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ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (317 download)
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:
Author : United States. National Aeronautics and Space Administration
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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (523 download)
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:
Author : National Aeronautics and Space Adm Nasa
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ISBN 13 : 9781723733512
Total Pages : 28 pages
Book Rating : 4.7/5 (335 download)
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...
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Publisher : DIANE Publishing
ISBN 13 : 1428995846
Total Pages : 47 pages
Book Rating : 4.4/5 (289 download)
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:
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)
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
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ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (317 download)
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:
Author : United States. National Aeronautics and Space Administration
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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (523 download)
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:
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ISBN 13 :
Total Pages : 560 pages
Book Rating : 4.3/5 (243 download)
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:
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ISBN 13 :
Total Pages : 522 pages
Book Rating : 4.0/5 ( download)
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:
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ISBN 13 :
Total Pages : 600 pages
Book Rating : 4.:/5 (317 download)
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:
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ISBN 13 :
Total Pages : 166 pages
Book Rating : 4.:/5 (317 download)
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:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721256563
Total Pages : 36 pages
Book Rating : 4.2/5 (565 download)
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 Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-16 with total page 36 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
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ISBN 13 :
Total Pages : 24 pages
Book Rating : 4.:/5 (317 download)
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 and published by . This book was released on 2001 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. National Aeronautics and Space Administration
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ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (523 download)
Download or read book INVISCID FLOW COMPUTATIONS OF THE ORBITAL SCIENCES X-34 OVER A MACH NUMBER RANGE OF 1.25 TO 6.0... 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:
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ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.:/5 (317 download)
Download or read book Inviscid Flow Computations of the Shuttle Orbiter for Mach 10 and 15 and Angle of Attack 40 to 60 Degrees written by and published by . This book was released on 2001 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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ISBN 13 :
Total Pages : 1040 pages
Book Rating : 4.:/5 (31 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1973 with total page 1040 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author : National Aeronautics and Space Adm Nasa
Publisher :
ISBN 13 : 9781730986840
Total Pages : 110 pages
Book Rating : 4.9/5 (868 download)
Download or read book Computation of Steady and Unsteady Quasi-One-Dimensional Viscous/Inviscid Interacting Internal Flows at Subsonic, Transonic, and Supersonic Mach Numbers written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-07 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computations of viscous-inviscid interacting internal flowfields are presented for steady and unsteady quasi-one-dimensional (Q1D) test cases. The unsteady Q1D Euler equations are coupled with integral boundary-layer equations for unsteady, two-dimensional (planar or axisymmetric), turbulent flow over impermeable, adiabatic walls. The coupling methodology differs from that used in most techniques reported previously in that the above mentioned equation sets are written as a complete system and solved simultaneously; that is, the coupling is carried out directly through the equations as opposed to coupling the solutions of the different equation sets. Solutions to the coupled system of equations are obtained using both explicit and implicit numerical schemes for steady subsonic, steady transonic, and both steady and unsteady supersonic internal flowfields. Computed solutions are compared with measurements as well as Navier-Stokes and inverse boundary-layer methods. An analysis of the eigenvalues of the coefficient matrix associated with the quasi-linear form of the coupled system of equations indicates the presence of complex eigenvalues for certain flow conditions. It is concluded that although reasonable solutions can be obtained numerically, these complex eigenvalues contribute to the overall difficulty in obtaining numerical solutions to the coupled system of equations. Swafford, Timothy W. and Huddleston, David H. and Busby, Judy A. and Chesser, B. Lawrence Unspecified Center COMPUTATIONAL FLUID DYNAMICS; FLOW DISTRIBUTION; MACH NUMBER; NAVIER-STOKES EQUATION; NUMERICAL ANALYSIS; SUBSONIC FLOW; SUPERSONIC FLOW; TRANSONIC FLOW; UNSTEADY FLOW; VISCOUS FLOW; ADIABATIC CONDITIONS; AXISYMMETRIC FLOW; BOUNDARY LAYERS; EULER EQUATIONS OF MOTION; INTEGRAL EQUATIONS; INVISCID FLOW; TURBULENT FLOW; WALL TEMPERATURE...
