was studied. The results indicate a further enhancement in the power coefficient, reaching 110% compared to a single rotor with semicircular blades.

This work aimed to prepare a nanoemulsion preparation containing budesonide and assess its Aerodynamic behavior in comparison with suspension of budesonide. In-vitro Aerodynamic performance of the corresponding micellar solution (ie. nanoemulsion preparation without oil) was investigated too. Nanoemulsions of almond oil containing budesonide, as a hydrophobic model drug molecule, were prepared and optimized. Then, the effect of variation of surfactant/ co-surfactant concentration on the Aerodynamic properties of the nebulized aerosol was studied. The results indicated that the most physically stable formulation makes the smallest Aerodynamic size. The concentration of co-surfactant was also shown to be critical in determination of Aerodynamic size. Furthermore, the optimized sample, with 3% w/w almond oil, 20% w/w Tween 80+Span 80 and 2% w/w ethanol showed a smaller MMAD in comparison with the commercially available suspension and the micellar solution.

Transport Aerodynamic optimisation has become an increasingly important field of study in response to emerging factors, such as new human needs and market demands. This paper provides a concept in-house built sports-car Aerodynamic and shape optimisation. Wind tunnel tests and numerical simulations have been set-up and conducted to understand the concept vehicle Aerodynamic structure and needs for performance improvement. A computer-aided design model has been developed and implemented into the computational fluid dynamics (CFD) software of StarCCM+ for detailed analysis. A 1/4th full-scale fibreglass model has been manufactured for validation. The combined experimental and CFD analyses show that the original aesthetic design exhibits high rear-end lift-force. Modifications have been assessed to improve the drag and lift forces for the front, middle and rear regions. Several geometrical changes are introduced, including new rear-wing design. Also, the front end, roof profile and various ducting modifications have been considered. The introduced design changes lead to optimised downforce of-560. 18 N with negligible increase to the accumulated drag effects with CD ≤ 0. 3.

In this paper, the Aerodynamic and mechanical design of a centripetal-flow fan has been undertaken at a particular thermal environment in which the working fluid behaves as an ideal gas. A preliminary design (one-dimensional analysis) study was conducted at first, based on which three-dimensional modeling and optimization were subsequently applied to the design of the centripetal-flow fan. The Aerodynamic performance of the designed fan and its operating characteristics in different working conditions were assessed by means of numerical simulations. Our results suggest that isentropic efficiency and pressure ratio of the centripetal-flow fan at design operating conditions can reach 81. 14% and 1. 0833, respectively, which satisfy the requirements for fans in commercial and industrial applications. From the fan performance curves, it is found that as the mass flow rate increases, the efficiency of the fan operating at the designed rotational speed first increases and then decreases. There exists an optimal mass flow rate which leads to the maximum efficiency of the fan. Similarly, the fan pressure ratio first increases as the mass flow rate increases, attains a maximum value and then decreases as the mass flow rate further increases. At off-design rotational speeds, although the fan characteristic curves show the same tendency as those observed at the design condition. Moreover, the fan characteristic curve becomes steeper with an increased rotational speed, which means that the variations of isentropic efficiency and pressure ratio with change in mass flow rate become much greater. The results of our present study confirm the feasibility of using the centripetal-flow fan for various industrial applications.

Unmanned Combat Aerial Vehicles (UCAVs) are designed to be lightweight and compact, which can impact their overall lift and Aerodynamic capabilities. This study focuses on enhancing the Coefficient of Lift (CL) by optimising the Back Sweep Angle in the Lambda wing-UCAV. The model's baseline geometry remains unchanged during the experimental and numerical analysis, while different back sweep angles ranging from δ=00 to δ=500 are investigated at varied free-stream velocities and angles of attack. This helps to understand the generation of induced lift in the intricate shapes of the Lambda Wing. The results indicate a 5% to 10% increase in the lift for every 100 increments of the Back Sweep Angle, and the vortices' strength increases and reaches a maximum at δ=400. At greater angles (δ >400), the lift drops gradually with the Reynolds number. The stagnation point shifts from 25% to 35% along the chord towards the pressure surface as the angles of attack increase from α=50 to α=100. The angle of attack α>100.

Icing phenomenon on a natural laminar flow airfoil (NLF-0414) has been experimentally investigated.Double horn glaze ice geometry which was acquired during a 15 minutes spray time at−2.23oC with liquid water content and a median volumetric diameter of 1.0 g/m3 and 20 mm, has been extracted from database of NASA Lewis Research Center. Pressure distribution over airfoil surfacewas evaluated at angles of attack between -2 to 6 degreesfor both iced and clean airfoils. Aerodynamics performance degradation of the iced airfoil has been studied and it is shown that double horn ice accretion, due to its unique geometry, severely affects Aerodynamic characteristics of natural laminar flow airfoils. Reattachment locations have been evaluated for upper and lower separation bubbles. The upper surface separation bubble was seen to increase in size in contrary to the lower surface separation bubble.