Aerodynamic Analyses Of Skins For Morphing Wings

Fadi Magdy R Mishriky

doi:10.32920/ryerson.14653551

Abstract

Aerodynamic Analyses Of Skins For Morphing Wings

Highlights

Aircraft Morphing Technology: It was on December 17, 1903, when Oliver Wright was sitting inside a heavier-than-air power manned machine, and his brother, Wilbur Wright, was running beside their flyer, ensuring that the wing tips will not tilt and hit the ground
The lifting capabilities of the airfoil dropped from 93.7% to 73.4% as the wrinkle height increased from ε = 0.002 C to ε = 0.01 C, with an approximate increase of 4% for every 0.002 C increase in the wrinkle height
For cases with a wrinkle installed at X = 0.75 C, the lift-todrag ratio dropped to 93.4% and 35.1% for wrinkle heights of ε = 0.002 C and ε = 0.01 C, respectively. These results presented in figures (5.17), (5.19) and (5.22) show that the aerodynamic performance of wrinkled airfoils is significantly lower than the performance of a clean airfoil at the same flight conditions, and that introducing a single wrinkle to the upper surface of the airfoil has a prominent degrading effect on its performance

Summary

Introduction

Aircraft Morphing Technology: It was on December 17, 1903, when Oliver Wright was sitting inside a heavier-than-air power manned machine, and his brother, Wilbur Wright, was running beside their flyer, ensuring that the wing tips will not tilt and hit the ground. Among the validation test cases that the authors ran in [30] is the flow over the Pratt and Whitney PAK-B low pressure turbine blade This profile encounters a laminar separation bubble on the suction side of the airfoil followed by a subsequent reattachment due to the transition of the boundary layer over the laminar separation bubble. The transition of the boundary layer occurs at the free shear layer due to the inflected velocity profile of the laminar separation bubble This is the exact same transition mechanism that is experienced in case of flows over rectangular cavities. Based on the boundary conditions, the flow may include shear layer separation, shock waves, entrapped vortices, secondary flows, boundary layer transition and flow-acoustic resonance The latter phenomenon of hydrodynamic resonance has intrigued the interest of researchers to explore the interaction between the separated shear layer and the cavity edges in all the three common methods, namely, experimentally, analytically and numerically

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Conclusion