2 NACA 12 airfoil drag coefficient results. 1 NACA 212 with 212 flap lift coefficient results NACA 212 with 212 flap drag coefficient results NACA 212 with 212 flap L/D ratio results NACA 212 with 212 flap moment coefficient results NLF(1)-416 airfoil lift coefficient results NLF(1)-416 airfoil drag coefficient results NLF(1)-416 airfoil moment coefficient results NACA 12 airfoil lift coefficient results. 1 RelativePosition TransitionLocation ImprovedWind TunnelModel UncertaintyAnalysisandDataRepeatability SpanwiseDragVariation CONCLUSIONS REFERENCES APPENDIXA VITAħ vii LIST OF FIGURES Page Fig. 9 Instrumentation DataReduction Flow Visualization EXPERIMENTAL RESULTSAND DISCUSSION. 2Ħ vi Page RelativeAngle Modified Profile Shapes AG91Airfoil ComparisonWith OtherAirfoils TransitionLocation EXPERIMENTAL TOOLS Wind Tunnel Airfoil Model. 9 MCARFA Program Accuracy PROFIL Background PROFIL Potential Flow Solution PROFIL Boundary Layer Solution PROFIL Accuracy NUMERICAL RESULTS AND DISCUSSION. They have helped, pushed, supported, and loved me more than they will ever know.ĥ V TABLE OF CONTENTS ABSTRACT. I would like to close by thanking my wife Kathy and son Kyle whom are my reason for life itself. I am etemally indebted to my parents Harvey and Ila Steen for teaching me everything really important in life and supporting me in anything I ever chose to do. Finally, I would like to thank my family. I feel extremely fortunate to have had the opportunity to work with and learn from such a truly exceptional man. Oran Nicks, who served not only as my boss, but also as a trusted advisor and friend. I also wish to thank the staff of the Texas A&M University Low Speed Wind Tunnel for their support and friendship through the completion of my education and the start of my professional career. I thank them all for supporting me through the extended period of time required for me to finish this thesis part time and for giving me three outstanding examples of professional success and personal character. A great debt of thanks is due to the members of my Advisory Committee Dr. Bill Cleary of Ciba-Geigy Corporation for donating the Ren Shape used in the wind tunnel model construction. of NASA Langley for providing a copy of the MCARFA computer code and Mr. Card at the NASA Langley Research Center for supporting the effort. Comparisons between the numerical and experimental data, the effects of the relative position and angle of the two elements, and Reynolds number variations from 8x15 to x16 for the optimum geometry case are presented.Ĥ iv ACKNOWLEDGMENTS This material is based upon work supported by the NASA-Langley Research Center under Grant No. Section surface pressure, wake survey, transition location, and flow visualization results were obtained in the Texas A&M University Low Speed Wind Tunnel. Numerical results show a nearly 11.75% decrease in overall wing drag with no increase in stall speed at sailplane cruise conditions when compared to a wing based on an efficient single element airfoil. The airfoil was numerically developed utilizing the NASA Langley Multi-Component Airfoil Analysis computer code running on a personal computer. The airfoil was designed to improve the cruise lift-to-drag ratio while maintaining an appropriate landing capability when compared to conventional airfoils. The airfoil design consists of a primary element and an independent secondary element with a primary to secondary chord ratio of three to one. Korkan Numerical and experimental results are presented for a new two element, fixed geometry natural laminar flow airfoil optimized for cruise Reynolds numbers on the order of three million. (August 1994) Gregory Glen Steen, B.S., Texas A&M University Co-Chairs of Advisory Committee: Dr. Haisler (Head of Department) August 1994 Major Subject: Aerospace Engineeringģ 111 ABSTRACT A Two Element Laminar Flow Airfoil Optimized for Cruise. Korkan (Co-Chair of Committee) (Co-Chair of Committee) Gerald _/. 1 A TWO ELEMENT LAMINAR FLOW AIRFOIL OPTIMIZED FOR CRUISE A Thesis by GREGORY GLEN STEEN Submitted to the Office of Graduate Studies of Texas A&M University in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE August 1994 Major Subject: Aerospace EngineeringĢ A TWO ELEMENT LAMINAR FLOW AIRFOIL OPTIMIZED FORCRUISE A Thesis by GREGORYGLEN STEEN Submittedto TexasA&M University in partialfulfillment of the requirements for the degree of MASTER OF SCIENCE Approved as to style and content by: / Leland A.
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