臺灣博碩士論文加值系統

本論文主要在利用合成噴流致動器提升機翼在過度區間氣動力之性能。首先使用熱線測速儀量測合成噴流致動器在不同激擾頻率下所產生的出口速度，對基本的合成噴流致動器有基礎的瞭解。在共振頻率下，量測到的出口速度會相對大於在其他頻率下所產生的出口速度。接著將10個合成噴流致動器裝置在機翼上表面10%弦長的距離，並使用六分力平衡儀量得致動器在不同頻率下開起及關閉時的升力及阻力變化。分析升、阻力變化對於不同激擾頻率的效果。激擾頻率為200Hz下對低攻角所產生的升力變化最有效果。激擾頻率在300到500Hz區間對於高攻角產生的升力變化較有效果。
在風洞實驗驗證致動器的效果後，改裝黑面琵鷺-100無人飛機的左翼，裝置20個致動器在機翼上表面進行實際飛行測試。飛測結果顯示，在500Hz的激擾頻率下，左翼的升力增加，對無人飛機產生一個向右滾轉的力矩並耦合產生向右偏航的力矩。歸納風洞實驗與飛測的有效激擾頻率，都相當接近於機翼表面的剪切層擾動的基礎頻率。

This thesis experimentally studies the application of synthetic jet actuator (SJA) made of piezoelectric (PZ) material in enhancing the aerodynamic performance at low Reynolds numbers. First of all, the fundamental properties of the SJA are investigated by the hot-wire anemometer used to measure the exit velocities of the SJA with different excitation frequency on the PZ material. At the resonance frequency, the exit velocity of the SJA is highest than others. Next, the wind tunnel experiment is conducted to measure the force acting on the wind tunnel model of the NACA 633-018 with the SJA excitation at on and off conditions. To analyze the lift and drag difference with different excitation frequency, 200Hz excitation case is more effective at the low angle of attack and for 300Hz~500Hz excitation case is suitable the high angle of attack.
Finally, for active flow control application of the synthetic jet actuator is realized in the Spoonbill-100 UAV flight test. There are twenty pieces of actuators installed on the left side of the main wing. The flight test results indicate that the excitation frequency at 500Hz is the only effective frequency to enhance the lift. Therefore, the extra lift will generate the roll moment coupled with the yaw moment in real flight test. In comparison with the wind tunnel experiment and flight test, the effective excitation frequencies are very close to the fundamental frequency of the shear layer disturbances of the wing tested.

CHINESE ABSTRACT I
ABSTRACT II
EXTENDED CHINESE ABSTRACT IV
ACKNOWLEDGMENT IX
CONTENTS X
LIST OF TABLES XII
LIST OF FIGURES XIII
NOMENCLATURE XIX
CHAPTER Ⅰ INTRODUCTION 1
1.1 AERODYNAMIC CHARACTERISTICS AT LOW REYNOLDS NUMBERS 2
1.1.1 Flow Properties 2
1.1.2 Laminar Separation Bubble 3
1.1.3 Hysteresis Phenomenon 4
1.2 SYNTHETIC JET ACTUATOR AND FLOW CONTROL 5
1.2.1 Flow Control on Boundary Layer Separation and Wing Stall 5
1.2.2 Principle and Application of Synthetic Jet Actuator 6
1.3 MOTIVATION AND OBJECTIVES 7
CHAPTER Ⅱ EXPERIMENTAL ARRANGEMENT 9
2.1 LOW SPEED WIND TUNNEL 9
2.2 EXPERIMENTAL APPARATUS 9
2.2.1 Pitot-Static Tube and Pressure Transducer 9
2.2.2 Force and Moment Measurement System 10
2.2.3 Flow Measurement System 11
2.3 UAV SYSTEM 14
2.3.1 Aerial Vehicle Design 14
2.3.2 Avionics System 17
2.3.3 Synthetic Jet Actuator System 19
2.4 TEST MODELS 20
2.4.1 Synthetic Jet Actuator Model 20
2.4.1 Wing Model 20
2.5 UNCERTAINTY ANALYSIS 21
CHAPTER Ⅲ RESULTS AND DISCUSSION 23
3.1 PARAMETERS FOR SYNTHETIC JET ACTUATOR 23
3.1.1 Effect of Excitation Waveform and Voltage 23
3.1.2 Velocity Response for SJA with Different Frequency 24
3.2 MEASUREMENT OF AERODYNAMIC LOADING WITH SJA 24
3.2.1 Test and verification wind tunnel model 24
3.2.2 Aerodynamic Performance with SJA 25
3.3 FLIGHT TEST 27
3.3.1 Flight Test Procedure 27
3.3.2 Flight Test Results 28
CHAPTER Ⅳ CONCLUDING REMARKS 29
REFERENCES 31
PUBLICATION LIST 100

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