Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Unstructured Grid Euler Method Assessment For Longitudinal And Lateral Directional Aerodynamic Performance Analysis Of The Hsr Technology Concept Airplane At Supersonic Cruise Speed
Download Unstructured Grid Euler Method Assessment For Longitudinal And Lateral Directional Aerodynamic Performance Analysis Of The Hsr Technology Concept Airplane At Supersonic Cruise Speed full books in PDF, epub, and Kindle. Read online Unstructured Grid Euler Method Assessment For Longitudinal And Lateral Directional Aerodynamic Performance Analysis Of The Hsr Technology Concept Airplane At Supersonic Cruise Speed ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Aerodynamic Performance Analysis of the HSR Technology Concept Airplane at Supersonic Cruise Speed by :
Download or read book Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Aerodynamic Performance Analysis of the HSR Technology Concept Airplane at Supersonic Cruise Speed written by and published by . This book was released on 1999 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721035311 Total Pages :44 pages Book Rating :4.0/5 (353 download)
Book Synopsis Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Aerodynamic Performance Analysis of the Hsr Technology Concept Airplane at Supersonic Cruise Speed by : National Aeronautics and Space Administration (NASA)
Download or read book Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Aerodynamic Performance Analysis of the Hsr Technology Concept Airplane at Supersonic Cruise Speed written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-12 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unstructured grid Euler computations, performed at supersonic cruise speed, are presented for a High Speed Civil Transport (HSCT) configuration, designated as the Technology Concept Airplane (TCA) within the High Speed Research (HSR) Program. The numerical results are obtained for the complete TCA cruise configuration which includes the wing, fuselage, empennage, diverters, and flow through nacelles at M (sub infinity) = 2.4 for a range of angles-of-attack and sideslip. Although all the present computations are performed for the complete TCA configuration, appropriate assumptions derived from the fundamental supersonic aerodynamic principles have been made to extract aerodynamic predictions to complement the experimental data obtained from a 1.675%-scaled truncated (aft fuselage/empennage components removed) TCA model. The validity of the computational results, derived from the latter assumptions, are thoroughly addressed and discussed in detail. The computed surface and off-surface flow characteristics are analyzed and the pressure coefficient contours on the wing lower surface are shown to correlate reasonably well with the available pressure sensitive paint results, particularly, for the complex flow structures around the nacelles. The predicted longitudinal and lateral/directional performance characteristics for the truncated TCA configuration are shown to correlate very well with the corresponding wind-tunnel data across the examined range of angles-of-attack and sideslip. The complementary computational results for the longitudinal and lateral/directional performance characteristics for the complete TCA configuration are also presented along with the aerodynamic effects due to empennage components. Results are also presented to assess the computational method performance, solution sensitivity to grid refinement, and solution convergence characteristics.Ghaffari, FarhadLangley Research CenterCOMPUTATIONAL FLUID DYNAMICS; SUPERSONIC TRANSPORTS; UNSTRUCTURED GRID
Book Synopsis Unstructured Grid Viscous Flow Simulation Over High-Speed Research Technology Concept Airplane at High-Lift Conditions by : Farhad Ghaffari
Download or read book Unstructured Grid Viscous Flow Simulation Over High-Speed Research Technology Concept Airplane at High-Lift Conditions written by Farhad Ghaffari and published by . This book was released on 1999 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerical viscous solutions based on an unstructured grid methodology are presented for a candidate high-speed civil transport configuration designated as the Technology Concept Airplane (TCA), within the High-Speed Research (HSR) program. The numerical results are obtained on a representative TCA high-lift configuration that consisted of the fuselage and the wing, with deflected full-span leading-edge and trailing-edge flaps. Typical on- and off-surface flow structures, computed at high-lift conditions appropriate for the takeoff and landing, indicated features that are generally plausible. Reasonable surface pressure correlations between the numerical results and the experimental data are obtained at free-stream Mach number M[sub infinity]=0.25 and Reynolds number c[overscore] R[sub c overscore]=8 times 10[factor 6] for moderate angles of attack of 9.7 deg. and 13.5 deg. However, above and below this angle-of-attack range, the correlation between computed and measured pressure distributions starts to deteriorate over the examined angle-of-attack range. The predicted longitudinal aerodynamic characteristics are shown to correlate very well with existing experimental data across the examined angle-of-attack range. An excellent agreement is also obtained between the predicted lift-to-drag ratio and the experimental data over the examined range of flow conditions.
Book Synopsis Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Stability Analysis of the HSR Reference H Configuration at Transonic Speeds by :
Download or read book Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Stability Analysis of the HSR Reference H Configuration at Transonic Speeds written by and published by . This book was released on 1999 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Langley Scientific and Technical Information Output: 1999 by :
Download or read book NASA Langley Scientific and Technical Information Output: 1999 written by and published by . This book was released on 2000 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721195343 Total Pages :34 pages Book Rating :4.1/5 (953 download)
Book Synopsis Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Stability Analysis of the Hsr Reference H Configuration at Transonic Speeds by : National Aeronautics and Space Administration (NASA)
Download or read book Unstructured Grid Euler Method Assessment for Longitudinal and Lateral/Directional Stability Analysis of the Hsr Reference H Configuration at Transonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic Euler computations, based on unstructured grid methodology, are performed for a proposed High Speed Civil Transport (HSCT) configuration, designated as the Reference H configuration within the High Speed Research (HSR) Program. The predicted results are correlated with appropriate experimental wind-tunnel data for the baseline configuration with and without control surface deflections for a range of angle of attack at M(sub infinity) = 0.95. Good correlations between the predictions and measured data have been obtained for the longitudinal aerodynamic characteristics of the baseline configuration. The incremental effects in the longitudinal aerodynamic characteristics due to horizontal rail deflections as well as wing leading-edge and trailing-edge flap deflections have also been predicted reasonably well. Computational results and correlations with data are also presented for the lateral and directional stability characteristics for a range of angle of attack at a constant sideslip angle as well as a range of sideslip angles at a constant angle of attack. In addition, the results are presented to assess the computational method performance and convergence characteristics. Ghaffari, Farhad Langley Research Center NASA/TM-1999-209526, NAS 1.15:209526, L-17927
Book Synopsis Monthly Catalog of United States Government Publications by :
Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on 2000 with total page 948 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722378486 Total Pages :54 pages Book Rating :4.3/5 (784 download)
Book Synopsis Euler Technology Assessment for Preliminary Aircraft Design-Unstructured/Structured Grid Nastd Application for Aerodynamic Analysis of an Advanced Fighter/Tailless Configuration by : National Aeronautics and Space Administration (NASA)
Download or read book Euler Technology Assessment for Preliminary Aircraft Design-Unstructured/Structured Grid Nastd Application for Aerodynamic Analysis of an Advanced Fighter/Tailless Configuration written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study supports the NASA Langley sponsored project aimed at determining the viability of using Euler technology for preliminary design use. The primary objective of this study was to assess the accuracy and efficiency of the Boeing, St. Louis unstructured grid flow field analysis system, consisting of the MACGS grid generation and NASTD flow solver codes. Euler solutions about the Aero Configuration/Weapons Fighter Technology (ACWFT) 1204 aircraft configuration were generated. Several variations of the geometry were investigated including a standard wing, cambered wing, deflected elevon, and deflected body flap. A wide range of flow conditions, most of which were in the non-linear regimes of the flight envelope, including variations in speed (subsonic, transonic, supersonic), angles of attack, and sideslip were investigated. Several flowfield non-linearities were present in these solutions including shock waves, vortical flows and the resulting interactions. The accuracy of this method was evaluated by comparing solutions with test data and Navier-Stokes solutions. The ability to accurately predict lateral-directional characteristics and control effectiveness was investigated by computing solutions with sideslip, and with deflected control surfaces. Problem set up times and computational resource requirements were documented and used to evaluate the efficiency of this approach for use in the fast paced preliminary design environment. Michal, Todd R. Langley Research Center...
Book Synopsis Euler Technology Assessment for Preliminary Aircraft Design-Unstructured/Structured Grid NASTD Application for Aerodynamic Analysis of an Advanced Fighter/Tailless Configuration by : Todd R. Michal
Download or read book Euler Technology Assessment for Preliminary Aircraft Design-Unstructured/Structured Grid NASTD Application for Aerodynamic Analysis of an Advanced Fighter/Tailless Configuration written by Todd R. Michal and published by . This book was released on 1998 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Euler Technology Assessment for Preliminary Aircraft Design Employing OVERFLOW Code with Multiblock Structured-grid Method by : David A. Treiber
Download or read book Euler Technology Assessment for Preliminary Aircraft Design Employing OVERFLOW Code with Multiblock Structured-grid Method written by David A. Treiber and published by . This book was released on 1995 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Euler Technology Assessment Program for Preliminary Aircraft Design Employing SPITFLOW Code with Cartesian Unstructured Grid Method by : Dennis B. Finley
Download or read book Euler Technology Assessment Program for Preliminary Aircraft Design Employing SPITFLOW Code with Cartesian Unstructured Grid Method written by Dennis B. Finley and published by . This book was released on 1995 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Euler Technology Assessment Program for Preliminary Aircraft Design Employing Splitflow Code with Cartesian Unstructured Grid Method by : National Aeronautics and Space Adm Nasa
Download or read book Euler Technology Assessment Program for Preliminary Aircraft Design Employing Splitflow Code with Cartesian Unstructured Grid Method written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-07 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents results from the Euler Technology Assessment program. The objective was to evaluate the efficacy of Euler computational fluid dynamics (CFD) codes for use in preliminary aircraft design. Both the accuracy of the predictions and the rapidity of calculations were to be assessed. This portion of the study was conducted by Lockheed Fort Worth Company, using a recently developed in-house Cartesian-grid code called SPLITFLOW. The Cartesian grid technique offers several advantages for this study, including ease of volume grid generation and reduced number of cells compared to other grid schemes. SPLITFLOW also includes grid adaptation of the volume grid during the solution convergence to resolve high-gradient flow regions. This proved beneficial in resolving the large vortical structures in the flow for several configurations examined in the present study. The SPLITFLOW code predictions of the configuration forces and moments are shown to be adequate for preliminary design analysis, including predictions of sideslip effects and the effects of geometry variations at low and high angles of attack. The time required to generate the results from initial surface definition is on the order of several hours, including grid generation, which is compatible with the needs of the design environment. Finley, Dennis B. Unspecified Center...
Book Synopsis Euler Technology Assessment for Preliminary Aircraft Design: Compressibility Predictions by Employing the Unstructured Grid USM3D Code by : Tom A. Kinard
Download or read book Euler Technology Assessment for Preliminary Aircraft Design: Compressibility Predictions by Employing the Unstructured Grid USM3D Code written by Tom A. Kinard and published by . This book was released on 1996 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Euler Technology Assessment Program for Preliminary Aircraft Design Employing SPLITFLOW Code with Cartesian Unstructured Grid Method by : Dennis B. Finley
Download or read book Euler Technology Assessment Program for Preliminary Aircraft Design Employing SPLITFLOW Code with Cartesian Unstructured Grid Method written by Dennis B. Finley and published by . This book was released on 1995 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Euler Technology Assessment for Preliminary Aircraft Design by : Tom A. Kinard
Download or read book Euler Technology Assessment for Preliminary Aircraft Design written by Tom A. Kinard and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723044540 Total Pages :102 pages Book Rating :4.0/5 (445 download)
Book Synopsis Euler Technology Assessment for Preliminary Aircraft Design by : National Aeronautics and Space Administration (NASA)
Download or read book Euler Technology Assessment for Preliminary Aircraft Design written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of the second phase of the Euler Technology Assessment program was to evaluate the ability of Euler computational fluid dynamics codes to predict compressible flow effects over a generic fighter wind tunnel model. This portion of the study was conducted by Lockheed Martin Tactical Aircraft Systems, using an in-house Cartesian-grid code called SPLITFLOW. The Cartesian grid technique offers several advantages, including ease of volume grid generation and reduced number of cells compared to other grid schemes. SPLITFLOW also includes grid adaption of the volume grid during the solution to resolve high-gradient regions. The SPLITFLOW code predictions of configuration forces and moments are shown to be adequate for preliminary design, including predictions of sideslip effects and the effects of geometry variations at low and high angles-of-attack. The transonic pressure prediction capabilities of SPLITFLOW are shown to be improved over subsonic comparisons. The time required to generate the results from initial surface data is on the order of several hours, including grid generation, which is compatible with the needs of the design environment. Finley, Dennis B. and Karman, Steve L., Jr. Langley Research Center COMPRESSIBILITY EFFECTS; COMPUTATIONAL FLUID DYNAMICS; EULER EQUATIONS OF MOTION; UNSTRUCTURED GRIDS (MATHEMATICS); CARTESIAN COORDINATES; TRANSONIC FLOW; VORTICES; ANGLE OF ATTACK; GRID GENERATION (MATHEMATICS); SIDESLIP; PRESSURE DISTRIBUTION; AERODYNAMIC LOADS; FIGHTER AIRCRAFT...
Book Synopsis Development of Unstructured Grid Methods for Steady and Unsteady Aerodynamic Analysis by :
Download or read book Development of Unstructured Grid Methods for Steady and Unsteady Aerodynamic Analysis written by and published by . This book was released on 1990 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
