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  • 1
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    Comparison of two-dimensional and three-dimensional droplet trajectory calculations in the vicinity of finite wings (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computational predictions of ice accretion on flying aircraft most commonly rely on modeling in 2D. These 2D methods treat an aircraft geometry either as wing-like with infinite span, or as an axisymmetric body. Recently, fully 3D methods have been introduced that model an aircraft's true 3D shape. Because 3D methods are more computationally expensive than 2D methods, 2D methods continue to be widely used. However, a 3D method allows investigation of whether it is valid to continue applying 2D methods to a finite wing. The extent of disagreement between LEWICE, a 2D method, and LEWICE3D, a 3D method, in calculating local collection efficiencies at the leading edge of finite wings is investigated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0645
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Collection Efficiency and Ice Accretion Calculations for a Sphere, a Swept MS(1)-317 Wing, a Swept NACA-0012 Wing Tip, an Axisymmetric Inlet, and a Boeing 737-300 (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Collection efficiency and ice accretion calculations have been made for a sphere, a swept MS(1)-317 wing, a swept NACA-0012 wing tip, an axisymmetric inlet, and a Boeing 737-300 inlet using the NPARC flow solver and the NASA Lewis LEWICE3D grid based ice accretion code. Euler flow solutions for the geometries were generated using the NPARC flow solver. The LEWICE3D grid based ice accretion program was used to calculate the impingement efficiencies and ice shapes. Ice shapes specifying rime and mixed icing conditions were generated for a 30 minute hold condition. All calculations were performed on an SGI Model Power Challenge Computer. The results have been compared to experimental flow and impingement data. In general, the calculated flow and collection efficiencies compared well with experiment, and the ice shapes looked reasonable and appeared representative of the rime and mixed icing conditions for which they were calculated.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TM-106831 , E-9381 , NAS 1.15:106831 , AIAA PAPER 95-0755 , Aerospace Sciences Meeting and Exhibit; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Wind-US Unstructured Flow Solutions for a Transonic Diffuser (2005)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Wind-US Computational Fluid Dynamics flow solver computed flow solutions for a transonic diffusing duct. The calculations used an unstructured (hexahedral) grid. The Spalart-Allmaras turbulence model was used. Static pressures along the upper and lower wall agreed well with experiment, as did velocity profiles. The effect of the smoothing input parameters on convergence and solution accuracy was investigated. The meaning and proper use of these parameters are discussed for the benefit of Wind-US users. Finally, the unstructured solver is compared to the structured solver in terms of run times and solution accuracy.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/CR-2005-213417 , AIAA Paper 2005-1004 , E-14939 , AIAA 43rd Aerospace Sciences Meeting and Exhibit; Jan 10, 2005 - Jan 13, 2005; Reno, NV; United States
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  • 4
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    Wind-US Flow Calculations for the M2129 S-Duct Using Structured and Unstructured Grids (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Computational Fluid Dynamics (CFD) flow solutions for the M2129 diffusing S-duct with and without vane effectors were computed by the Wind-US flow solver. Both structured and unstructured 3-D grids were used. Without vane effectors, the duct exhibited massive flow separation in both experiment and CFD. With vane effectors installed, the flow remained attached and aerodynamic losses were reduced. Total pressure recovery and distortion near the duct outlet were computed from the solutions and compared favorably to experimental values. These calculations are part of a validation effort for the Wind-US code. They also provide an example case to aid engineers in learning to use the Wind-US software.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/CR-2003-212736 , AIAA Paper 2004-0525 , E-14261 , 42nd Aerospace Sciences Meeting and Exhibit; Jan 05, 2004 - Jan 08, 2004; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Comparison of two-dimensional and three-dimensional droplet trajectory calculations in the vicinity of finite wings (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Computational predictions of ice accretion on flying aircraft most commonly rely on modeling in two dimensions (2D). These 2D methods treat an aircraft geometry either as wing-like with infinite span, or as an axisymmetric body. Recently, fully three dimensional (3D) methods have been introduced that model an aircrafts true 3D shape. Because 3D methods are more computationally expensive than 2D methods, 2D methods continue to be widely used. However, a 3D method allows us to investigate whether it is valid to continue applying 2D methods to a finite wing. The extent of disagreement between LEWICE, a 2D method, and LEWICE3D, a 3D method, in calculating local collection efficiencies at the leading edge of finite wings is investigated in this paper.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-105617 , E-6806 , NAS 1.15:105617 , AIAA PAPER 92-0645 , Aerospace Sciences Meeting; Jan 06, 1992 - Jan 09, 1992; Reno, NV; United States
    Format: application/pdf
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  • 6
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    AirShow 1.0 CFD Software Users' Guide (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: AirShow is visualization post-processing software for Computational Fluid Dynamics (CFD). Upon reading binary PLOT3D grid and solution files into AirShow, the engineer can quickly see how hundreds of complex 3-D structured blocks are arranged and numbered. Additionally, chosen grid planes can be displayed and colored according to various aerodynamic flow quantities such as Mach number and pressure. The user may interactively rotate and translate the graphical objects using the mouse. The software source code was written in cross-platform Java, C++, and OpenGL, and runs on Unix, Linux, and Windows. The graphical user interface (GUI) was written using Java Swing. Java also provides multiple synchronized threads. The Java Native Interface (JNI) provides a bridge between the Java code and the C++ code where the PLOT3D files are read, the OpenGL graphics are rendered, and numerical calculations are performed. AirShow is easy to learn and simple to use. The source code is available for free from the NASA Technology Transfer and Partnership Office.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/CR-2005-213891 , E-15262
    Format: application/pdf
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