Aerodynamics and Design for Ultra-Low Reynolds Number Flight

More documents

Recommendations

Info

xviii
List of Figures 2.1 Comparison of INS2d on-body and control volume drag values for the NACA 4402. ............................................................................................... 11 2.2 Results of a grid-sizing study for the NACA 0002 at Re=6000............................. 12 2.3 Comparison of computed and experimental Cd for the R.A.F. 6 and R.A.F. 6a airfoils. ............................................................................................ 14 2.4 MSES and INS2d predicted lift curves for the NACA 4402 and NACA 4404. Flow is fully laminar and Re=1000........................................................................ 16 2.5 MSES and INS2d predicted drag polars for the NACA 4402 and NACA 4404. Flow is fully laminar and Re=1000........................................................................ 16 2.6 INS2d time-accurate analyses of an impulsively started NACA 4402 at Re=6000. ............................................................................................................ 18 3.1 Zero lift C p distributions for the NACA 0008. ...................................................... 23 3.2 Zero lift C p distributions for the NACA 0002. ...................................................... 24 3.3 Cp distributions for the NACA 0008 at α=2.0. At Re=6000, trailing edge separation is imminent, but the Re=2000 case remains fully attached.......... 26 3.4 Lift curves for the NACA 0002 and NACA 0008. ................................................ 27 3.5 Streamlines for the NACA 0008 at Re=6000. The aft 45% of the airfoil is visible. The point of separation is indicated by an arrow.................................. 28 3.6 Streamlines for the NACA 0008 at Re=2000. The aft 45% of the airfoil is visible. The point of separation is indicated by an arrow.................................. 29 3.7 Drag polars for uncambered NACA 4-digit sections across a range of thickness. 31 3.8 Lift curves for uncambered NACA 4-digit sections, Re=6000.............................. 33 3.9 Lift curves for uncambered NACA 4-digit sections, Re=2000.............................. 34 3.10 NACA 0002 and NACA 0008 boundary layer development at Re=6000. ............ 35 3.11 Lift curves for the NACA 4402 and NACA 0002. ................................................ 37 3.12 Drag polars for the NACA 4402 and NACA 0002. ............................................... 37 xix
Page 1 and 2: AERODYNAMICS AND DESIGN FOR ULTRA-L
Page 3: I certify that I have read this dis
Page 7 and 8: Abstract Growing interest in micro-
Page 9 and 10: Nomenclature A Rotor disk area B Nu
Page 11 and 12: τ Shear stress ω, Ω Rotor angul
Page 13 and 14: Contents Acknowledgments...........
Page 15 and 16: Chapter 5..........................
Page 17: List of Tables 3.1 Effect of Airfoi
Page 21 and 22: 5.6 Small test fixture in the large
Page 23 and 24: 6.38 Predicted spanwise thrust dist
Page 25 and 26: Chapter 1 Introduction 1.1 Looking
Page 27 and 28: Chapter 1 wind-tunnel facilities an
Page 29 and 30: 1.3 Summary of Contributions Chapte
Page 31 and 32: Chapter 2 Two-Dimensional Computati
Page 33 and 34: Chapter 2 The artificial compressib
Page 35 and 36: Chapter 2 The control volume method
Page 37 and 38: 2.2.4 Comparison with Experiment Th
Page 39 and 40: Chapter 2 to diverge if significant
Page 41 and 42: 2.4 Flow Field Assumptions The INS2
Page 43 and 44: Chapter 2 The results of these time
Page 45 and 46: Chapter 3 Analysis and Design of Ai
Page 47 and 48: Chapter 3 adverse gradient in the p
Page 49 and 50: The canonical pressure coefficient
Page 51 and 52: Chapter 3 reaches α=5.0 and a lift
Page 53 and 54: ��
Page 55 and 56: Cl 0.50 0.40 0.30 0.20 0.10 0.00 -0
Page 57 and 58: Re=6000 result due to Reynolds numb
Page 59 and 60: FIGURE 3.10 NACA 0002 and NACA 0008
Page 61 and 62: C l C l 0.8 0.7 0.6 0.5 0.4 0.3 0.2
Page 63 and 64: Chapter 3 The maximum L/D for all n
Page 65 and 66: 3.5 Effect of Leading Edge Shape an
Page 67 and 68: C l 0.60 0.50 0.40 0.30 0.20 0.10 0
Page 69 and 70:
Chapter 3 prominent droop near the
Page 71 and 72:
Chapter 3 Small improvements in lif
Page 73 and 74:
Chapter 4 Hybrid Method for Rotor D
Page 75 and 76:
Q/r D L Chapter 4 FIGURE 4.1 Typica
Page 77 and 78:
4.2.3 Elimination of Trigonometric
Page 79 and 80:
Chapter 4 applications of interest
Page 81 and 82:
4.2.7 The Distinction Between the A
Page 83 and 84:
Chapter 4 Two input parameters dete
Page 85 and 86:
Chapter 4 simplification, particula
Page 87 and 88:
4.3.3 Conservation of Angular Momen
Page 89 and 90:
Chapter 4 moves downstream is less
Page 91 and 92:
Chapter 4 of the pitch angle at the
Page 93 and 94:
FIGURE 4.6 Converged wake streamlin
Page 95 and 96:
Chapter 4 idealized models. The met
Page 97 and 98:
��
Page 99 and 100:
Chapter 5 Overview of Experimental
Page 101 and 102:
1. Substrate Preparation 2. Polymer
Page 103 and 104:
Chapter 5 surface finish and aids i
Page 105 and 106:
FIGURE 5.5 Small test fixture in th
Page 107 and 108:
Chapter 5 The direct influence of t
Page 109 and 110:
FIGURE 5.9 Large test fixture in th
Page 111 and 112:
5.4.1 Motor Power Supply All tests
Page 113 and 114:
Chapter 5 or roughly (+/-) 25% of t
Page 115 and 116:
Chapter 5 newly forming blade tip v
Page 117 and 118:
FIGURE 5.14 Near-body grid geometry
Page 119 and 120:
Chapter 6 Design Examples and Compa
Page 121 and 122:
Chapter 6 capable of speeds up to 1
Page 123 and 124:
FIGURE 6.2 The Astro Flight Firefly
Page 125 and 126:
t/c 0.5 0.4 0.3 0.2 0.1 0.0 FIGURE
Page 127 and 128:
c/R 0.0 0.2 0.4 0.6 0.8 1.0 r/R Cha
Page 129 and 130:
FIGURE 6.10 Carbon-fiber two-blade
Page 131 and 132:
Power Req. (W) 3.5 3.0 2.5 2.0 1.5
Page 133 and 134:
Chapter 6 TABLE 6.1 Comparison of p
Page 135 and 136:
Electro-mechanical Efficiency 0.20
Page 137 and 138:
these variations and possible solut
Page 139 and 140:
upper and lower surface corners of
Page 141 and 142:
Chapter 6 The Sample-1 rotor exhibi
Page 143 and 144:
The static deformations described i
Page 145 and 146:
Q( r) This problem is solved as a l
Page 147 and 148:
Structural Analyses Chapter 6 The m
Page 149 and 150:
Aero-Structural Twist (deg.) 0.00 -
Page 151 and 152:
Thrust (g) 5 4 3 2 1 0 10000 20000
Page 153 and 154:
Thrust (g) 4.5 4.0 3.5 3.0 2.5 2.0
Page 155 and 156:
Torque per unit span (g cm) 0.75 0.
Page 157 and 158:
Thrust per unit span (g) 3.5 3.0 2.
Page 159 and 160:
V total / ωr 1.0 0.9 0.8 Classical
Page 161 and 162:
Torque per unit span (g cm) 0.75 0.
Page 163 and 164:
Chapter 6 Recall that this rotor wa
Page 165 and 166:
Incidence (deg.) 30 25 20 15 10 5 0
Page 167 and 168:
Thrust (g) 9 8 7 6 5 4 3 2 38000 40
Page 169 and 170:
x/R 0.4 0.2 0.0 -0.2 Chapter 6 FIGU
Page 171 and 172:
Cl 0.64 0.62 0.60 0.58 0.0 0.2 0.4
Page 173 and 174:
C f 0.125 0.100 0.075 0.050 0.025 0
Page 175 and 176:
Chapter 7 Micro-Rotorcraft Prototyp
Page 177 and 178:
This vehicle does not currently inc
Page 179 and 180:
FIGURE 7.2 The 65g prototype electr
Page 181 and 182:
7.4 The 150g Prototype Chapter 7 Th
Page 183 and 184:
At hover, with a mass of 153g, the
Page 185 and 186:
Using the 150g prototype as an exam
Page 187 and 188:
Chapter 7 Basic rotor theory has be
Page 189 and 190:
most of the blade. These values are
Page 191 and 192:
Chapter 7 For large scale helicopte
Page 193 and 194:
Chapter 8 Conclusions and Recommend
Page 195 and 196:
the significant performance gains a
Page 197 and 198:
Chapter 8 are also opportunities to
Page 199 and 200:
Chapter 8 formation flight, and man
Page 201 and 202:
References [1] Spedding, G.R., Liss
Page 203 and 204:
[28] Lamb, Sir Horace, Hydrodynamic
show all

Aerodynamics and Design for Ultra-Low Reynolds Number Flight

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?