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.

Download or read book A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High Speed Aircraft written by National Aeronautics and Space Administration (NASA) and published by . This book was released on 2018-08-27 with total page 36 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.Quinn, Robert D. and Gong, LeslieArmstrong Flight Research CenterSURFACE TEMPERATURE; COMPUTATION; PROCEDURES; TRANSIENT HEATING; ESTIMATING; SUPERSONIC SPEED; SPACE SHUTTLE ORBITERS; YF-12 AIRCRAFT; BOUNDARY LAYER TRANSITION; HEAT TRANSFER COEFFICIENTS; LAMINAR HEAT TRANSFER; RESEARCH VEHICLES...

Download or read book A Design Manual for Determining the Thermal Characteristics of High Speed Aircraft written by Harold Alexander Johnson and published by . This book was released on 1947 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Integral Approach to Transient Heat conduction Problems with Phase Transition written by Tse-Fou Zien and published by . This book was released on 1975 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approximate method for studying transient heat-conduction problems is presented. Its application to various linear problems and nonlinear problems involving phase transitions is described by means of several idealized problems. The method is basically a refined version of the well-known Karman-Pohlhausen integral technique in boundary-layer theory, and represents a further development of the basic ideas previously exploited to calculate skin friction and heat transfer in boundary-layer flows. The approximate solutions obtained are extensively compared with existing exact solutions and those of the classical Karman-Pohlhausen method. From the simplicity and accuracy of the present method as demonstrated in the results, the potential utility of the method in providing simple, engineering solutions to complex aerodynamic heating problems can be inferred.

Download or read book Real time Aerodynamic Heating and Surface Temperature Calculations for Hypersonic Flight Simulation written by Robert D. Quinn and published by . This book was released on 1990 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Computer Code SKINTEMP for Predicting Transient Missile and Aircraft Heat Transfer Characteristics written by Mary L. Cummings and published by . This book was released on 1994 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt: A FORTRAN computer code (SKINTEMP) has been developed to calculate transient missile/aircraft aerodynamic heating parameters utilizing basic flight parameters such as altitude, Mach number, and angle of attack. The insulated skin temperature of a vehicle surface on either the fuselage (axisymmetric body) or wing (two-dimensional body) is computed from a basic heat balance relationship throughout the entire spectrum (subsonic, transonic, supersonic, hypersonic) of flight. This calculation method employs a simple finite difference procedure which considers radiation, forced convection, and non-reactive chemistry. Surface pressure estimates are based on a modified Newtonian flow model. Eckert's reference temperature method is used as the forced convection heat transfer model. SKINTEMP predictions are compared with a limited number of test cases. SKINTEMP was developed as a tool to enhance the conceptual design process of high speed missiles and aircraft. Recommendations are made for possible future development of SKINTEMP to further support the design process.

Download or read book A Review of High speed Convective Heat transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Real time Aerodynamic Heating and Surface Temperature Calculations for Hypersonic Flight Simulation written by Robert D. Quinn and published by . This book was released on 1990 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Computer Code SKINTEMP for Predicting Transient Missile and Aircraft Heat Transfer Characteristics written by Mary L. Cummings and published by . This book was released on 1994 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A FORTRAN computer code (SKINTEMP) has been developed to calculate transient missile/aircraft aerodynamic heating parameters utilizing basic flight parameters such as altitude, Mach number, and angle of attack. The insulated skin temperature of a vehicle surface on either the fuselage (axisymmetric body) or wing (two-dimensional body) is computed from a basic heat balance relationship throughout the entire spectrum (subsonic, transonic, supersonic, hypersonic) of flight. This calculation method employs a simple finite difference procedure which considers radiation, forced convection, and non-reactive chemistry. Surface pressure estimates are based on a modified Newtonian flow model. Eckert's reference temperature method is used as the forced convection heat transfer model. SKINTEMP predictions are compared with a limited number of test cases. SKINTEMP was developed as a tool to enhance the conceptual design process of high speed missiles and aircraft. Recommendations are made for possible future development of SKINTEMP to further support the design process.

Download or read book Real Time Aerodynamic Heating and Surface Temperature Calculations for Hypersonic Flight Simulation written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-11 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: A real-time heating algorithm was derived and installed on the Ames Research Center Dryden Flight Research Facility real-time flight simulator. This program can calculate two- and three-dimensional stagnation point surface heating rates and surface temperatures. The two-dimensional calculations can be made with or without leading-edge sweep. In addition, upper and lower surface heating rates and surface temperatures for flat plates, wedges, and cones can be calculated. Laminar or turbulent heating can be calculated, with boundary-layer transition made a function of free-stream Reynolds number and free-stream Mach number. Real-time heating rates and surface temperatures calculated for a generic hypersonic vehicle are presented and compared with more exact values computed by a batch aeroheating program. As these comparisons show, the heating algorithm used on the flight simulator calculates surface heating rates and temperatures well within the accuracy required to evaluate flight profiles for acceptable heating trajectories. Quinn, Robert D. and Gong, Leslie Armstrong Flight Research Center RTOP 505-63-31...

Download or read book Calculation Procedure for the Determination of Surface Temperatures in High Speed Flight written by Neal Leonard Dyste and published by . This book was released on 1949 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1 90 to 3 07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Flight Measurements of Airplane Structural Temperatures at Supersonic Speeds written by Richard D. Banner and published by . This book was released on 1957 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Skin and structural temperatures have been obtained on the X-1B and X-1E research airplanes under transient aerodynamic heating conditions at speeds up to Mach numbers near 2.0. Extensive temperature measurements were obtained throughout the X-1B airplane, and temperature distributions are shown on the nose cone, the wing, and the vertical tail. Temperatures for the X-1E wing leading edge and internal wing structure were compared with similar data for the X-1B. No critical skin and structural temperatures were obtained on the two airplanes over the range of these tests. Simplified calculations of the skin temperatures in the laminar-flow regions of the nose cone and the leading edges agreed favorably with the general trends in the measured data. The flat-plate skin-temperature calculations in the turbulent-flow regions agreed favorably with the measured data on the nose cone and at the midsemispan station of the wing but overestimated the vertical-tail skin temperatures and also the upper wing skin temperature near the wing tip. The relatively low values of the upper skin temperatures that were measured at the wing tip were believed to be caused by separated-flow effects in this region.

Download or read book Heat Transfer to Bodies Traveling at High Speed in the Upper Atmosphere written by Jackson R. Stalder and published by . This book was released on 1948 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method has been developed whereby the surface temperature of bodies made be calculated for steady flight at any speed in a rarified gas. The method has been applied in the computation of surface temperatures of a plate for a range of altitudes of from 75 to 190 miles up to flight speeds of 36,000 feet per second.

Download or read book Heat Transfer Coefficients for External Surfaces of Aircraft and Missiles for Flight at Mach Numbers Up to 5 0 written by Donald Robert Haworth and published by . This book was released on 1963 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Structural Failure Analysis and Prediction Methods for Aerospace Vehicles and Structures written by Sook-Ying Ho and published by Bentham Science Publishers. This book was released on 2010 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book deals with structural failure (induced by mechanical, aerodynamic, acoustic and aero-thermal, loads, etc.) of modern aerospace vehicles, in particular high-speed aircraft, solid propellant rocket systems and hypersonic flight vehicles, where structural integrity, failure prediction and service life assessment are particularly challenging, due to the increasingly more demanding mission requirements and the use of non-traditional materials, such as non-metallic composites, in their construction. Prediction of the complex loading environment seen in high-speed operation and constitutive / fracture models which can adequately describe the non-linear behaviour exhibited by advanced alloys and composite materials are critical in analyzing the non-linear structural response of modern aerospace vehicles and structures. The state-of-the-art of the different structural integrity assessment and prediction methodologies (including non-destructive structural health monitoring techniques) used for the structural design, service life assessment and failure analysis of the different types of aerospace vehicles are presented. The chapters are written by experts from aerospace / defence research organizations and academia in the fields of solid mechanics, and structural mechanics and dynamics of aircraft, rocket and hypersonic systems. The book will serve as a useful reference document containing specialist knowledge on appropriate prediction methodologies for a given circumstance and experimental data acquired from multi-national collaborative programs.

Download or read book Finite Volume Numerical Methods for Aeroheating Rate Calculations from Infrared Thermographic Data written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-08 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The use of multi-dimensional finite volume heat conduction techniques for calculating aeroheating rates from measured global surface temperatures on hypersonic wind tunnel models was investigated. Both direct and inverse finite volume techniques were investigated and compared with the standard one-dimensional semi-infinite technique. Global transient surface temperatures were measured using an infrared thermographic technique on a 0.333-scale model of the Hyper-X forebody in the NASA Langley Research Center 20-Inch Mach 6 Air tunnel. In these tests the effectiveness of vortices generated via gas injection for initiating hypersonic transition on the Hyper-X forebody was investigated. An array of streamwise-orientated heating striations was generated and visualized downstream of the gas injection sites. In regions without significant spatial temperature gradients, one-dimensional techniques provided accurate aeroheating rates. In regions with sharp temperature gradients caused by striation patterns multi-dimensional heat transfer techniques were necessary to obtain more accurate heating rates. The use of the one-dimensional technique resulted in differences of 20% in the calculated heating rates compared to 2-D analysis because it did not account for lateral heat conduction in the model.