Aung Myo Thu | Meiktila Technological University (original) (raw)
Address: Myanmar Aerospace Engineering University, Meiktila, Myanmar.
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Swiss Federal Institute of Technology (ETH) & University of Zurich
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Papers by Aung Myo Thu
Journal of Aerospace Engineering, 2012
AbstractAn investigation of the flow field around a double-delta wing was carried out at the Aero... more AbstractAn investigation of the flow field around a double-delta wing was carried out at the Aerodynamics Analysis and Design Laboratory's (AADL) water tunnel facility. The model has a sharp leading edge and 76/40° configuration, which is representative of current fighter aircraft. The experiments were conducted at Reynolds numbers of 10,000 and 15,000. The dye injection technique was utilized to analyze the flow. A comparison of the vortical flow structure and the bursting point locations was done for a Reynolds number of 15,000 and found to be in reasonable agreement. The major objective of this experiment was to study the effect of the angle of attack (AOA) and Reynolds number on the vortical flow structure. In this flow visualization result, the dominant feature of the AOA and Reynolds number effect on the vortical flow structure over the double-delta wing has been observed. With increasing Reynolds number, the distance between the vortex trajectory and the model surface becomes smaller. As the AOA in...
International Journal of Aviation, Aeronautics, and Aerospace, 2018
The unsteady flow field around oscillating OA-209 airfoil at a Reynolds number of 3.5×105 were in... more The unsteady flow field around oscillating OA-209
airfoil at a Reynolds number of 3.5×105 were investigated. Three
different reduced frequencies were tested in order to see how it
affects the hysteresis loop of an airfoil. At a reduced frequency of
0.05 the deep dynamic stall phenomenon was observed. Lift
overshooting was observed as a result of dynamic stall vortex (DSV)
shedding. Further investigation was carried out to find out the cause
of DSV formation and shedding over airfoil. Particle image
velocimetry (PIV) and CFD tools were used and it was found out that
dynamic stall separation (DSS), which is separated from leading edge
separation (LES) and trailing edge separation (TES), triggered the
dynamic stall vortex (DSV).
The Korean Society for Aeronautical and Space Sciences, 2011 Fall Conference.
The calibration tests based on the ISSI BF 400 paint have been shown and the obstacles were addre... more The calibration tests based on the ISSI BF 400 paint have been shown and the obstacles were addressed making these successful measurements. There are slight changes in the calibration curves according to different reference temperature and pressure values. The effects of these changes on the interpretation of delta wing flow are well discussed in this paper.
An investigation of the flow field around a double-delta wing was carried out at the Aerodynamics... more An investigation of the flow field around a double-delta wing was carried out at the Aerodynamics Analysis and Design
Laboratory’s (AADL) water tunnel facility. The model has a sharp leading edge and 76=40 configuration, which is representative of current
fighter aircraft. The experiments were conducted at Reynolds numbers of 10,000 and 15,000. The dye injection technique was utilized to analyze
the flow.Acomparison of the vortical flow structure and the bursting point locations was done for a Reynolds number of 15,000 and found to be
in reasonable agreement. The major objective of this experiment was to study the effect of the angle of attack (AOA) and Reynolds number on
the vortical flow structure. In this flow visualization result, the dominant feature of the AOA and Reynolds number effect on the vortical flow
structure over the double-delta wing has been observed. With increasing Reynolds number, the distance between the vortex trajectory and the
model surface becomes smaller. As the AOA increases, the intertwining or coiling up features cannot be seen and the vortex bursting point
locations move upstream. The distance between the vortical streakline and the model surface becomes larger with increasing AOA. The
crossover point of the main and strake wing vortices also depends on the AOA.
Journal of Aerospace Engineering, 2012
AbstractAn investigation of the flow field around a double-delta wing was carried out at the Aero... more AbstractAn investigation of the flow field around a double-delta wing was carried out at the Aerodynamics Analysis and Design Laboratory's (AADL) water tunnel facility. The model has a sharp leading edge and 76/40° configuration, which is representative of current fighter aircraft. The experiments were conducted at Reynolds numbers of 10,000 and 15,000. The dye injection technique was utilized to analyze the flow. A comparison of the vortical flow structure and the bursting point locations was done for a Reynolds number of 15,000 and found to be in reasonable agreement. The major objective of this experiment was to study the effect of the angle of attack (AOA) and Reynolds number on the vortical flow structure. In this flow visualization result, the dominant feature of the AOA and Reynolds number effect on the vortical flow structure over the double-delta wing has been observed. With increasing Reynolds number, the distance between the vortex trajectory and the model surface becomes smaller. As the AOA in...
International Journal of Aviation, Aeronautics, and Aerospace, 2018
The unsteady flow field around oscillating OA-209 airfoil at a Reynolds number of 3.5×105 were in... more The unsteady flow field around oscillating OA-209
airfoil at a Reynolds number of 3.5×105 were investigated. Three
different reduced frequencies were tested in order to see how it
affects the hysteresis loop of an airfoil. At a reduced frequency of
0.05 the deep dynamic stall phenomenon was observed. Lift
overshooting was observed as a result of dynamic stall vortex (DSV)
shedding. Further investigation was carried out to find out the cause
of DSV formation and shedding over airfoil. Particle image
velocimetry (PIV) and CFD tools were used and it was found out that
dynamic stall separation (DSS), which is separated from leading edge
separation (LES) and trailing edge separation (TES), triggered the
dynamic stall vortex (DSV).
The Korean Society for Aeronautical and Space Sciences, 2011 Fall Conference.
The calibration tests based on the ISSI BF 400 paint have been shown and the obstacles were addre... more The calibration tests based on the ISSI BF 400 paint have been shown and the obstacles were addressed making these successful measurements. There are slight changes in the calibration curves according to different reference temperature and pressure values. The effects of these changes on the interpretation of delta wing flow are well discussed in this paper.
An investigation of the flow field around a double-delta wing was carried out at the Aerodynamics... more An investigation of the flow field around a double-delta wing was carried out at the Aerodynamics Analysis and Design
Laboratory’s (AADL) water tunnel facility. The model has a sharp leading edge and 76=40 configuration, which is representative of current
fighter aircraft. The experiments were conducted at Reynolds numbers of 10,000 and 15,000. The dye injection technique was utilized to analyze
the flow.Acomparison of the vortical flow structure and the bursting point locations was done for a Reynolds number of 15,000 and found to be
in reasonable agreement. The major objective of this experiment was to study the effect of the angle of attack (AOA) and Reynolds number on
the vortical flow structure. In this flow visualization result, the dominant feature of the AOA and Reynolds number effect on the vortical flow
structure over the double-delta wing has been observed. With increasing Reynolds number, the distance between the vortex trajectory and the
model surface becomes smaller. As the AOA increases, the intertwining or coiling up features cannot be seen and the vortex bursting point
locations move upstream. The distance between the vortical streakline and the model surface becomes larger with increasing AOA. The
crossover point of the main and strake wing vortices also depends on the AOA.