Download or read book Computational experimental Aeroheating Predications for X 33 Phase 2 Vehicle Nasa tm 1998 207290 Jun 1 1998 written by and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book COMPUTATIONAL EXPERIMENTAL AEROHEATING PREDICTIONS FOR X 33 NASA TM 1998 207315 APR 7 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computational experimental Aero heating Predictions for X 33 Phase II Vehicle written by H. Harris Hamilton and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book X 33 Computational Aeroheating Aerodynamic Predictions and Comparisons With Experimental Data written by Brian Ray Hollis and published by . This book was released on 2003 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book X 33 Computational Aeroheating Aerodynamic Predictions and Comparisons with Experimental Data 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 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report details a computational fluid dynamics study conducted in support of the phase II development of the X-33 vehicle. Aerodynamic and aeroheating predictions were generated for the X-33 vehicle at both flight and wind-tunnel test conditions using two finite-volume, Navier-Stokes solvers. Aerodynamic computations were performed at Mach 6 and Mach 10 wind-tunnel conditions for angles of attack from 10 to 50 with body-flap deflections of 0 to 20. Additional aerodynamic computations were performed over a parametric range of free-stream conditions at Mach numbers of 4 to 10 and angles of attack from 10 to 50. Laminar and turbulent wind-tunnel aeroheating computations were performed at Mach 6 for angles of attack of 20 to 40 with body-flap deflections of 0 to 20. Aeroheating computations were performed at four flight conditions with Mach numbers of 6.6 to 8.9 and angles of attack of 10 to 40. Surface heating and pressure distributions, surface streamlines, flow field information, and aerodynamic coefficients from these computations are presented, and comparisons are made with wind-tunnel data.Hollis, Brian R. and Thompson, Richard A. and Berry, Scott A. and Horvath, Thomas J. and Murphy, Kelly J. and Nowak, Robert J. and Alter, Stephen J.Langley Research CenterAERODYNAMIC HEATING; COMPUTATIONAL FLUID DYNAMICS; FLOW DISTRIBUTION; NAVIER-STOKES EQUATION; PRESSURE DISTRIBUTION; AERODYNAMIC COEFFICIENTS; ANGLE OF ATTACK; FINITE VOLUME METHOD; FLIGHT CONDITIONS; HYPERSONIC SPEED; WIND TUNNEL TESTS; X-33 REUSABLE LAUNCH VEHICLE
Download or read book COMPUTATIONAL AEROHEATING PREDICTIONS FOR X 34 NASA TM 1998 206289 MAY 5 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book X 34 EXPERIMENTAL AEROHEATING AT MACH 6 AND 10 NASA TM 1998 207319 APR 7 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book X 33 Rev F Turbulent Aeroheating Results from Test 6817 in NASA Langley 20 Inch Mach 6 Air Tunnel and Comparisons with Computations 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 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements and predictions of the X-33 turbulent aeroheating environment have been performed at Mach 6, perfect-gas air conditions. The purpose of this investigation was to compare measured turbulent aeroheating levels on smooth models, models with discrete trips, and models with arrays of bowed panels (which simulate bowed thermal protections system tiles) with each other and with predictions from two Navier-Stokes codes, LAURA and GASP. The wind tunnel testing was conducted at free stream Reynolds numbers based on length of 1.8 x 10(exp 6) to 6.1 x 10(exp 6) on 0.0132 scale X-33 models at a = 40-deg. Turbulent flow was produced by the discrete trips and by the bowed panels at ill but the lowest Reynolds number, but turbulent flow on the smooth model was produced only at the highest Reynolds number. Turbulent aeroheating levels on each of the three model types were measured using global phosphor thermography and were found to agree to within .he estimated uncertainty (plus or minus 15%) of the experiment. Computations were performed at the wind tunnel free stream conditions using both codes. Turbulent aeroheating levels predicted using the LAURA code were generally 5%-10% lower than those from GASP, although both sets of predictions fell within the experimental accuracy of the wind tunnel data.Hollis, Brian R. and Horvath, Thomas J. and Berry, Scott A.Langley Research CenterX-33 REUSABLE LAUNCH VEHICLE; AERODYNAMIC HEATING; HYPERSONIC SPEED; TURBULENT FLOW; SCALE MODELS; WIND TUNNEL TESTS; COMPUTATIONAL FLUID DYNAMICS; NAVIER-STOKES EQUATION; ALGORITHMS; BOUNDARY LAYER TRANSITION; REYNOLDS NUMBER; PANELS; THERMOGRAPHY; GLOBAL AIR SAMPLING PROGRAM; FREE FLOW
Download or read book Aeroheating Predictions For X 34 Using And Inviscid Boundary Layer Method NASA TM 1998 206906 Apr 7 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1998* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book X 33 Rev F Aeroheating Results of Test 6770 in NASA Langley 20 Inch Mach 6 Air Tunnel 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 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeroheating characteristics of the X-33 Rev-F configuration have been experimentally examined in the Langley 20-Inch Mach 6 Air Tunnel (Test 6770). Global surface heat transfer distributions, surface streamline patterns, and shock shapes were measured on a 0.013-scale model at Mach 6 in air. Parametric variations include angles-of-attack of 20-deg, 30-deg, and 40-deg; Reynolds numbers based on model length of 0.9 to 4.9 million; and body-flap deflections of 10-deg and 20-deg. The effects of discrete roughness elements on boundary layer transition, which included trip height, size, and location, both on and off the windward centerline, were investigated. This document is intended to serve as a quick release of preliminary data to the X-33 program; analysis is limited to observations of the experimental trends in order to expedite dissemination.Berry, Scott A. and Horvath, Thomas J. and Kowalkowski, Matthew K. and Liechty, Derek S.Langley Research CenterX-33 REUSABLE LAUNCH VEHICLE; AERODYNAMIC HEATING; AERODYNAMIC CONFIGURATIONS; WIND TUNNEL TESTS; HYPERSONIC SPEED; HEAT TRANSFER; BOUNDARY LAYER TRANSITION; AEROTHERMODYNAMICS; WIND TUNNEL MODELS; REYNOLDS NUMBER; FLAPPING; THERMOGRAPHY; SCALE MODELS; SPACECRAFT MODELS
Download or read book X 33 Computational Aero heating Predictions and Comparisons with Experimental Data written by Brian R. Hollis and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computational Aeroheating Predictions for X 34 written by and published by . This book was released on 1998 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book THE X 33 EXTENDED FLIGHT TEST RANGE NASA TM 1998 206557 DEC 3 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ANALYSIS OF AEROSPIKE PLUME INDUCED BASE HEATING ENVIRONMENT NASA TM 1998 208139 JUN 1 1998 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1999* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
