INFLUENCE OF CALORIMETER HEAT TRANSFER GAGES ON AERODYNAMIC HEATING

AIAA Journal ◽  
1963 ◽  
Vol 1 (2) ◽  
pp. 497-498 ◽  
Author(s):  
TUDOR SPRINKS
Keyword(s):  
Heat Transfer ◽  
Aerodynamic Heating

Heat Transfer and Recovery Factor of Aerodynamic Heating on a Flared Cone

AIAA Journal ◽  
2021 ◽  
pp. 1-9
Author(s):  
Mingjie Zhang ◽  
Wufei Si ◽  
Cunbiao Lee
Keyword(s):  
Heat Transfer ◽  
Recovery Factor ◽  
Aerodynamic Heating

A Procedure to Evaluate the Thermal Response of a Multilayered Thermal Protection System Subjected to Aerodynamic Heating

2009 ◽  
Author(s):  
Michele Ferraiuolo ◽  
Oronzio Manca ◽  
Aniello Riccio
Keyword(s):  
Heat Transfer ◽  
Thermal Protection ◽  
Outer Space ◽  
Thermal Response ◽  
Temperature Limit ◽  
The Body ◽  
Heat Radiation ◽  
Aerodynamic Heating ◽  
Internal Temperature ◽  
Design Activities

Next generation reusable re-entry vehicles must be capable of sustaining consistent repeated aero-thermal loads without damage or deterioration. This means that such structures must tolerate the high temperatures engendered by aero-thermal re-entry fluxes due to the establishment of a hypersonic regime over the body. Thermal Protection Systems (TPS) are used to maintain a reusable launch vehicle’s structural temperature within acceptable limits during re-entry flights; that is, internal temperature should not overcome the temperature limit use of the internal structure. TPS are usually composed by several layers made of different materials. Heat transfer through a multilayer insulation during atmospheric re-entry involves combined modes of heat transfer: heat conduction through the solid, heat radiation to the outer space etc. In the frame of TPS design activities a procedure based on one dimensional analytical solutions of transient nonlinear analyses has been developed in order to estimate the temperature variation with time and space of a multilayered body subjected to aerodynamic heating inside a radiating space. Since internal temperature values of TPSs of re-entry vehicles cannot exceed certain values, that procedure allows to quickly evaluate those temperature values and to preliminary size layer thicknesses before preparing and performing Finite Element analyses.

scholarly journals A case study on the aerodynamic heating of a hypersonic vehicle

2012 ◽  
Vol 116 (1183) ◽  
pp. 873-893 ◽  
Author(s):  
M. Mifsud ◽  
D. Estruch-Samper ◽  
D. MacManus ◽  
R. Chaplin ◽  
J. Stollery
Keyword(s):  
Heat Transfer ◽  
Turbulent Flows ◽  
Hypersonic Vehicle ◽  
Boundary Layer Transition ◽  
Vehicle Body ◽  
Scale Model ◽  
Aerodynamic Heating ◽  
Complex Flow ◽  
Layer Transition

Abstract A Parabolised Navier-Stokes (PNS) flow solver is used to predict the aerodynamic heating on the surface of a hypersonic vehicle. This case study highlights some of the main heat flux sensitivies to various conditions for a full-scale vehicle and illustrates the use of different complimentary methods in assessing the heat load for a realistic application. Different flight phases of the vehicle are considered, with freestream conditions from Mach 4 to Mach 8 across a range of altitudes. Both laminar and turbulent flows are studied, together with the effect of the isothermal wall temperature, boundary-layer transition location and body incidence. The effect of the Spalart-Allmaras and Baldwin-Lomax turbulent models on the heat transfer distributions is assessed. A rigorous assessment of the computations is conducted through both iterative and grid convergence studies and a supporting experimental investigation is performed on a 1/20th scale model of the vehicle’s forebody for the validation of the numerical results. Good agreement is found between the PNS predictions, measurements and empirical methods for the vehicle forebody. The present PNS approach is shown to provide useful predictions of the heat transfer over the axisymmetric vehicle body. A highly complex flow field is predicted in the fin-body-fin region at the rear of the vehicle characterised by strong interference effects which limit the predictions over this region to a predominately qualitative level.

scholarly journals Experimental Study on Aerodynamic Heating Induced by Dual Injections into Hypersonic Cross Flow

2017 ◽  
Vol 2017 ◽  
pp. 1-16 ◽  
Author(s):  
Masato Taguchi ◽  
Koichi Mori ◽  
Yoshiaki Nakamura
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Single Injection ◽  
Surface Heat ◽  
Aerodynamic Heating ◽  
Temperature Sensitive ◽  
Maximum Heat ◽  
Short Spacing ◽  
Surface Heat Transfer ◽  
Maximum Heat Flux

In this study, the distribution of surface heat transfer induced by dual side-jets injected into a hypersonic flow has been visualized using a temperature sensitive paint. The experiments were performed in both tandem and parallel injector arrangements, and the spacing between the injection holes was taken as a parameter in each arrangement. As a result, the aerodynamic heating in the separated region of the boundary layer and in the horseshoe vortex was clearly visualized. In the tandem arrangements, heat transfer remarkably increased immediately upstream of the front injector. The distributions and the intensity of surface heat transfer were similar to those caused by the single injection. On the other hand, in the parallel arrangements, the extent of the separation nearly doubled, and the maximum heat flux decreased to less than half of that from the single injection. The global distribution of heat transfer varied significantly as the injector spacing was changed. When the injectors were positioned with a large spacing, the interaction between the side-jets was relatively lowered, and thus distribution, as for the single injector, was induced around each injection hole individually. In contrast, with a short spacing, the dual injection behaved as a single obstacle. The most effective reduction of maximum heat flux was achieved with an intermediate injector spacing.

scholarly journals Numerical Study on Transient Heat Transfer of a Quartz Lamp Heating System

2014 ◽  
Vol 2014 ◽  
pp. 1-11 ◽  
Author(s):  
Yan Yu ◽  
Pingjian Ming ◽  
Song Zhou
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Finite Volume Method ◽  
Finite Volume ◽  
High Speed ◽  
Numerical Study ◽  
Heating System ◽  
Aerodynamic Heating ◽  
Thermal Testing ◽  
Volume Method

Thermal ground testing is an accepted and frequently used method for simulating the aerodynamic heating of high speed flight vehicles. A numerical method based on a finite volume method for a quartz lamp heating system, used in thermal testing, is proposed. In this study, the unstructured finite-volume method (UFVM) for radiation has been formulated and implemented in a fluid flow solver GTEA on unstructured grids. For comparison and validation of the proposed method, a 2D furnace with cooling pipes was chosen. The results obtained from the proposed FVM agreed well with the exact solutions. Numerical results show that the quartz lamp can be simplified as a slat with the same temperature radiation source, and a simplified 2D thermal testing case was then simulated with the coupling effects of radiation, convection, and conduction heat transfer. Different temperature loading curves and ratios of intervals between the lamps and lamp length (l/s) were studied using the proposed method. The radiation heat flux on the metal surface was a wave-shaped curve. Comparing the different interval ratios, we found that the smaller the interval ratio, the larger the maximum value and the smaller the difference between the maximum and minimum heat flux.

On the Analysis of the Aerodynamic Heating Problem

2010 ◽  
Vol 132 (12) ◽  
Author(s):  
A. Özer Arnas ◽  
Daisie D. Boettner ◽  
Gunnar Tamm ◽  
Seth A. Norberg ◽  
Jason R. Whipple ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Analytical Solution ◽  
Graduate Education ◽  
Convective Heat Transfer ◽  
Convective Heat ◽  
Analytical Study ◽  
Point Of View ◽  
Aerodynamic Heating ◽  
Numerical Studies

A complete analytical solution to the problem of aerodynamic heating is lacking in heat transfer textbooks, which are used for undergraduate and graduate education. There are many issues that are very important from a convective heat transfer point of view. In practice, poor analyses lead to poor design, thus faulty manufacturing. Since, over the years analysis has given way to numerical studies, the instructors do not take the necessary time to go through analytical details. Thus the students just use the results without any awareness of how to get them and the inherent limitations of the analytical solution. The only intent of this paper, therefore, is to present the detailed analytical study of the aerodynamic heating problem.

Numerical investigation of the effect of disk position on the aerodynamic heating and drag of a spiked blunt body in hypersonic flow

2018 ◽  
Vol 122 (1258) ◽  
pp. 1916-1942 ◽  
Author(s):  
R. Yadav ◽  
A. Bodavula ◽  
S. Joshi
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Blunt Body ◽  
Aerodynamic Drag ◽  
Heat Fluxes ◽  
Aerodynamic Heating ◽  
Base Diameter ◽  
Transfer Rates ◽  
Hypersonic Speed ◽  
Single Disk

ABSTRACTDetailed numerical simulations have been carried out on a spiked blunt body with multiple hemispherical disks using a commercial CFD code in order to investigate their effectiveness in reducing the aerodynamic drag and heating. The base configuration is a hemispherical cylinder whose diameter is 40 mm with an overall length of 70 mm. The lengths of the aerospikes investigated are 1, 1.5, 2 and 2.5 times the base diameter of the cylinder and the radii of the aerodisks are varied between 0.05, 0.1, 0.15 and 0.2 times the diameter of the cylinder. Besides these, the position of the aerodisks is varied with the rearmost aerodisk placed at 25%, 50% and 75% along the length of the aerospike and the intermediate aerodisk for three-disk cases, positioned at 25%, 50% and 75% of the distance between the front and the rearmost disk. All the investigations have carried out at a freestream Mach number of 6.2 and Reynolds number of 2.64 × 107/m. It has been observed that the multidisk spikes are advantageous for the purpose of reduction of both aerodynamic drag and heating at hypersonic speed. The two aerodisk spiked configurations show better results in terms of aerodynamic heating and drag in comparison to the single-disk aerospikes while the three-disk spikes yield only a marginal reduction in aerodynamic drag over the two-disk configurations. For reduction of heat fluxes and heat transfer rates though, the three-disk configurations are extremely advantageous and give much larger reductions are compared to the two-disk configurations.

Effects of structural thermal boundary conditions on hypersonic aerothermoelasticity of all-movable control surface

2018 ◽  
Vol 233 (7) ◽  
pp. 2673-2689 ◽  
Author(s):  
Kun Ye ◽  
ZhengYin Ye ◽  
XianZong Meng ◽  
Zhan Qu
Keyword(s):  
Heat Transfer ◽  
Temperature Distribution ◽  
Boundary Conditions ◽  
Thermal Stresses ◽  
Stokes Equations ◽  
Thermal Environment ◽  
The Body ◽  
Control Surface ◽  
Aerodynamic Heating ◽  
Thermal Boundary Conditions

Structural thermal boundary conditions are usually simplified in the aerothermoelastic analysis. However, it will influence the heat transfer, the temperature distribution, and the structure stiffness, which have effects on the accurate prediction of the aerothermoelastic characteristics. In this study, an aerothermoelastic framework for hypersonic vehicles is developed, and the effects of structural thermal boundary conditions on aerothermoelasticity of all-movable control surface are investigated. The Reynold’s averaged Navier–Stokes equations are solved by computational fluid dynamics method to obtain the thermal environment. The transient heat transfer, the thermal stress, and the structure mode are analyzed by using finite element method. Finally, the local piston theory is used to calculate the unsteady aerodynamic force, and aeroelastic characteristics are analyzed in the state space. Aerothermoelastic characteristics of three different structural thermal boundaries are investigated in detail, including aerodynamic heating only on control surface; aerodynamic heating on both the control surface and the shaft; and aerodynamic heating on the control surface, the shaft, and the body. The results show that the heat transfer process, the temperature distribution, the thermal stresses, and the natural frequencies of the structure are influenced significantly by structural thermal boundary conditions especially in the shaft. Furthermore, the aerothermoelastic stability margin is affected ultimately.

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