Download or read book Integrated Hypersonic Aerothermoelastic Methodology for Transatmospheric Vehicle TAV thermal Protection System TPS Structural Design and Optimization written by D. D. Liu and published by . This book was released on 2002 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: The adaptation of ZONA unified hypersonic/supersonic method ZONA7U and its integration/development into a ZONA aerothermoelastic software system for transatmospheric vehicle (TAV)/thermal protection system (TPS) design/analysis was proven a successful tool through feasibility study with cases of a CKEM body, blunt cones, and a modeled X-34 wing body. Preceding the feasibility study, substantial effort was directed toward further development of a new code, ZSTREAM, and using it and ZABRO to replace the outdated modules in SHVD, thus to couple them with SHABP for aerothermoelastic applications. In the feasibility study, the cases are well validated with FD solutions. Next, computed heat rates by applying ZONA aerothermoelastic software to X-34 through two assigned hypersonic trajectories were shown and found to agree with those using MINIVER. A potential TPS design procedure was established using the obtained heat rates as an input to MINIVER, resulting in a minimum weight TPS per hot-wall consideration. With FEM/TRIM modules, ASTROS* yields the trim solution and stress distribution for a flexible X-34 at a typical trajectory joint, demonstrating the multifunctionality in MDO for the aerothermoelastic software.

Download or read book Aerothermodynamic Calculations on X 34 at Mach 6 Wind Tunnel Conditions written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 40 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 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 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 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 Forced Boundary Layer Transition on X 43 Hyper X in NASA Larc 20 Inch Mach 6 Air Tunnel written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-19 with total page 64 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 20-Inch Mach 6 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, and 4-deg; Reynolds numbers based on model length of 1.2 to 15.4 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.Berry, Scott A. and DiFulvio, Michael and Kowalkowski, Matthew K.Langley Research CenterAERODYNAMIC HEATING; BOUNDARY LAYER TRANSITION; WIND TUNNEL TESTS; SCALE MODELS; HEAT TRANSFER; HYPERSONIC FLIGHT; THERMOGRAPHY; ANGLE OF ATTACK; REYNOLDS NUMBER; HYPERSONIC SPEED; X-43 VEHICLE

Download or read book Development of X 33 X 34 Aerothermodynamic Data Bases 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 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A synoptic of programmatic and technical lessons learned in the development of aerothermodynamic data bases for the X-33 and X-34 programs is presented in general terms and from the perspective of the NASA Langley Research Center Aerothermodynamics Branch. The format used is that of the aerothermodynamic chain, the links of which are personnel, facilities, models/test articles, instrumentation, test techniques, and computational fluid dynamics (CFD). Because the aerodynamic data bases upon which the X-33 and X-34 vehicles will fly are almost exclusively from wind tunnel testing, as opposed to CFD, the primary focus of the lessons learned is on ground-based testing. Miller, C. G. Langley Research Center

Download or read book Wind tunnel Investigation at Mach Numbers from 3 0 to 6 8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by Albin O. Pearson and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book High speed Wind Tunnels written by Luigi Crocco and published by . This book was released on 1946 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: The importance assumed in recent times by experimental supersonic wind tunnels, as well as the power required, has brought about the need for a study which would permit a comparison of the types tested and the principal theoretical plans.

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 Real Gas Flow Properties for NASA Langley Research Center Aerothermodynamic Facilities Complex Wind Tunnels written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-13 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational algorithm has been developed which can be employed to determine the flow properties of an arbitrary real (virial) gas in a wind tunnel. A multiple-coefficient virial gas equation of state and the assumption of isentropic flow are used to model the gas and to compute flow properties throughout the wind tunnel. This algorithm has been used to calculate flow properties for the wind tunnels of the Aerothermodynamics Facilities Complex at the NASA Langley Research Center, in which air, CF4. He, and N2 are employed as test gases. The algorithm is detailed in this paper and sample results are presented for each of the Aerothermodynamic Facilities Complex wind tunnels. Hollis, Brian R. Langley Research Center...

Download or read book Review of the X 15 Program written by Joseph Weil and published by . This book was released on 1962 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Assessment of a Flow Through Balance for Hypersonic Wind Tunnel Models with Scramjet Exhaust Flow Simulation written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this investigation were twofold: first, to determine whether accurate force and moment data could be obtained during hypersonic wind tunnel tests of a model with a scramjet exhaust flow simulation that uses a representative nonwatercooled, flow-through balance; second, to analyze temperature time histories on various parts of the balance to address thermal effects on force and moment data. The tests were conducted in the NASA Langley Research Center 20-Inch Mach 6 Wind Tunnel at free-stream Reynolds numbers ranging from 0.5 to 7.4 x 10(exp 6)/ft and nominal angles of attack of -3.5 deg, 0 deg, and 5 deg. The simulant exhaust gases were cold air, hot air, and a mixture of 50 percent Argon and 50 percent Freon by volume, which reached stagnation temperatures within the balance of 111, 214, and 283 F, respectively. All force and moment values were unaffected by the balance thermal response from exhaust gas simulation and external aerodynamic heating except for axial-force measurements, which were significantly affected by balance heating. This investigation showed that for this model at the conditions tested, a nonwatercooled, flow-through balance is not suitable for axial-force measurements during scramjet exhaust flow simulation tests at hypersonic speeds. In general, heated exhaust gas may produce unacceptable force and moment uncertainties when used with thermally sensitive balances. Huebner, Lawrence D. and Kniskern, Marc W. and Monta, William J. Langley Research Center...

Download or read book Calculation of Interference for a Porous Wall Wind Tunnel by the Method of Block Cyclic Reduction written by C. F. Lo and published by . This book was released on 1975 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The lift interference was calculated for a porous wall wind tunnel by a modified method of block cyclic reduction. This efficient, numerical method has indicated its accuracy by comparison with other available analytical and approximate solutions. A scheme is introduced to search for optimum wall configurations. The lift interference computed for an NACA 64-series finite airfoil in some optimum configurations has demonstrated the achievement of minimization of interference. The effect of test section length is also examined. (Author).

Download or read book The High speed Flexible throat Supersonic Wind Tunnel written by and published by . This book was released on 1948 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Revolutionary Atmosphere written by Robert S. Arrighi and published by . This book was released on 2010-04-30 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Altitude Wind Tunnel's (AWT) steel shell loomed, almost threateningly, over the National Aeronautics and Space Administration (NASA) Glenn Research Center's main campus in Cleveland, Ohio, for over 60 years. The facility had been inactive since 1975, but the hulking tunnel sat in a conspicuous location between the visitors' center and the Icing Research Tunnel and was seen daily by hundreds, if not thousands, of people. The tunnel slowly ebbed from NASA Glenn's collective consciousness. Inside the steel shell, significant contributions had been made in the advancement of the jet engine and the high-profile Project Mercury and Centaur Program. Yet, the AWT had remained a mystery to most current employees and the public. Not only did the rusting giant have an obscure past, few even knew its name. This book, the accompanying Web site (http://awt.grc.nasa.gov), and other documentation have been created to resurrect the esteemed reputation of this once-vital and historically significant facility. The AWT's unrivaled capability to test full-scale engines in simulated altitude conditions advanced the development of the jet engine considerably during its formative period in the 1940s and in its maturity in the 1950s. The AWT was the nation's first wind tunnel built specifically to study the operation of engines. Its ability to consistently re-create flight conditions allowed researchers to systematically study engine behavior and perfect innovations such as the afterburner and the variable-area nozzle. Between 1959 and 1963 the AWT was slowly transformed into two large test chambers. The tunnel's simulated high-altitude conditions allowed NASA to cancel costly and time-consuming flight testing for Project Mercury. Afterward the tunnel was converted into one of the nation's first large vacuum chambers and renamed the "Space Power Chambers" (SPC). It was used to quickly remedy a number of problems for the Centaur second-stage rocket. The SPC tests allowed the Centaur to sustain its tight schedule for the Surveyor and later orbiting observatory missions. Use of the facility tapered off in the 1970s, and an effort to resurrect the wind tunnel failed in the early 1980s. After years of neglect, the tunnel was demolished in late 2008 and spring 2009. NASA's historical publications tend to focus on center histories, specific programs (particularly the human space program), or chronologies and other reference materials. The NASA Glenn Research Center has carved out a niche by writing the histories of several of its research facilities. The Icing Research Tunnel, Rocket Engine Test Facility, and Plum Brook Reactor have all been documented in recent years. These three books appear to be the only single-facility studies in NASA's historical collection. Certainly the center and program histories describe test facilities, but they are mostly portrayed as research tools contributing to a larger complex or project. The histories of facilities, therefore, provide a unique perspective. In some cases, the facilities have made long-term contributions to a specific program or field, such as the Icing Research Tunnel and the field of icing research. Other facilities, however, can serve as a useful lens through which to view the progression of research, technology, and the larger laboratory over a long period of time. The AWT, with its 30-year operational career and its contributions to the turbojet and space revolutions, falls into this latter category. The story is important for several reasons. First, it demonstrates that the ability to adapt to technological changes is vital for large test facilities. Long-term investment in test facilities differentiated the National Advisory Committee for Aeronautics (NACA) from manufacturers, the military, and its counterparts in other countries.

Download or read book NASA Lewis 8 By 6 Foot Supersonic Wind Tunnel User Manual written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-29 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: The 8- by 6-Foot Supersonic Wind Tunnel (SWT) at Lewis Research Center is available for use by qualified researchers. This manual contains tunnel performance maps which show the range of total temperature, total pressure, static pressure, dynamic pressure, altitude, Reynolds number, and mass flow as a function of test section Mach number. These maps are applicable for both the aerodynamic and propulsion cycle. The 8- by 6-Foot Supersonic Wind Tunnel is an atmospheric facility with a test section Mach number range from 0.36 to 2.0. General support systems (air systems, hydraulic system, hydrogen system, infrared system, laser system, laser sheet system, and schlieren system are also described as are instrumentation and data processing and acquisition systems. Pretest meeting formats are outlined. Tunnel user responsibility and personal safety requirements are also stated. Soeder, Ronald H. Glenn Research Center...