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 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 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 34 Experimental Aero heating at Mach 6 and 10 written by Scott A. Berry 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 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 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 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 Rev F Turbulent Aeroheating Results From Test 6817 in NASA Langley 20 Inch Mach 6 Air Tunnel and Comparisons With Computations written by Brian R. Hollis and published by . This book was released on 2003 with total page 76 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 Scott A. Berry and published by . This book was released on 1999 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerothermodynamic Calculations on X 34 at Mach 6 Wind Tunnel Conditions written by William A. Wood and published by . This book was released on 1999 with total page 26 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 Adm Nasa and published by Independently Published. This book was released on 2018-09-24 with total page 74 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 Aerothermodynamic Calculations on X 34 at Mach 6 Wind Tunnel Conditions written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-25 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of Reynolds number and turbulence on surface heat-transfer rates are numerically investigated for a 0.015 scale X-34 vehicle at wind tunnel conditions. Laminar heating rates, non-dimensionalized by Fay-Riddell stagnation heating, do not change appreciably with an order of magnitude variation in Reynolds number. Modeling a turbulent versus laminar boundary layer at the same Reynolds number increases the windside heating by a factor of four, portions on the leeside by a factor of two, and causes a 30 percent increase in wing leading edge heating. A discrepancy between laminar and turbulent heating trends on the windside centerline is explained by the presence of attached windside vortices in the laminar solutions, structures that are inhibited by the turbulence modeling. Wood, William A. Langley Research Center NASA/TM-1999-208998, NAS 1.15:208998, L-17794

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 AEROTHERMODYNAMIC CALCULATIONS ON X 34 AT MACH 6 WIND TUNNEL CONDITIONS NASA TM 1999 208998 MAR 1 1999 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 38 Experimental Aeroheating at Mach 10 written by Scott A. Berry and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Forced Boundary Layer Transition on X 43 Hyper X in NASA LaRC 31 Mach 10 Air Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeroheating and boundary layer transition characteristics for the X-43 (Hyper-X) configuration have been experimentally examined in the Langley 31-Inch Mach 10 Air Tunnel. Global surface heat transfer distributions, and surface streamline patterns were measured on a 0.333-scale model of the Hyper-X forebody. Parametric variations include angles-of-attack of 0-deg, 2-deg, 3-deg, and 4-deg; Reynolds numbers based on model length of 1.2 to 5.1 million; and inlet cowl door both open and closed. The effects of discrete roughness elements on the forebody boundary layer, which included variations in trip configuration and height, were investigated. This document is intended to serve as a release of preliminary data to the Hyper-X program; analysis is limited to observations of the experimental trends in order to expedite dissemination.Administration (NASA)Langley Research CenterAERODYNAMIC HEATING; BOUNDARY LAYER TRANSITION; WIND TUNNEL TESTS; SCALE MODELS; HEAT TRANSFER; THERMOGRAPHY; HYPERSONIC FLIGHT; X-43 VEHICLE; REYNOLDS NUMBER; ANGLE OF ATTACK; HYPERSONIC SPEED