Skin friction correlations for high enthalpy flows

Hazelton, David; Bowersox, Rodney D. W.

doi:10.2514/6.1998-1636

Cited by 2 publications

(1 citation statement)

References 11 publications

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“…Two studies have investigated means of removing the perfect gas assumptions from the conventional compressible turbulent correlations. Using the Crocco relation, Wallace (1967) modified the correlation of Spalding & Chi (1964), and more recently, Hazelton & Bowersox (1998) examined the effect of the calorically perfect gas assumption on skin-friction levels predicted by van Driest II (1956). When compared to a high-enthalpy modified form, the perfect gas theory increasingly underestimated C f as the free-stream Mach number and, hence, flow stagnation enthalpy was increased.…”

Section: Turbulent Boundary Layersmentioning

confidence: 99%

Skin-friction measurements in high-enthalpy hypersonic boundary layers

2003

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Skin-friction measurements are reported for high-enthalpy and high-Mach-number laminar, transitional and turbulent boundary layers. The measurements were performed in a free-piston shock tunnel with air-flow Mach number, stagnation enthalpy and Reynolds numbers in the ranges of 4.4–6.7, 3–13 MJ kg$^{-1}$ and $0.16\times 10^{6}$–$21\times 10^{6}$, respectively. Wall temperatures were near 300 K and this resulted in ratios of wall enthalpy to flow-stagnation enthalpy in the range of 0.1–0.02. The experiments were performed using rectangular ducts. The measurements were accomplished using a new skin-friction gauge that was developed for impulse facility testing. The gauge was an acceleration compensated piezoelectric transducer and had a lowest natural frequency near 40 kHz. Turbulent skin-friction levels were measured to within a typical uncertainty of ± 7%. The systematic uncertainty in measured skin-friction coefficient was high for the tested laminar conditions; however, to within experimental uncertainty, the skin-friction and heat-transfer measurements were in agreement with the laminar theory of van Driest (1952). For predicting turbulent skin-friction coefficient, it was established that, for the range of Mach numbers and Reynolds numbers of the experiments, with cold walls and boundary layers approaching the turbulent equilibrium state, the Spalding & Chi (1964) method was the most suitable of the theories tested. It was also established that if the heat transfer rate to the wall is to be predicted, then the Spalding & Chi (1964) method should be used in conjunction with a Reynolds analogy factor near unity. If more accurate results are required, then an experimentally observed relationship between the Reynolds analogy factor and the skin-friction coefficient may be applied.

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Section: Turbulent Boundary Layersmentioning

confidence: 99%

Skin-friction measurements in high-enthalpy hypersonic boundary layers

2003

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Design and Applications of Preliminary Evaluation Platform of Aerodynamic Forces for Supersonic/Hypersonic Vehicles

2018

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Rapid evaluation of aerodynamic forces is a key technology in conceptual and preliminary performance assessment and design optimization for supersonic/hypersonic vehicles, which is expected to achieve a balance between accuracy and time. In this paper, the preliminary evaluation platform of aerodynamic forces is built based on the physical theories and engineering methods. This platform computes the local velocity vector by using the streamline tracing technology, and extracts the pressure and friction coefficients by calling methods in method database. Furthermore, an example based on HL-20 is brought out. A good agreement is obtained by comparing the calculated results via CFD with the experimental. Also, a good angle of attack compatibility of streamline tracing technology is concluded. This platform has a computation time less than that via CFD and an flight range greater than that via wind tunnel. Finally, the simple flight dynamics simulation is taken out and the synergetic process is verified.

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Skin friction correlations for high enthalpy flows

Cited by 2 publications

References 11 publications

Skin-friction measurements in high-enthalpy hypersonic boundary layers

Skin-friction measurements in high-enthalpy hypersonic boundary layers

Design and Applications of Preliminary Evaluation Platform of Aerodynamic Forces for Supersonic/Hypersonic Vehicles

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