Könnyű sportrepülőgép tervezése szélcsatorna tesztek és korszerű tervezőprogramok alkalmazásával

Jelen tanulmányi anyag egy könnyűszerkezetes sportrepülőgép (LSA) előzetes tervezését mutatja be – kitérve ennek különböző tervezési fázisaira, illetve szélcsatorna kísérleteire – amely különös figyelmet fordít egy könnyűszerkezetü, nagy hatótávolságú, alacsony üzemanyagfogyasztású, illetve kis költségvetésű repülőgép gyártására. Számos szélcsatorna-teszt végrehajtására került sor, a repülőgép aerodinamikai számításainak fejlesztésére. Az előzetes tervezési számításokat, illetve a szélcsatorna kísérleteket sorozatos repülési kísérletek követik, amik segítségével meghatározhatjuk a repülő valós teljesítményét és dinamikai stabilitását

The contact angle of nanofluids as thermophysical property

Droplet volume and temperature affect contact angle significantly. Phase change heat transfer processes of nanofluids – suspensions containing nanometre-sized particles – can only be modelled properly by understanding these effects. The approach proposed here considers the limiting contact angle of a droplet asymptotically approaching zero-volume as a thermophysical property to characterise nanofluids positioned on a certain substrate under a certain atmosphere. Graphene oxide, alumina, and gold nanoparticles are suspended in deionised water. Within the framework of a round robin test carried out by nine independent European institutes the contact angle of these suspensions on a stainless steel solid substrate is measured with high accuracy. No dependence of nanofluids contact angle of sessile droplets on the measurement device is found. However, the measurements reveal clear differences of the contact angle of nanofluids compared to the pure base fluid. Physically founded correlations of the contact angle in dependency of droplet temperature and volume are obtained from the data. Extrapolating these functions to zero droplet volume delivers the searched limiting contact angle depending only on the temperature. It is for the first time, that this specific parameter, is understood as a characteristic material property of nanofluid droplets placed on a certain substrate under a certain atmosphere. Together with the surface tension it provides the foundation of proper modelling phase change heat transfer processes of nanofluids

Thermophysical Properties of NH3/IL+ Carbon Nanomaterial Solutions

This study proposes the use of new working fluids, refrigerant/IL+ carbon nanomaterials (CNMs), in absorption systems as an alternative to conventional working fluids. In this regard, the thermophysical properties of ammonia and carbon nanomaterials (graphene and single-wall carbon nanotubes) dispersed into [BMIM]BF4 ionic liquid are theoretically investigated. The thermophysical properties of NH3/IL+ CNMs solutions are computed for weight fractions of NH3 in the range of 0.018–0.404 and temperatures between 293 and 388 K. In addition, two weight fractions of CNMs are considered: 0.005 and 0.01, respectively. Our results indicate that by adding a small amount of nanomaterial to the ionic liquid, the solution’s thermal conductivity is enhanced, while its viscosity and specific heat are reduced. Correlations of the thermal conductivity, viscosity, specific heat, and density of the NH3/IL+ CNMs solutions are proposed

Computational Study Of Curved Underbody Diffusers

This paper presents new results concerning the aerodynamics of the Ahmed body fitted with a non-flat underbody diffuser. As in previous investigations performed, the angle and the length of the diffuser are the parameters systematically varied within ranges relevant for a hatchback passenger car. Coefficients of lift and drag are compared with the values obtained for the flat underbody diffuser, and the results reveal significant improvements concerning aerodynamic characteristics of body

Preliminary Design of a LSA Aircraft Using Wind Tunnel Tests

This paper presents preliminary results concerning the design and aerodynamic calculations of a light sport aircraft (LSA). These were performed for a new lightweight, low cost, low fuel consumption and long-range aircraft. The design process was based on specific software tools as Advanced Aircraft Analysis (AAA), XFlr 5 aerodynamic and dynamic stability analysis, and Catia design, according to CS-LSA requirements. The calculations were accomplished by a series of tests performed in the wind tunnel in order to assess experimentally the aerodynamic characteristics of the airplane

Water-Based Graphene Oxide–Silicon Hybrid Nanofluids—Experimental and Theoretical Approach

In the current paper, a new hybrid nanofluid based on graphene oxide sheets and silicon nanoparticles is proposed for thermal applications. GO sheets and Si nanoparticles with different mixture ratios are dispersed in distilled water. Dynamic viscosity is measured at temperatures within the range 20–50 °C and the values are compared to the results available in the literature. The results indicated that the viscosity increases with increasing the mixture ratio of graphene oxide. A new correlation for the dynamic viscosity based on the experimental findings is proposed. Finally, the criteria for the performance of new hybrid nanofluid for thermal applications are analyzed

Flight Control System Design and Analysis of a Light Sport Aircraft with Emphasis on Multibody Dynamics and Aerodynamic Analysis

The present contribution is a companion paper of [9] which presents a preliminary design of the flight control system of a Light Sport Aircraft (based on previous wind tunnel analysis), validation process, aerodynamic simulations in ANSYS CFX and multibody dynamics in Adams. The main purpose of this study is to obtain knowledge on simulation software’s, as Ansys and Adams, in order to design, calculate and improve the flight control mechanism of an ultralight aircraft