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Design and Application of a New Splitter Plate Pressure Probe for Wind Tunnel Flow Measurements

Journal of Mechanics Engineering and Automation 2019年第6期9卷 188-192页

作者： kasim biber Department of Mechanical Engineering Faculty of EngineeringArchitecture and DesignBartin UniversityBartin 74100Turkey

A new siplitter plate presure probe was developed for flow field measurements on an airfoil with slotted flap in a low speed wind tunnel with 7 by 10 ft test section. Wind tunnel tests were conducted at a Reynolds number of 2.2 million and Mach number of 0.13. The splitter plate was made of aluminum and had pressure taps on its one side. The probe can make many measurements in the plane of the plate simultaneously by using these pressure tabs. It was supported by a traversing strut in the wind tunnel and surveyed the flow field on the airfoil upper surface. Measured pressures were presented by isobars of coefficients. These isobars were connected with the pressure coefficients distributed over the airfoil. Results of splitter plate pressure probe compare well with other single-point measuring probes. However, results show that no matter how small the probe, its presence in the flow causes a disturbance, especially in the highly time-dependent separated flow regions.

关键词： Splitter plate-pressure probe flow field pressures wind tunnel instrumentation flow field isobars multi-element

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Transonic Airfoil Design and Optimization for an Unmanned Air Vehicle Concept

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Journal of Mechanics Engineering and Automation 2019年第6期9卷 193-202页

作者： kasim biber Trenton White Department of Mechanical Engineering Faculty of EngineeringArchitecture and DesignBartin UniversityBartin 74100Turkey US Air Force Research Laboratory Wright Patterson Air Force BaseOhio 45433-7542USA

Design,optimization and analysis of a new energy efficient 16%thick transonic airfoil were completed for a notional air vehicle *** airfoil specifications included a range of Reynolds number per foot from 1.7 million to 2.5 million and Mach number from 0.4 to *** optimization in geometry and inverse design modules of the airfoil analysis program MSES were used to design a new 16%thick reference *** performance of the reference airfoil was then optimized with an objective of minimizing drag coefficient for 7 design points with conflicting requirements in Reynolds and Mach number by using the MSES/LINDOP *** optimization results in an upward shift of drag bucket in the direction of higher lift *** surface pressure distribution and Mach contour plots show that supersonic compression waves on airfoil surface are terminated at Mach 0.78 with a normal shock wave and associated flow separation,which causes not only a decrease of the maximum suction pressure,but also a decrease in lift and increase in drag *** new optimized airfoil shows robust performance when operating within the specified design constraints.

关键词： Airfoil optimization airfoil design transonic airfoils shock flows compression waves.

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