[12] Rogers, S. E. <strong>and</strong> Kwak, D., “An Upwind Differencing Scheme <strong>for</strong> the Steady-state Incompressible Navier-Stokes Equations,” NASA TM 101051, November 1988. [13] Rogers, S. E. <strong>and</strong> Kwak, D., “An Upwind Differencing Scheme <strong>for</strong> the Time Accurate Incompressible Navier-Stokes Equations,” AIAA Journal, Vol. 28, No. 2, 1990, pp. 253-262. [14] Chorin, Alex<strong>and</strong>re Joel, “A Numerical Method <strong>for</strong> Solving Incompressible Viscous Flow Problems,” Journal of Computational Physics, Vol. 2, No. 1, 1967. [15] Thom, A., Swart, P., “The Forces on an Aerofoil at Very <strong>Low</strong> Speeds,” Journal of the Royal Aeronautical Society, Vol. 44, pp. 761-770, 1940. [16] Drela, M., Giles, M.B., “ISES - A Two-Dimensional Viscous <strong>Aerodynamics</strong> <strong>Design</strong> <strong>and</strong> Analysis Code,” AIAA Paper 87-0424, January 1987. [17] Schlichting, Hermann, Boundary-Layer Theory, 7th ed., McGraw-Hill, New York, 1979. [18] Strat<strong>for</strong>d, B. S., Aeronautical Research Council R. & M. 3002, 1954. [19] Curle, N. <strong>and</strong> Skan, S. W., Aeronautical Quarterly, No. 8, 1957, pp. 257. [20] Thwaites, B., Aeronautical Quarterly, No. 1, 1949, pp. 245. [21] Abbot, Ira H. <strong>and</strong> Von Doenhoff, Albert E., Theory of Wing Sections, Dover Publications Inc., New York, 1959. [22] Maughmer, Mark D., Somers, Dan M., “<strong>Design</strong> <strong>and</strong> Experimental Results <strong>for</strong> a High-Altitude, Long Endurance Airfoil,” Journal of Aircraft, Vol. 26, No. 2, 1989, pp. 148-153. [23] Akima, Hiroshi, “A Method of Univariate Interpolation that Has the Accuracy of a Third-Degree Polynomial,” ACM Transactions on Mathematical Software, Vol. 17, No. 3, 1991, pp. 341-366. [24] Nelder, J. A., Mead, R., “A Simplex Method <strong>for</strong> Function Minimization,” Computer Journal, Vol. 7, 1965, pp. 308-313. [25] Glauert, H., The Elements of Aerofoil <strong>and</strong> Airscrew Theory, Cambridge University Press, London, 1948. [26] McCormick, Barnes W. Jr., <strong>Aerodynamics</strong> of V/STOL <strong>Flight</strong>, Dover Publications Inc., New York, 1999. [27] Johnson, W., Helicopter Theory, Dover Publications Inc., New York, 1994. 178
[28] Lamb, Sir Horace, Hydrodynamics, Cambridge University Press, Cambridge, United Kingdom, 1997. [29] Kunz, Peter J., “Development of a Software Package <strong>for</strong> the Assessment of High Per<strong>for</strong>mance Sailplanes,” Master of Science Thesis, Department of Aerospace Engineering, Pennsylvania State University, University Park, Pennsylvania, August 1997, pp. 29-30, 43-51. [30] Gill, Murray, <strong>and</strong> Saunders, “User’s Guide <strong>for</strong> SNOPT 5.3: A Fortran Package <strong>for</strong> Large-scale Nonlinear Programming,” Technical Report SOL 98-1, Department of Engineering Economic Systems <strong>and</strong> Operations Research, Stan<strong>for</strong>d University, Stan<strong>for</strong>d, CA, May 1998. [31] A.G. Cooper, S. Kang, J. W. Kietzman, F. B. Prinz, J. L. Lombardi <strong>and</strong> L. Weiss, “Automated Fabrication of Complex Molded Parts Using Mold SDM,” Proceedings of the Solid Free<strong>for</strong>m Fabrication Symposium, University of Texas at Austin, Austin, Texas, August 1998. [32] Y. Cheng, “Fabrication Methods <strong>for</strong> a Mesoscopic Flying Vehicle,” Ph.D. thesis, Stan<strong>for</strong>d University, Stan<strong>for</strong>d, CA, June 2001. [33] Buning, P. G., Jesperson, D. C., Pulliam, T. H., Chan, W. M., Slotnick, J. P., Krist, S. E., <strong>and</strong> Renze, K. J., “OVERFLOW User's Manual, Version 1.8g,” NASA Langley Research Center, March 1999. [34] Meakin, R., “Composite Overset Structured Grids,” H<strong>and</strong>book of Grid Generation, edited by Thompson, J. F., Soni, B. K., <strong>and</strong> Weatherill, N. P., CRC Press, Washington, DC, 1999, pp. 11-1 to 11-19. [35] Meakin, R. L., <strong>and</strong> Wissink, A. M., “Unsteady Aerodynamic Simulation of Static <strong>and</strong> Moving Bodies Using Scalable Computers,” AIAA-99-3302, Proc. 14th AIAA Computational Fluid Dynamics Conf., Norfolk VA, July 1999 pp. 469-483. [36] Strawn, R. C. <strong>and</strong> Djomehri, M. J., “Computational Modeling of Hovering Rotors <strong>and</strong> Wake <strong>Aerodynamics</strong>,” presented at the AHS 57th Annual Forum, Washington, DC, May 9-11, 2001. [37] Chan, William M. <strong>and</strong> Buning, Pieter G., “User’s Manual <strong>for</strong> FOMOCO Utilities - Force <strong>and</strong> Moment Computation Tools <strong>for</strong> Overset Grids,” NASA TM-110408, 1996. [38] Myonic AG, Eckweg 8, PO Box 6121, CH – 2500 Biel-Bienne 6. [39] Astro <strong>Flight</strong> Incorporated, 13311 Beach Ave., Marina Del Rey, CA 90292. [40] Internet Technical Library, MicroMo Electronics Incorporated, 14881 Evergreen Ave.,Clearwater, FL 33762-3008. 179
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AERODYNAMICS AND DESIGN FOR ULTRA-L
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I certify that I have read this dis
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Abstract Growing interest in micro-
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Nomenclature A Rotor disk area B Nu
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τ Shear stress ω, Ω Rotor angul
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Contents Acknowledgments...........
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Chapter 5..........................
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List of Tables 3.1 Effect of Airfoi
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List of Figures 2.1 Comparison of I
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5.6 Small test fixture in the large
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6.38 Predicted spanwise thrust dist
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Chapter 1 Introduction 1.1 Looking
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Chapter 1 wind-tunnel facilities an
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1.3 Summary of Contributions Chapte
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Chapter 2 Two-Dimensional Computati
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Chapter 2 The artificial compressib
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Chapter 2 The control volume method
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2.2.4 Comparison with Experiment Th
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Chapter 2 to diverge if significant
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2.4 Flow Field Assumptions The INS2
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Chapter 2 The results of these time
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Chapter 3 Analysis and Design of Ai
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Chapter 3 adverse gradient in the p
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The canonical pressure coefficient
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Chapter 3 reaches α=5.0 and a lift
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Cl 0.50 0.40 0.30 0.20 0.10 0.00 -0
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Re=6000 result due to Reynolds numb
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FIGURE 3.10 NACA 0002 and NACA 0008
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C l C l 0.8 0.7 0.6 0.5 0.4 0.3 0.2
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Chapter 3 The maximum L/D for all n
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3.5 Effect of Leading Edge Shape an
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C l 0.60 0.50 0.40 0.30 0.20 0.10 0
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Chapter 3 prominent droop near the
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Chapter 3 Small improvements in lif
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Chapter 4 Hybrid Method for Rotor D
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Q/r D L Chapter 4 FIGURE 4.1 Typica
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4.2.3 Elimination of Trigonometric
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Chapter 4 applications of interest
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4.2.7 The Distinction Between the A
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Chapter 4 Two input parameters dete
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Chapter 4 simplification, particula
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4.3.3 Conservation of Angular Momen
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Chapter 4 moves downstream is less
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Chapter 4 of the pitch angle at the
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FIGURE 4.6 Converged wake streamlin
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Chapter 4 idealized models. The met
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Chapter 5 Overview of Experimental
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1. Substrate Preparation 2. Polymer
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Chapter 5 surface finish and aids i
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FIGURE 5.5 Small test fixture in th
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Chapter 5 The direct influence of t
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FIGURE 5.9 Large test fixture in th
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5.4.1 Motor Power Supply All tests
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Chapter 5 or roughly (+/-) 25% of t
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Chapter 5 newly forming blade tip v
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FIGURE 5.14 Near-body grid geometry
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Chapter 6 Design Examples and Compa
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Chapter 6 capable of speeds up to 1
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FIGURE 6.2 The Astro Flight Firefly
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t/c 0.5 0.4 0.3 0.2 0.1 0.0 FIGURE
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c/R 0.0 0.2 0.4 0.6 0.8 1.0 r/R Cha
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FIGURE 6.10 Carbon-fiber two-blade
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Power Req. (W) 3.5 3.0 2.5 2.0 1.5
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Chapter 6 TABLE 6.1 Comparison of p
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Electro-mechanical Efficiency 0.20
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these variations and possible solut
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upper and lower surface corners of
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Chapter 6 The Sample-1 rotor exhibi
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The static deformations described i
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Q( r) This problem is solved as a l
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Structural Analyses Chapter 6 The m
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Aero-Structural Twist (deg.) 0.00 -
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