In this paper, the implementation of the variable-span morphing wing (VSMW) on the wings of a UAV to achiev the optimal performance for various flight regimes is studied in wind tunnels. For the implementation of this plan, a morphing wing with its related mechanism is designed, built and tested. Tests were carried out at a low- speed wind tunnel with speeds of 35, 60 and 80 m/s in the range of Reynolds Number between 250´103 to 620´103. For the implementation of the morphing wing plan, the maximum deviation of wing span relative to Basewing (BW) is 38 percent and change of aspect ratio is 74% percent. Experimental results showed the improved aerodynamic properties of VSMW compared to BW. These improvements are in the form of reduction of induced drag, thrust required and increasing of lift coefficient, aerodynamic efficiency, endurance and rang. According to the results, endurance and range for VSMW comparison to BW, respectively 17 and 5 percent increased. The experimental studies show that the maximum aerodynamic efficiency of the wing model occurs at 4 degree angle of attack with the maximum value being 14.8 for the base wing, 16.3 for the morphing wing with 50 percent (5 cm) extension in wing span, and 17.4 % for the morphing wing with 100 percent (10 cm) span extension. This research also shows how VSMW can be used as an alternative method of roll control instead of the regular method (i.e. using aileron control surfaces) as it provides more roll control power than the regular method.

The neoclassical growth model is tested by use of panel Data procedure in this research. In the econometric test, simoultanously time series and cross detection will be compared on the basis of panel Data method through which their observed points increase and consequently the estimation efficiency will be increased. The examination of neoclassical growth theory has been done with reference to external & internal factors of 52 selected countries from 1960 to 2000. The independent variable of model has been selected on the basis of the result of previous research which explains the result in three separate models: developed countries, developing countries, and whole countries. These factors are such as: Gross National Products with lag of period, work force age, growth rate, education level, the change of capital accumulation and economic trade volum. The consequences of this research is that: neoclassical growth model can explain the major part of economic growth of the countries with use of internal variables. Also with the use of panel procedure of fixed effect, we can see the fundamental differences and structure of the growth process for different countries; and show how the economic, and social conditions affect on the growth.

A multi-objective optimization (MOO) of two-element wing models with morphing flap by using computational fluid dynamics (CFD) techniques, artificial neural networks (ANN), and non-dominated sorting genetic algorithms (NSGA II), is performed in this paper. At first, the domain is solved numerically in various two-element wing models with morphing flap using CFD techniques and lift (L) and drag (D) coefficients in wings are calculated. Afterward, for modeling L and D using grouped method of Data handling (GMDH) type artificial neural networks, numerical Data of the preceding step will be applied. Eventually, for Pareto based multi-objective optimization of two-element wing models with morphing flap using NSGA II algorithm, the modeling, which is accomplished by GMDH will be applied. It is shown that the achieved Pareto solution includes important design information on such wings.

Three-dimensional numerical simulations are performed to examine the effects of dynamic wing morphing of a hummingbird-inspired flexible flapping wing on its aerodynamic performance in hovering flight. The range analysis and variation analysis in the orthogonal experiment are conducted to assess the significance level of various deformations observed in the hummingbird wings on wing aerodynamic performance. It has been found that both camber and twist significantly can affect lift, and twist has an even higher significant impact on lift efficiency. Spanwise bending, whether out-of-stroke-plane or in-stroke-plane, has a negligible impact on lift and efficiency, and the in-stroke-plane bending can cause lift to decrease to an extent. Optimal parameters for determining the wing deformations are selected and tested to validate the conclusions drawn in the analysis for the results in orthogonal experiment. Through a comparison study between the optimized wings and the rigid wing, it is found that although the wing flexibility can cause the net force to decrease, the flexible wing used less energy to bring the net force closer to the vertical direction, thereby improving the lift efficiency. This study provides an aerodynamics understanding of the efficiency improvement of the hummingbird-inspired flexible flapping wing.

Implementation of bottom step in high speed planing hulls can lead to resistance reduction. Moreover, by using step, rough water performance of planing hulls will improve because the lift force is distributed over the hull bottom which can lead to porpoising stability in waves. In this paper, three dimensional fluid flows around a stepped hull is simulated. The governing equations is solved by finite volume method in conjunction with volume of fluid. Free surface flow and the complexity related to the flow separation from step have been thoroughly investigated. Moreover, in the presented simulation, hull has two degrees of freedom in sinkage and dynamic trim. Therefore, dynamic fluid-body interaction (DFBI) solver based on the mesh morphing approach is utilized. In process of numerical solution, computational domain is fixed and the mesh around the hull is moved. The obtained results for the resistance, dynamic trim and sinkage, Chine wetted length and keel wetted length of stepped hull, at different velocities, have been compared and validated against available experimental Data. Also, dry length after step and stagnation line variations in various velocities is discussed. The obtained results indicate that the proposed numerical model can be used for optimal design of stepped hulls.

Inspiring from bird’s wings and flights has long been a fascinating subject. In recent years, due to advent of materials and implementation of bird’s flights, use of morphing wings have created considerable changes in scientific issues related to air vehicles. In this article, for the first time, aerodynamic and aeroacoustic studies of a type of (twist) morphing wing are performed. The main pupose of this article is to numerically investigate aerodynamics and aeroacoustics of a twisted morphing wing for a geometry similar to Shahed- 129 UAV. In the manufaturing part of this article, a new method is introduced, which uses actuators to change the wing’s shape. In this article, k- ω- SST modeling for turbulent flow and Fluent software were used. Our results show that with increase of twist angle and attack angle of up to 15 degrees, both lift and drag increase. In addition, at the same angle of attack, for high twist angles, increasing twist angle increases the growth of vortices, causesing a small increase in lift coefficient.

Todays gamma knife radiosurgery is used widely for treatment of very small brain tumors. In order to investigate accuracy of dosimetry and treatment planning calculations, using Monte Carlo simulation with dedicated code named as beamnrc including non-CT Data and CT Data options is necessary. The aim of this study is choosing the best options in order to have an accurate tools based on their advantages and disadvantages. In this study, gamma knife unit 4C along with standard water equivalent phantom and EBT3 films were used to obtain dose distributions. Monte Carlo simulation was done with non-CT Data and CT Data options of the code and their resulting dose were compared. Comparison the calculated and measured dose distributions at X, Y and Z axis showed gamma value below 1 which verified Monte Carlo simulations. Also comparing the dose distributions from both non-CT Data and CT Data with each other implies that there is no significant difference between two methods. Based on the obtained results using non-CT Data and CT Data results in the same dose distribution. So for simplicity, using non CT Data for regular phantom shapes is preferred.

In recent privacy has emerged as one of the major concerns of deep learning, since it requires huge amount of personal Data. Medical Image Analysis is one of the prominent areas where sensitive Data are shared to a third party service provider. In this paper, a secure deep learning scheme called Metamorphosed Learning (MpLe) is proposed to protect the privacy of images in medical image analysis. An augmented convolutional layer and image morphing are two main components of MpLe scheme. Data providers morph the images without privacy information using image morphing component. The human unrecognizable image is then delivered to the service providers who then apply deep learning algorithms on morphed Data using augmented convolution layer without any performance penalty. MpLe provides sturdy security and privacy with optimal computational overhead. The proposed scheme is experimented using VGG-16 network on CIFAR Dataset. The performance of MpLe is compared with similar works such as GAZELLE and MiniONN and found that the MpLe attracts very less computational and Data transmission overhead. MpLe is also analyzed for various adversarial attack and realized that the success rate is as low as 7. 9 × 10-90. The efficiency of the proposed scheme is proved through experimental and performance analysis.