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Thermal Effects On Static Aeroelastic Stability And Control Methods Of Predicting Structural Temperatures Due To Aerodynamic Heating By A H Blessing
Download Thermal Effects On Static Aeroelastic Stability And Control Methods Of Predicting Structural Temperatures Due To Aerodynamic Heating By A H Blessing full books in PDF, epub, and Kindle. Read online Thermal Effects On Static Aeroelastic Stability And Control Methods Of Predicting Structural Temperatures Due To Aerodynamic Heating By A H Blessing ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Thermal Effects on Static Aeroelastic Stability and Control: Methods of predicting structural temperatures due to aerodynamic heating, by A. H. Blessing by : Bell Aircraft Corp
Download or read book Thermal Effects on Static Aeroelastic Stability and Control: Methods of predicting structural temperatures due to aerodynamic heating, by A. H. Blessing written by Bell Aircraft Corp and published by . This book was released on 1959 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Thermal Effects on Static Aeroelastic Stability and Control: sup. Description and results of tests conducted to determine the thermally affected behavior of corrugated multiweb wing structures, by J. F. Quinn by : Bell Aircraft Corp
Download or read book Thermal Effects on Static Aeroelastic Stability and Control: sup. Description and results of tests conducted to determine the thermally affected behavior of corrugated multiweb wing structures, by J. F. Quinn written by Bell Aircraft Corp and published by . This book was released on 1959 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Thermoelastic Effects on Hypersonic Stability and Control: Hypersonic aerodynamics by : James R. Batt
Download or read book Thermoelastic Effects on Hypersonic Stability and Control: Hypersonic aerodynamics written by James R. Batt and published by . This book was released on 1963 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Aeroelastic Effects on Static Stability and Control: Aeroelastic interaction, by V. W. Donato by : Bell Aircraft Corporation
Download or read book Supersonic Aeroelastic Effects on Static Stability and Control: Aeroelastic interaction, by V. W. Donato written by Bell Aircraft Corporation and published by . This book was released on 1958 with total page 374 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book National Union Catalog written by and published by . This book was released on 1970 with total page 632 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes entries for maps and atlases.
Book Synopsis Proceedings of Symposium on Aerothermoelasticity by : David M. Jones
Download or read book Proceedings of Symposium on Aerothermoelasticity written by David M. Jones and published by . This book was released on 1962 with total page 1032 pages. Available in PDF, EPUB and Kindle. Book excerpt: A symposium on Aerothermoelasticity was held to present the latest significant developments in each scientific area and engineering area that comprise the component parts of this technology. New and significant contributions were presented in four technical areas consisting of dynamic aerothermoelasticity (flutter), stability and control, thermodynamics and aerodynamics (or aerothermodynamics), and structures including material and construction concepts. Categories important and significant to each technical area are discussed state-of-the-art wise. In addition, 26 separate papers are given on items of special importance.
Book Synopsis Procedures for Including Temperature Effects in Structural Analyses of Elastic Wings - Part I by : William R. Mills
Download or read book Procedures for Including Temperature Effects in Structural Analyses of Elastic Wings - Part I written by William R. Mills and published by . This book was released on 1958 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Methods for Determining the Optimum Design of Structures Protected from Aerodynamic Heating and Application to Typical Boost-glide Or Reentry Flight Paths by : Robert S. Harris (Jr.)
Download or read book Methods for Determining the Optimum Design of Structures Protected from Aerodynamic Heating and Application to Typical Boost-glide Or Reentry Flight Paths written by Robert S. Harris (Jr.) and published by . This book was released on 1962 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: General equations are developed for the design of efficient structures protected from thermal environments typical of those encountered in boost-glide or atmospheric-reentry conditions. The method is applied to insulated heat-sink stressed-skin structures and to internally cooled insulated structures. Plates loaded in compression are treated in detail. Under limited conditions of plate buckling, high loading, and short flight periods, and for aluminum structures only, the weights of both configurations are nearly equal. Load parameters are found and are similar to those derived in previous investigations for the restricted case of a constant equilibrium temperature at the outside surface of the insulation.
Book Synopsis The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight by : Richard Scherrer
Download or read book The Effects of Aerodynamic Heating and Heat Transfer on the Surface Temperature of a Body of Revolution in Steady Supersonic Flight written by Richard Scherrer and published by . This book was released on 1947 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approximate method for determining the convective cooling requirement in the laminar-boundary-layer region of a body of revolution in high-speed flight was developed and applied to an example body. The cooling requirement for the example body was determined as a function of Mach number, altitude, size, and a surface-temperature parameter. The maximum value of Mach number considered was 3.0 and the altitudes considered were those within the lower constant-temperature region of the atmosphere (40,000 to 120,000 ft). The extent of the laminar boundary layer was determined approximately at each condition as a function of the variables considered.
Book Synopsis A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-speed Aircraft by : Robert D. Quinn
Download or read book A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-speed Aircraft written by Robert D. Quinn and published by . This book was released on 2000 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.
Book Synopsis Thermal Structures for Aerospace Applications by : Earl Arthur Thornton
Download or read book Thermal Structures for Aerospace Applications written by Earl Arthur Thornton and published by AIAA. This book was released on 1996 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High Temperature Effects in Aircraft Structures by : Nicholas John Hoff
Download or read book High Temperature Effects in Aircraft Structures written by Nicholas John Hoff and published by . This book was released on 1958 with total page 398 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies by : James E. Brunk
Download or read book Free Flight Hypersonic Heat Transfer and Boundary Layer Transition Studies written by James E. Brunk and published by . This book was released on 1961 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959, with blunted and sharp 20 degree half angle nose cones, respectively. Round A-40 also incorporated nose cone incidence and a pitch disturber rocket. A maximum flight velociety of 5800 feet per second was attained, corresponding to a local shap cone Mach number and unit Reynolds number of 3.4 and 50 x 10(6) per foot respectively. Fligh dynamics data for the second stage of Round A-40 were obtained from analyses of the vector angle of attack history. The measured maximum trim angle of attack (1.5 degrees) agreed closely with the predicted trim based on an elastic structure and a nose cone incidence of 0.36 degrees. Surface temperatures and aerodynamic heating rates were obtained for one station and three radial positions on the conical portion of the blunted nose cone (Round A-40) and at 3 stations on each of the two longitudinal rays on the sharp cone (Round A-41). In addition, the temperature and heating rates were determined on the cylindrical portion of the Round A-41 payload and on the base of on Stage II fin for both vehicles. The maximum heating rate for the sharp cone was about 30 percent greater for the blunt cone as a result of higher local Mach numbers and Reynolds numbers on the sharp cone. Correlation of the blunted cone circumferential heating rates with the measured angle of attack showed that only a small increase in heating rate (less than about 5 percent increase from the zero angle of attack heating rate) occurs on the windward ray for turbulent heating conditions. The measured decrease in Stanton mumber with increasing Reynolds number (running length) for the sharp cone was found to be in close agreement with turbulent flow theory. Boundary layer transition reversal from turbulent to laminar flow was experienced on both the sharp and blunted tip cones. Transition reversal for the sharp cone, which had almost twice the local Mach number of the blunted cone, was found to occur at an enthalpy ratio, hw/hr, 30 percent greater than for the blunted cone. For both cones turbulent flow occurred within the Mach number and enthalpy region for complete stability of two dimensional disturbance as defined by Dunn and Lin. The possible effects of surface roughness in producing the observed transition reversal are discussed.
Book Synopsis Optimum Design of Insulated Tension Members Subjected to Aerodynamic Heating by : John R. Davidson
Download or read book Optimum Design of Insulated Tension Members Subjected to Aerodynamic Heating written by John R. Davidson and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Elevated-temperature Tests Under Static and Aerodynamic Conditions on Honeycomb-core Sandwich Panels by : Joseph M. Groen
Download or read book Elevated-temperature Tests Under Static and Aerodynamic Conditions on Honeycomb-core Sandwich Panels written by Joseph M. Groen and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Thermostructural Analysis of Unconventional Wing Structures of a Hyper-X Hypersonic Flight Research Vehicle for the Mach 7 Mission by : William L. Ko
Download or read book Thermostructural Analysis of Unconventional Wing Structures of a Hyper-X Hypersonic Flight Research Vehicle for the Mach 7 Mission written by William L. Ko and published by . This book was released on 2001 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer, thermal stresses, and thermal buckling analyses were performed on the unconventional wing structures of a Hyper-X hypersonic flight research vehicle (designated as X-43) subject to nominal Mach 7 aerodynamic heating. A wing midspan cross was selected for the the heat transfer and thermal stress analyses. Thermal buckling analysis was performed on three regions of the wing skin (lower or upper); 1) a fore wing panel, 2) an aft wing panel, and 3) a unit panel at the middle of the aft wing panel. A fourth thermal buckling analysis was performed on a midspan wing segment. The unit panel region is identified as the potential thermal buckling initiation zone. Therefore, thermal buckling analysis of the Hyper-X wing panels could be reduced to the thermal buckling analysis of that unit panel. "Buckling temperature magnification factors" were established. Structural temperature-time histories are presented. The results show that the concerns of shear failure at wing and spar welded sites.
Book Synopsis The Analytical Determination of the Thermal Response of a Typical Aircraft Structure Subjected to Transient External Heating and Cooling by : Thomas N. Bernstein
Download or read book The Analytical Determination of the Thermal Response of a Typical Aircraft Structure Subjected to Transient External Heating and Cooling written by Thomas N. Bernstein and published by . This book was released on 1966 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The thermal analysis is presented of a portion of the external surface thermal protection system and load bearing structure of a hypersonic vehicle, whose mission consists of a climb-out to 100,000 feet, cruise at Mach 6, descent, and a final phase, termed turn around, which includes landing rollout, refueling and maintenance. Temperature-dependent thermo-physical properties are utilized and compared to results obtained for constant thermo-physical properties.
