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Inviscid Flow Computations Of Several Aeroshell Configurations For A 07 Mars Lander Nasa
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Book Synopsis INVISCID FLOW COMPUTATIONS OF SEVERAL AEROSHELL CONFIGURATIONS FOR A '07 MARS LANDER... NASA by : United States. National Aeronautics and Space Administration
Download or read book INVISCID FLOW COMPUTATIONS OF SEVERAL AEROSHELL CONFIGURATIONS FOR A '07 MARS LANDER... NASA written by United States. National Aeronautics and Space Administration and published by . This book was released on 2002* 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 :9781720605577 Total Pages :28 pages Book Rating :4.6/5 (55 download)
Book Synopsis Inviscid Flow Computations of Several Aeroshell Configurations for a '07 Mars Lander by : National Aeronautics and Space Administration (NASA)
Download or read book Inviscid Flow Computations of Several Aeroshell Configurations for a '07 Mars Lander written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the results of an inviscid computational study conducted on several candidate aeroshell configurations for a proposed '07 Mars lander. Eleven different configurations were considered, and the aerodynamic characteristics of each of these were computed for a Mach number of 23.7 at 10, 15, and 20 degree angles of attack. The unstructured grid software FELISA with the equilibrium Mars gas option was used for these computations. The pitching moment characteristics and the lift-to-drag ratios at trim angle of attack of each of these configurations were examined to make a selection. The criterion for selection was that the configuration should be longitudinally stable, and should trim at an angle of attack where the L/D is -0.25. Based on the present study, two configurations were selected for further studyPrabhu, Ramadas K.Langley Research CenterAERODYNAMIC CHARACTERISTICS; AEROSHELLS; INVISCID FLOW; ANGLE OF ATTACK; MACH NUMBER; COMPUTATIONAL FLUID DYNAMICS
Book Synopsis INVISCID FLOW COMPUTATIONS OF TWO '07 MARS LANDER AEROSHELL CONFIGURATIONS OVER A MACH NUMBER RANGE OF 2 TO 24... NASA by : United States. National Aeronautics and Space Administration
Download or read book INVISCID FLOW COMPUTATIONS OF TWO '07 MARS LANDER AEROSHELL CONFIGURATIONS OVER A MACH NUMBER RANGE OF 2 TO 24... NASA written by United States. National Aeronautics and Space Administration and published by . This book was released on 2002* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Inviscid Flow Computations of Several Aeroshell Configurations for a '07 Mars Lander by :
Download or read book Inviscid Flow Computations of Several Aeroshell Configurations for a '07 Mars Lander written by and published by . This book was released on 2001 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Inviscid Flow Computations of Two '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2 to 24 by :
Download or read book Inviscid Flow Computations of Two '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2 to 24 written by and published by . This book was released on 2001 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Inviscid Flow Computations of Two '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2 To 24 by : National Aeronautics and Space Adm Nasa
Download or read book Inviscid Flow Computations of Two '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2 To 24 written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-09-15 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the results of an inviscid computational study conducted on two aeroshell configurations for a proposed '07 Mars Lander. The aeroshell configurations are asymmetric due to the presence of the tabs at the maximum diameter location. The purpose of these tabs was to change the pitching moment characteristics so that the aeroshell will trim at a non-zero angle of attack and produce a lift-to-drag ratio of approximately -0.25. This is required in the guidance of the vehicle on its trajectory. One of the two configurations is called the shelf and the other is called the tab. The unstructured grid software FELISA with the equilibrium Mars gas option was used for these computations. The computations were done for six points on a preliminary trajectory of the '07 Mars Lander at nominal Mach numbers of 2, 3, 5, 10, 15, and 24. Longitudinal aerodynamic characteristics namely lift, drag, and pitching moment were computed for 10, 15, and 20 degrees angles of attack. The results indicated that the two configurations have aerodynamic characteristics that have very similar aerodynamic characteristics, and provide the desired trim LID of approximately -0.25.Prabhu, Ramadas K.Langley Research CenterCOMPUTATIONAL FLUID DYNAMICS; INVISCID FLOW; AEROSHELLS; SPACECRAFT STRUCTURES; MACH NUMBER; TABS (CONTROL SURFACES); ASYMMETRY; UNSTRUCTURED GRIDS (MATHEMATICS); AERODYNAMIC CHARACTERISTICS; LIFT DRAG RATIO; HYPERSONIC SPEED; AERODYNAMIC LOADS...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720381785 Total Pages :48 pages Book Rating :4.3/5 (817 download)
Book Synopsis An Inviscid Computational Study of Three '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2. 3 To 4. 5 by : National Aeronautics and Space Administration (NASA)
Download or read book An Inviscid Computational Study of Three '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2. 3 To 4. 5 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the results of a study conducted to compute the inviscid longitudinal aerodynamic characteristics of three aeroshell configurations of the proposed '07 Mars lander. This was done in support of the activity to design a smart lander for the proposed '07 Mars mission. In addition to the three configurations with tabs designated as the shelf, the canted, and the Ames, the baseline configuration (without tab) was also studied. The unstructured grid inviscid CFD software FELISA was used, and the longitudinal aerodynamic characteristics of the four configurations were computed for Mach number of 2.3, 2.7, 3.5, and 4.5, and for an angle of attack range of -4 to 20 degrees. Wind tunnel tests had been conducted on scale models of these four configurations in the Unitary Plan Wind Tunnel, NASA Langley Research Center. Present computational results are compared with the data from these tests. Some differences are noticed between the two results, particularly at the lower Mach numbers. These differences are attributed to the pressures acting on the aft body. Most of the present computations were done on the forebody only. Additional computations were done on the full body (forebody and afterbody) for the baseline and the Shelf configurations. Results of some computations done (to simulate flight conditions) with the Mars gas option and with an effective gamma are also included.Prabhu, Ramadas K. and Sutton, Kenneth (Technical Monitor)Langley Research CenterAERODYNAMIC CHARACTERISTICS; AEROSHELLS; COMPUTATIONAL FLUID DYNAMICS; INVISCID FLOW; MACH NUMBER; MARS MISSIONS; WIND TUNNEL TESTS; FLIGHT CONDITIONS; SCALE MODELS; ANGLE OF ATTACK; SUPERSONIC SPEED; AFTERBODIES
Book Synopsis An inviscid computational study of three '07 Mars lander aeroshell configurations over a Mach number range of 2.3 to 4.5 by :
Download or read book An inviscid computational study of three '07 Mars lander aeroshell configurations over a Mach number range of 2.3 to 4.5 written by and published by DIANE Publishing. This book was released on with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Inviscid Computational Study of Three '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2.3 to 4.5 by :
Download or read book An Inviscid Computational Study of Three '07 Mars Lander Aeroshell Configurations Over a Mach Number Range of 2.3 to 4.5 written by and published by . This book was released on 2001 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 2002 with total page 560 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12 by :
Download or read book NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12 written by and published by . This book was released on 1989 with total page 600 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 04-2169 - 04-2293 written by and published by . This book was released on 2004 with total page 522 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Langley Scientific and Technical Information Output-2001 by :
Download or read book NASA Langley Scientific and Technical Information Output-2001 written by and published by . This book was released on 2002 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Inviscid Flow Computations of the Shuttle Orbiter for Mach 10 and 15 and Angle of Attack 40 to 60 Degrees ... Nasa by : United States. National Aeronautics and Space Administration
Download or read book Inviscid Flow Computations of the Shuttle Orbiter for Mach 10 and 15 and Angle of Attack 40 to 60 Degrees ... Nasa written by United States. National Aeronautics and Space Administration and published by . This book was released on 2002* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781724112323 Total Pages :38 pages Book Rating :4.1/5 (123 download)
Book Synopsis Inviscid Flow Computations of the Orbital Sciences X-34 Over a Mach Number Range of 1.25 to 6.0 by : National Aeronautics and Space Adm Nasa
Download or read book Inviscid Flow Computations of the Orbital Sciences X-34 Over a Mach Number Range of 1.25 to 6.0 written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-27 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the results of an inviscid computational study conducted on the Orbital Sciences X-34 vehicle to compute its inviscid longitudinal aerodynamic characteristics over a Mach number range of 1.25 to 6.0. The unstructured grid software FELISA was used and th e aerodynamic characteristics were computed at Mach numbers 1.25, 1.6, 2.5, 4.0, 4.63, and 6.0, and an angle of attack range of -4 to 32 degrees. These results were compared with available aerodynamic data from wind tunnel test on X-34 models. The comparison showed excellent agreement in C(sub N). The computed pitching moment compared well at Mach numbers 2.5 and higher, and at angles of attack of up to 12 deg. The agreement was not good at higher angles of attack possibly due to viscous effects. At lower Mach numbers there were significant differences between computed and measured C(sub m) values. This could not be explained. Since the present computations are inviscid, the computed C(sub A) was consistently lower than the measured values as expected. Prabhu, Ramadas K. Langley Research Center NASA/CR-2001-210849, NAS 1.26:210849
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724292971 Total Pages :30 pages Book Rating :4.2/5 (929 download)
Book Synopsis Developments in the Simulation of Compressible Inviscid and Viscous Flow on Supercomputers by : National Aeronautics and Space Administration (NASA)
Download or read book Developments in the Simulation of Compressible Inviscid and Viscous Flow on Supercomputers written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-26 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: In anticipation of future supercomputers, finite difference codes are rapidly being extended to simulate three-dimensional compressible flow about complex configurations. Some of these developments are reviewed. The importance of computational flow visualization and diagnostic methods to three-dimensional flow simulation is also briefly discussed. Steger, J. L. and Buning, P. G. Ames Research Center NASA-TM-86674, A-85121, NAS 1.15:86674
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781792635823 Total Pages :28 pages Book Rating :4.6/5 (358 download)
Book Synopsis High-Speed Flow Calculations Past 3-D Configurations Based on the Reynolds Averaged Navier-Stokes Equations by : National Aeronautics and Space Adm Nasa
Download or read book High-Speed Flow Calculations Past 3-D Configurations Based on the Reynolds Averaged Navier-Stokes Equations written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-30 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational fluid dynamics tool has been developed capable of analyzing the viscous supersonic/hypersonic flow about realistic configurations. This techniques can predict the flow in regions of canopies, wings, and canards in addition to the usual simple symmetric configurations. It also allows for interactions between aerodynamic surfaces such as the vortex interaction between canards and wings. Chaussee, Denny S. Ames Research Center NASA-TM-100082, A-88118, NAS 1.15:100082 ...
