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Most published Xplore authors for Wind Tunnels

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Xplore Articles related to Wind Tunnels

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Analysis of aerodynamic characteristics for a flying-wing UAV with asymmetric wing damage

2018 33rd Youth Academic Annual Conference of Chinese Association of Automation (YAC), 2018

This paper investigates the influence of aerodynamic characteristics for a flying-wing Unmanned Air Vehicle (UAV) subject to asymmetric wing damage. Firstly, the conceptual design of a flying-wing UAV is introduced. The UAV model with right wing damage is constructed, from which the vehicle's physical characteristics, such as mass, center of gravity (C.G.) and moment of inertia are calculated. Next, the ...


Hypersonic Flow Velocity Measurements Using FLEET

2018 Conference on Lasers and Electro-Optics (CLEO), 2018

We developed and applied a Femtosecond Laser Electronic Excitation Tagging (FLEET) system to nonintrusive flow velocity measurements in a large scale hypersonic wind tunnel. Freestream and boundary layer velocity measurements are compared with model predictions.


Influence Investigation of Wide-Bodied Aircraft Test Model Cavity Pressure on Force Test Data Accuracy

2018 3rd International Conference on Smart City and Systems Engineering (ICSCSE), 2018

The sting support is the conventional support methodology in large aircraft wind tunnel force test with the ventral support as an auxiliary support to eliminate the support interference. In the previous large aircraft force test of the FL-26 wind tunnel, It is generally considered that the cavity pressure pattern and magnitude in situations of sting support and ventral support are ...


Numerical Prediction of Magnus Effect for Dual-Spin Projectile

2018 6th International Conference on Mechanical, Automotive and Materials Engineering (CMAME), 2018

Dual-spin projectile is comprised by precision guidance kit (PGK) and normal spin-stabilized projectile. The boundary layer of the dual-spin projectile body is affected by both PGK's tail flow and spin rate. In this paper, the normal force coefficient and side force coefficient were performed using steady-state Reynolds-averaged Navier-Stokes (RANS) for different PGK orientation angle, projectile body spin rate and angle ...


Implementation of hot-wire anemometer on olfactory mobile robot to localize gas source

2018 International Conference on Information and Communications Technology (ICOIACT), 2018

Wind is a major factor that can inhibit the process of tracking the source of gas leakage by the olfactory mobile robot, as it can reduce and even remove the gas concentration. This will cause the robot to take a long time to find the source of the gas leak, even fails. Therefore, this study has implemented anemometer to help ...


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Educational Resources on Wind Tunnels

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IEEE-USA E-Books

  • Analysis of aerodynamic characteristics for a flying-wing UAV with asymmetric wing damage

    This paper investigates the influence of aerodynamic characteristics for a flying-wing Unmanned Air Vehicle (UAV) subject to asymmetric wing damage. Firstly, the conceptual design of a flying-wing UAV is introduced. The UAV model with right wing damage is constructed, from which the vehicle's physical characteristics, such as mass, center of gravity (C.G.) and moment of inertia are calculated. Next, the aerodynamic model of damaged UAV is established in DATCOM, and the aerodynamic coefficients of UAV under different damage conditions are computed. Based on the obtained aerodynamic coefficients, the effect of asymmetric wing damage for the UAV is analyzed. Furthermore, the influence of the static stability is analyzed according to the aerodynamic derivatives.

  • Hypersonic Flow Velocity Measurements Using FLEET

    We developed and applied a Femtosecond Laser Electronic Excitation Tagging (FLEET) system to nonintrusive flow velocity measurements in a large scale hypersonic wind tunnel. Freestream and boundary layer velocity measurements are compared with model predictions.

  • Influence Investigation of Wide-Bodied Aircraft Test Model Cavity Pressure on Force Test Data Accuracy

    The sting support is the conventional support methodology in large aircraft wind tunnel force test with the ventral support as an auxiliary support to eliminate the support interference. In the previous large aircraft force test of the FL-26 wind tunnel, It is generally considered that the cavity pressure pattern and magnitude in situations of sting support and ventral support are assumed to be basically consistent, and the influence of model cavity pressure with sting support and ventral support on test data was not deducted. With the research and development of wide-body aircraft in China, As an important part of the accuracy of the test data, support interference must be studied in detail. In order to research the influence on the fore test data, a wide- bodied aircraft wind tunnel test was conducted in FL-26 wind tunnel. Four bottom pressure pipes were embedded to measure the cavity pressure in both sting support and Ventral support. For wide-body aircraft type, the test results show that the difference between cavity pressure patterns in the sting and Ventral support is apparent, and the influence on lift and pitch moment can be neglected.

  • Numerical Prediction of Magnus Effect for Dual-Spin Projectile

    Dual-spin projectile is comprised by precision guidance kit (PGK) and normal spin-stabilized projectile. The boundary layer of the dual-spin projectile body is affected by both PGK's tail flow and spin rate. In this paper, the normal force coefficient and side force coefficient were performed using steady-state Reynolds-averaged Navier-Stokes (RANS) for different PGK orientation angle, projectile body spin rate and angle of attack. From numerical predicted data, the normal force coefficient is found to be spin insensitive and the side force coefficient varies approximately linearly with spin rate. The slope of lines about side force coefficient versus spin rate are approximately constant for a constant angle of attack and Mach number, different PGK orientation angle just affects the intercept of lines.

  • Implementation of hot-wire anemometer on olfactory mobile robot to localize gas source

    Wind is a major factor that can inhibit the process of tracking the source of gas leakage by the olfactory mobile robot, as it can reduce and even remove the gas concentration. This will cause the robot to take a long time to find the source of the gas leak, even fails. Therefore, this study has implemented anemometer to help the robot to determine the direction of the gas source. A hot wire anemometer is a tool used to measure wind speed by utilizing heated wire filaments. The nickel wire is wrapped to a semiconductor temperature sensor and is supplied with a constant current resulting in a temperature of 60 °C. The Neural Network algorithm is used to determine wind direction based on the pattern of temperature change values on four anemometers. The experimental results showed that this anemometer has an accuracy rate of 88%. In addition, the application of anemometer on the olfactory mobile robot can help the robot's movement towards the target so that it can improve the success rate.

  • Development of the AMT in yawing control of flying wing UAVs

    This paper focus the property and application on an innovative yawing control effector for unmanned aerial vehicles (UAV) named all moving wing tips (AMT). The prospective application area of AMT is flying wing and other kind of stealth fighters. In terms of performance, it has a linearly drag output through a deflection from 20° to 60°, which is friendly to control methodology, and the yawing control efficiency is at a same order of magnitude with the traditional rudder. The AMT has a good prospect of application on future UAVs.

  • Analysis of S-4180 using computational fluid dynamics

    Computational fluid dynamics is Virtual method of scientific and engineering investigation, concerned with the development and application of a video- camera like tool - a software - which is used to analyze a fluid dynamics as well as heat and mass transfer problem in a unified way. Here, the software is like a virtual video-camera and result in movie where each picture gives a fluid dynamics information, i.e., flow properties. The main objective of this paper is to use Computational Fluid Dynamic method for the analysis of two dimensional characteristics of airfoil s-4180 of Seligg. The coefficient of lift (Cl) and drag (CD) of s-4180 airfoil were successfully measured at an angle of attack 00-30 using CFD.

  • Experimental Investigation of Micro-Aerial Vehicle Wing Designs

    The use of micro aerial vehicles (MAV) has become a rapidly growing class of aerial vehicle for habit, commercial industrial and many other applications. However, micro aerial vehicle design is a challenge because of the lack of understanding about the aerodynamics of miniaturized aircraft at low speeds. This paper presents a novel tandem-morphing wing system for MAV design. The bio-inspired design is tested with various angles of attack for low chord Reynolds number regimes around 2×104. 16 different morphing-wing configurations are tested for lift-to-drag ratio optimization. This systematic experiments link the influence of the airfoil configurations of tandem-wings to the performance of its aerodynamic characteristics.

  • Clamp-on transducers for measuring swirl, cross flow and axial flow

    It is sometimes said that the ideal flowmeter would be immune to swirl and cross flow. Since no real flowmeter is ideal, it seems that one would like to know if swirl or cross flow are present at a metering site, and if present, in what amount. It turns out that simple modification or reorientation of standard clamp-on transducers for liquid axial flow leads to totally noninvasive solutions for liquid swirl and liquid cross flow. To obtain analogous measurements in gases, however, one to three holes in the pipe or pressure boundary are generally required. Clamp-on laboratory results are presented for water in unperforated 2-inch pipes (1D≈51 mm) and for air in 10-inch (254-mm ID) steel pipe containing one hole for the measurement of swirl or circulation, a second hole for cross flow and a third hole for axial flow. In another air experiment, conducted in a small wind tunnel, circulation about an airfoil is related to lift

  • Wind tunnel measurements for the characterization of a small scale monoplane Wells turbine

    In the field of wave energy harnessing, Oscillating Water Column (OWC) devices are nowadays a consolidated technology. In OWC energy converters, waves generate an oscillating flow, whose energy can be effectively captured, for instance, by means of self-rectifying Wells turbines. In the design of Wells turbines, main issues are the improvement of their peak efficiency and the widening of their operational range. In order to reach these goals, a deep knowledge of the turbine fluid dynamic performance is essential. This paper presents the results of the experimental investigation of a small scale monoplane Wells turbine, tested in an open circuit low speed wind tunnel of the suction type in order to characterize its performance in terms of non- dimensional parameters, namely, torque and pressure drop coefficients and efficiency. The prototype under investigation, with blades of constant chord and NACA0015 profile, has been designed in order to be matched with a REWEC (Resonant Wave Energy Converter) breakwater, which had been located off the beach of Reggio Calabria. The REWEC under consideration was an excellent small scale model of full scale sea wave energy conversion devices for oceanic applications. Results have been compared with previous in-field tests, showing a very good agreement.



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