Download or read book An Inviscid Computational Study of the Space Shuttle Orbiter and Several Damaged Configurations 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 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Inviscid aerodynamic characteristics of the Space Shuttle Orbiter were computed in support of the Columbia Accident Investigation. The unstructured grid software FELISA was used and computations were done using freestream conditions corresponding to those in the NASA Langley 20-Inch Mach 6 CF4 tunnel test section. The angle of attack was held constant at 40 degrees. The baseline (undamaged) configuration and a large number of damaged configurations of the Orbiter were studied. Most of the computations were done on a half model. However, one set of computations was done using the full-model to study the effect of sideslip. The differences in the aerodynamic coefficients for the damaged and the baseline configurations were computed. Simultaneously with the computation reported here, tests were being done on a scale model of the Orbiter in the 20-Inch Mach 6 CF4 tunnel to measure the deltas . The present computations complemented the CF4 tunnel test, and provided aerodynamic coefficients of the Orbiter as well as its components. Further, they also provided details of the flow field.Prabhu, Ramadas K. and Merski, N. Ronald (Technical Monitor)Langley Research CenterACCIDENT INVESTIGATION; AERODYNAMIC CHARACTERISTICS; INVISCID FLOW; SPACE SHUTTLE ORBITERS; COMPUTATIONAL FLUID DYNAMICS; COLUMBIA (ORBITER); AERODYNAMIC CONFIGURATIONS; DAMAGE; WIND TUNNEL TESTS; METHANE; SIDESLIP; UNSTRUCTURED GRIDS (MATHEMATICS); HYPERSONIC SPEED; COMPUTER PROGRAMS; AERODYNAMIC COEFFICIENTS; ANGLE OF ATTACK; FLOW DISTRIBUTION
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 National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-26 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the results of a computational study done to compute the inviscid longitudinal aerodynamic characteristics of the Space Shuttle Orbiter for Mach numbers 10 and 15 at angles of attack of 40, 50, 55, and 60 degrees. These computations were done to provide limited aerodynamic data in support of the Orbiter contingency abort task. The Orbiter had all the control surfaces in the undeflected position. The unstructured grid software FELISA was used for these computations with the equilibrium air option. Normal and axial force coefficients and pitching moment coefficients were computed. The hinge moment coefficients of the body flap and the inboard and outboard elevons were also computed. These results were compared with Orbiter Air Data Book (OADB) data and those computed using GASP. The comparison with the GASP results showed very good agreement in Cm and Ca at all the points. The computed axial force coefficients were smaller than those computed by GASP. There were noticeable differences between the present results and those in the OADB at angles of attack greater than 50 degrees. Prabhu, Ramadas K. and Sutton, Kenneth (Technical Monitor) Langley Research Center NASA/CR-2001-211267, NAS 1.26:211267
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:
Download or read book A High Angle of Attack Inviscid Shuttle Orbiter Computation written by and published by . This book was released on 1992 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A High Angle of Attack Inviscid Shuttle Orbiter Computation written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-23 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: As a preliminary step toward predicting the leeside thermal environment for winged reentry vehicles at flight conditions, a computational solution for the flow about the Shuttle Orbiter at wind tunnel conditions was made using a point-implicit, finite volume scheme known as the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA). The surface pressures resulting from the computational solution are compared with wind tunnel data. The results indicate that the dominant inviscid flow features are being accurately predicted on the leeside of the Shuttle Orbiter at a moderately high angle of attack. Kleb, William L. and Weilmuenster, K. James Langley Research Center RTOP 506-40-91-01...
Download or read book Experimental and Computational Analysis of the Space Shuttle Orbiter Hypersonic pitch up Anomaly written by Gregory J. Brauckmann and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Prediction of Sts 107 Hypervelocity Flow Fields about the Shuttle Orbiter with Various Wing Leading Edge Damage written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-21 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computations were performed for damaged configurations of the Shuttle Orbiter in support of the STS-107 Columbia accident investigation. Two configurations with missing wing leading-edge reinforced carbon-carbon (RCC) panels were evaluated at conditions just prior to the peak heating trajectory point. The initial configuration modeled the Orbiter with an approximate missing RCC panel 6 to determine whether this damage could result in anomalous temperatures measured during the STS-107 reentry. This missing RCC panel 6 computation was found to produce heating augmentation factors of 5 times the nominal heating rates on the side fuselage with lesser heat increases on the front of the OMS pod. This is consistent with the thermocouple and resistance temperature detector sensors from the STS-107 re-entry which observed off nominal high early in the re-entry trajectory. A second damaged configuration modeled the Orbiter with missing RCC panel 9 and included ingestion of the flow into the outboard RCC channel. This computation lowered the level (only 2 times nominal) and moved the location of the heating augmentation on the leeside fuselage relative to the missing RCC panel 6 configuration. The lesser heating augmentation for missing RCC panel 9 was confined near the wing fuselage juncture. Near nominal heating was predicted on the remainder of the side fuselage with some lower than nominal heating on the front surface of the OMS pod. These results for missing RCC panel 9 are consistent with data from the STS-107 re-entry where the heating augmentation was observed to move off the side fuselage and OMS pod sensors at later times in the trajectory. As this solution requires supersonic mass ingestion into the RCC channel, it is probably not an appropriate model prior to penetration of the flow through the spar into the wing structure. It may, however, be representative of the conditions at later times and could account for the movement of the heating signature on the side fus
Download or read book Study of Several Factos Affecting Crew Escape Trajectories from the Space Shuttle Orbiter at Low subsonic Speeds written by and published by . This book was released on 1985 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Study of Several Factors Affecting Crew Escape Trajectories from the Space Shuttle Orbiter at Low subsonic Speeds written by and published by . This book was released on 1985 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Turbulent Wing Leading Edge Correlation Assessment for the Shuttle Orbiter written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-13 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study was conducted in support of the Orbiter damage assessment activity that takes place for each Shuttle mission since STS-107 (STS - Space Transportation System). As part of the damage assessment activity, the state of boundary layer (laminar or turbulent) during reentry needs to be estimated in order to define the aerothermal environment on the Orbiter. Premature turbulence on the wing leading edge (WLE) is possible if a surface irregularity promotes early transition and the resulting turbulent wedge flow contaminates the WLE flow. The objective of this analysis is to develop a criterion to determine if and when the flow along the WLE experiences turbulent heating given an incoming turbulent boundary layer that contaminates the attachment line. The data to be analyzed were all obtained as part of the MH-13 Space Shuttle Orbiter Aerothermodynamic Test conducted on a 1.8%-scale Orbiter model at Calspan/University of Buffalo Research Center in the Large Energy National Shock Tunnels facility. A rational framework was used to develop a means to assess the state of the WLE flow on the Orbiter during reentry given a contaminated attachment-line flow. Evidence of turbulent flow on the WLE has been recently documented for a few STS missions during the Orbiter s flight history, albeit late in the reentry trajectory. The criterion developed herein will be compared to these flight results. King, Rudolph A. and Vaughan, Matthew P. Langley Research Center NASA/TM-2009-215949, L-19784, LF99-9713
Download or read book Space Shuttle Orbiter Trimmed Center of Gravity Extension Study Volume 1 Effects of Configuration Modifications on the Aerodynamic Characteristics of the 140 A B Orbiter at Mach 10 3 written by and published by . This book was released on 1975 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Shuttle Orbiter Trimmed Center of gravity Extension Study Volume 2 Effects of Configuration Modifications on the Aerodynamic Characteristics of the 140 A B Orbiter at Transonic Speeds written by and published by . This book was released on 1976 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Shuttle Orbiter Trimmed Center of gravity Extension Study Volume 3 Impact of Retrofits for Center of gravity Extension on Orbiter Thermal protection System written by and published by . This book was released on 1979 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Shuttle Orbiter Trimmed Center of gravity Extension Study Volume 8 Effects of Configuration Modifications on the Aerodynamic Characteristics of the 140 A B Orbiter at a Mach Number of 5 97 written by and published by . This book was released on 1984 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Shuttle Orbiter Trimmed Center of gravity Extension Study Volume 5 Effects of Configuration Modifications on the Aerodynamic Characteristics of the 140A B Orbiter at Mach Numbers of 2 5 3 95 and 4 6 written by and published by . This book was released on 1979 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Shuttle Orbiter Trimmed Center of gravity Extension Study Volume 7 Effects of Configuration Modifications on the Subsonic Aerodynamic Characteristics of the 1140 A B Orbbiter at High Reynolds Numbers written by and published by . This book was released on 1981 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
