scholarly journals Aerodynamic Heating at Hypersonic Speed

10.5772/13890 ◽  
2011 ◽  
Author(s):  
Andrey B.
Keyword(s):  
Aerodynamic Heating ◽  
Hypersonic Speed

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.

Aerospace Thermal-Structural Testing Technology

1997 ◽  
Vol 50 (9) ◽  
pp. 477-498 ◽  
Author(s):  
Earl A. Thornton
Keyword(s):  
High Speed ◽  
Structural Testing ◽  
Aerodynamic Heating ◽  
Heating And Cooling ◽  
Structural Test ◽  
Space Experiments ◽  
Test Technology ◽  
Testing Technology ◽  
Structural Tests ◽  
Structural Boundary

This review article describes aerospace thermal-structural testing technology. It begins with discussions of aerodynamic heating and space radiation heating. The review continues with a general discussion of thermal-structural test technology including heating and cooling, instrumentation, and thermal-structural boundary conditions. Then illustrative thermal structural tests are presented for high speed flight in the atmosphere and flight in space. Experiments conducted in the laboratory as well as flight tests are described. Several experiments are reviewed to demonstrate the diversity of thermal-structural phenomena. This article includes 120 references.

Structural Response of Fiber Composite Fan Blades

1975 ◽  
Author(s):  
C. C. Chamis ◽  
M. D. Minich
Keyword(s):  
Quantitative Data ◽  
Fiber Composite ◽  
Structural Response ◽  
Aerodynamic Heating ◽  
Analysis Method ◽  
Centrifugal Forces ◽  
The Core ◽  
Composite Mechanics ◽  
Composite Blades ◽  
Load Conditions

A fiber composite airfoil, typical for high-tip speed compressor applications, is subjected to load conditions anticipated to be encountered in such applications, and its structural response is theoretically investigated. The analysis method used consists of composite mechanics embedded in pre- and post-processors and coupled with NASTRAN. The load conditions examined include thermal due to aerodynamic heating, pressure due to aerodynamic forces, centrifugal, and combinations of these. The various responses investigated include root reactions due to various load conditions, average composite and ply stresses, ply delaminations, and the fundamental modes and the corresponding reactions. The results show that the thermal and pressure stresses are negligible compared to those caused by the centrifugal forces. Also, the core-shell concept for composite blades is an inefficient design (core plies not highly stressed) and appears to be sensitive to interply delaminations. The results are presented in graphical and tabular forms to illustrate the types and amount of data required for such an analysis, and to provide quantitative data of the various responses which can be helpful in designing such composite blades.

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