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  • 1
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    Imaging Supersonic Aircraft Shock Waves (1997)
    In:  Other Sources
    Details
    Publication Date: 2011-08-23
    Description: A schlieren imaging system that uses the sun as a light source was developed it) obtain direct flow-field images of shock waves of aircraft in flight. This system was used to study how shock waves evolve to form sonic booms. The image quality obtained was limited by several optical and mechanical factors. Converting the photographs to digital images and applying digital image-processing techniques greatly improved the final quality of the images and more clearly showed the shock structures.
    Keywords: Aerodynamics
    Type: Journal of Flow Visualization and Image Processing; Volume 4; 189-199
    Format: text
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  • 2
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    F-18 high alpha research vehicle: Lessons learned (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The F-18 High Alpha Research Vehicle has proven to be a useful research tool with many unique capabilities. Many of these capabilities are to assist in characterizing flight at high angles of attack, while some provide significant research in their own right. Of these, the thrust vectoring system, the unique ability to rapidly reprogram flight controls, the reprogrammable mission computer, and a reprogrammable onboard excitation system have allowed an increased utility and versatility of the research being conducted. Because of this multifaceted approach to research in the high angle of attack regime, the capabilities of the F-18 High Alpha Research Vehicle were designed to cover as many high alpha technology bases as the program would allow. These areas include aerodynamics, controls, handling qualities, and propulsion.
    Keywords: AERODYNAMICS
    Type: Fourth High Alpha Conference, Volume 2 15 p(SEE N95-14239 03-02); Fourth High Alpha Co
    Format: application/pdf
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  • 3
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    On the Minimum Induced Drag of Wings (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN13483 , Soaring Society of America (SSA) Convention 2014; Feb 27, 2013 - Mar 31, 2013; Reno, NV; United States
    Format: application/pdf
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  • 4
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    On the Minimum Induced Drag of Wings (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Of all the types of drag, induced drag is associated with the creation and generation of lift over wings. Induced drag is directly driven by the span load that the aircraft is flying at. The tools by which to calculate and predict induced drag we use were created by Ludwig Prandtl in 1903. Within a decade after Prandtl created a tool for calculating induced drag, Prandtl and his students had optimized the problem to solve the minimum induced drag for a wing of a given span, formalized and written about in 1920. This solution is quoted in textbooks extensively today. Prandtl did not stop with this first solution, and came to a dramatically different solution in 1932. Subsequent development of this 1932 solution solves several aeronautics design difficulties simultaneously, including maximum performance, minimum structure, minimum drag loss due to control input, and solution to adverse yaw without a vertical tail. This presentation lists that solution by Prandtl, and the refinements by Horten, Jones, Kline, Viswanathan, and Whitcomb.
    Keywords: Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN3811 , Society of American Materials and Process Engineers (SAMPE); Jun 28, 2011; Palmdale, CA; United States
    Format: application/pdf
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  • 5
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    Gliding Experiments of the Wright Brothers: Flight Research 1899-1908 (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Presentation showing glider experiments of the Wright Brothers from 1899-1908 are presented. The slides review the experiments that the Wright Brothers conducted prior to their first powered flight in 1903 to developing the first practical aircraft in 1905, Many pictures of the gliders and other devices are used to illustrate the gradual development and experimentation that preceeded the first powered flight.
    Keywords: Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN3547 , Minter Field Fly-In; Jun 17, 2011; Shafter, CA; United States
    Format: application/pdf
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  • 6
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    On the Minimum Induced Drag of Wings (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This presentation on 1933 Prandtl applications to a small research UAV. We will discuss the implications of 1933 Prantl, connections to Horten, our discovery of how this reveals the mechanisms used by the flight of birds, and our recent work on FOSS and pressures on the wing.
    Keywords: Aircraft Design, Testing and Performance
    Type: AFRC-E-DAA-TN57433 , Pacific Division AAAS Annual Meeting; Jun 12, 2018 - Jun 15, 2018; Pomona, CA; United States
    Format: application/pdf
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  • 7
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    Computational Fluid Dynamics Analysis of the Stall Characteristics of a Wing Design Based on Prandtl's Minimum Induced Drag (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Stall characteristics of a wing whose design was based on Prandtls minimum induced drag analysis is presented. Flow field is resolved using RANS CFD (Computational Fluid Dynamics) solver OVERFLOW-2. Both in freestream and in ground effect are analyzed. In addition, effect of low-Mach preconditioner on the stall characteristic is presented. Results show that simulations that lack preconditioner predicts higher stall angle as well as much more benign behavior near the stall angle. Stall analysis in freestream show that flow begins to separate at the inboard region. The flow at the tip remains attached until approximately 19.0 degrees angle of attack.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN48257 , AIAA Applied Aerodynamics Conference; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States|AIAA Aviation and Aeronautics Forum (Aviation 2018); Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
    Format: application/pdf
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  • 8
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    On the Minimum Induced Drag of Wings (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Prandtl 1933 spanload development showing the wing developed to achieve this spanload, including the planform and the twist. Additionally, the derivative propeller, rotor, fan are also shown, including the planform and the twist.
    Keywords: Aircraft Design, Testing and Performance
    Type: AFRC-E-DAA-TN60613 , Annual Experimental Soaring Association Western Workshop; Aug 31, 2018 - Sep 03, 2018; Tehachapi, CA; United States
    Format: application/pdf
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  • 9
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    On the Minimum Induced Drag of Wings (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Birds do not require the use of vertical tails. They do not appear to have any mechanism by which to control their yaw. As an example the albatross is notable in this regard. The authors believe this is possible because of a unique adaptation by which there exists a triple-optimal solution that provides the maximum aerodynamic efficiency, the minimum structural weight, and it provides for coordination of control in roll and yaw. Until now, this solution has eluded researchers, and remained unknown. Here it is shown that the correct specification of spanload provides for all three solutions at once, maximum aerodynamic efficiency, minimum structural weight, and coordinated control. The implications of this result has far reaching effects on the design of aircraft, as well as dramatic efficiency improvement.
    Keywords: Aircraft Stability and Control; Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN23522 , Pioneer Valley High School; 21 Feb. 2018; Santa Maria, CA; United States|California Polytechnic State University (Aero Design Class); 21 Feb. 2018; San Luis Obispo, CA; United States|Cal Poly Aero Class; 14 May 2015; Edwards, CA; United States|AIAA SciTech 2017; 9-13 Jan. 2017; Grapevine, TX; United States|Sustainable Aviation (SA) Symposium 2017; 21-22 Apr. 2017; Redwood City, CA; United States|Annual Experimental Soaring Association Western Workshop 2017 ; 2-3 Sep. 2017; Tehachapi, CA; United States|Annual Academy of Model Aeronautics (AMA) Expo West; 5-7 Jan. 2018; Ontario, CA; United States|Annual Academy of Model Aeronautics (AMA) Expo West; 6-8 Jan. 2017; Ontario, CA; United States
    Format: application/pdf
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  • 10
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    On the Minimum Induced Drag of Wings -or- Thinking Outside the Box (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Of all the types of drag, induced drag is associated with the creation and generation of lift over wings. Induced drag is directly driven by the span load that the aircraft is flying at. The tools by which to calculate and predict induced drag we use were created by Ludwig Prandtl in 1903. Within a decade after Prandtl created a tool for calculating induced drag, Prandtl and his students had optimized the problem to solve the minimum induced drag for a wing of a given span, formalized and written about in 1920. This solution is quoted in textbooks extensively today. Prandtl did not stop with this first solution, and came to a dramatically different solution in 1932. Subsequent development of this 1932 solution solves several aeronautics design difficulties simultaneously, including maximum performance, minimum structure, minimum drag loss due to control input, and solution to adverse yaw without a vertical tail. This presentation lists that solution by Prandtl, and the refinements by Horten, Jones, Kline, Viswanathan, and Whitcomb.
    Keywords: Aircraft Design, Testing and Performance
    Type: DFRC-E-DAA-TN4103 , Experimental Soaring Association 2011 Western Workshop; Sep 02, 2011 - Sep 05, 2011; Tehachapi, CA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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