- Page 1 and 2: AERODYNAMICS AND DESIGN FOR ULTRA-L
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- Page 10 and 11: Q Rotor torque RPM Revolutions per
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- Page 14 and 15: Chapter 3 .........................
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- Page 20 and 21: 3.13 Lift curves for 2% and 4% camb
- Page 22 and 23: 6.20 Comparison of laser scanning i
- Page 24 and 25: 7.5 Figure of merit as a function o
- Page 26 and 27: Chapter 1 Major problems have inclu
- Page 28 and 29: Chapter 1 dimensional steady aerody
- Page 30 and 31: Chapter 1 6
- Page 32 and 33: Chapter 2 What is being sought here
- Page 34 and 35: Chapter 2 Conventional airfoils hav
- Page 36 and 37: Chapter 2 2.2.3 Grid Sizing Study A
- Page 38 and 39: Chapter 2 14 C d 0.28 0.24 0.20 0.1
- Page 40 and 41: Chapter 2 16 Cl 0.8 0.7 0.6 0.5 0.4
- Page 42 and 43: Chapter 2 but does not represent a
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- Page 46 and 47: Chapter 3 extrapolation based on hi
- Page 48 and 49: Chapter 3 24 Cp -0.2 -0.1 0.0 0.1 0
- Page 50 and 51: Chapter 3 26 Cp -0.6 -0.4 -0.2 0.0
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Chapter 3 3.3 Maximum Section Thick
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Chapter 3 laminar flat plate drag d
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Chapter 3 34 Cl 0.60 0.50 0.40 0.30
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Chapter 3 with increasing camber. T
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Chapter 3 Further analyses have inv
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Chapter 3 40 Cl 0.8 0.7 0.6 0.5 0.4
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Chapter 3 42 The primary effect of
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Chapter 3 the number of variables c
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Chapter 3 46 y/c 0.07 0.06 0.05 0.0
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Chapter 3 The optimized design of t
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Chapter 4 4.2 Derivation of the Rot
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Chapter 4 Neglecting for now any co
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Chapter 4 4.2.4 Prandtl Tip Loss Co
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Chapter 4 where: Note that if the P
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Chapter 4 4.3 Viscous Swirl Modelin
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Chapter 4 60 FIGURE 4.3 Effect of R
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Chapter 4 modeled as a Gaussian dis
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Chapter 4 Beyond the assumptions in
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Chapter 4 This equation assumes tha
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Chapter 4 68 x/R 2 1.5 1 0.5 0 0.5
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Chapter 4 Here, u is the constant d
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Chapter 4 lift distribution, and ro
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Chapter 4 74
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Chapter 5 5.2 Rotor Manufacturing 5
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Chapter 5 78 ���� FIGURE 5.
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Chapter 5 The test fixtures for mea
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Chapter 5 82 FIGURE 5.6 Small test
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Chapter 5 power and efficiency curv
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Chapter 5 86 FIGURE 5.10 Large test
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Chapter 5 is much more challenging
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Chapter 5 RPM with a standard devia
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Chapter 5 The micro-rotor case that
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Chapter 5 but the no slip condition
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Chapter 6 Prandtl tip loss model an
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Chapter 6 efficiencies are only a p
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Chapter 6 with its chord and incide
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Chapter 6 in the rotor geometry, oc
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Chapter 6 6.3.3 Two-Blade Ten Inch
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Chapter 6 analysis method are prese
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Chapter 6 108 Thrust (g) 5 4 3 2 1
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Chapter 6 110 Voltage (V) Current (
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Chapter 6 10% for the other samples
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Chapter 6 6.5 Effects of Structural
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Chapter 6 116 Incidence (deg.) 20 1
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Chapter 6 118 Incidence (deg.) 20 1
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Chapter 6 The governing equation re
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Chapter 6 The importance of the ope
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Chapter 6 124 Aero-Structural Twist
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Chapter 6 126 Aero-Structural Twist
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Chapter 6 Similar results are found
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Chapter 6 computational fluid dynam
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Chapter 6 6.7 Modeling Effects on P
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Chapter 6 The inflow angle variatio
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Chapter 6 four-blade 2.5cm diameter
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Chapter 6 138 V total / ωr φ (deg
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Chapter 6 method with the contracte
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Chapter 6 output power of the motor
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Chapter 6 6.8.2 Effect of Wake Mode
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Chapter 6 146 Incidence (deg.) 30 2
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Chapter 6 in boundary layer thickne
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Chapter 6 Unfortunately there does
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Chapter 7 Chapter 6. Four Myonic 5m
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Chapter 7 required for hover is 16V
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Chapter 7 Since this prototype was
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Chapter 7 158 TABLE 7.3 Mass alloca
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Chapter 7 160 TABLE 7.4 Summary of
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Chapter 7 efficiency is devastating
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Chapter 7 Similarly the thrust may
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Chapter 7 166 Rotor Solidity 0.10 0
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Chapter 7 168 Figure of Merit 0.8 0
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Chapter 8 performance ramifications
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Chapter 8 further investigation, bu
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Chapter 8 not been determined wheth
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Chapter 8 176
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[12] Rogers, S. E. and Kwak, D.,
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[41] WES-Technik GmbH, Klosterstr.