OVERFLOW Rotor Simulations Using Advanced Turbulence and Transition Modeling

Coder, James G.

doi:10.2514/6.2017-1432

Cited by 16 publications

(6 citation statements)

References 15 publications

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“…Unlike the PSP blade at lower blade-tip Mach number of 0.585, no experimental data is available for this hover condition. Therefore, we compare the integrated blade loads with published CFD work by Coder [26] and Rohit [25] using the structured OVERFLOW CFD solver with fully turbulence models. Surface pressure coefficients are also shown for various blade pitch angles.…”

Section: Surface Pressure Predictionsmentioning

confidence: 99%

Numerical Simulations on the PSP Rotor Using HMB3

Jiménez-García¹,

Barakos²

2018

2018 AIAA Aerospace Sciences Meeting

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Section: Surface Pressure Predictionsmentioning

confidence: 99%

Numerical Simulations on the PSP Rotor Using HMB3

Jiménez-García¹,

Barakos²

2018

2018 AIAA Aerospace Sciences Meeting

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“…Both highly resolved and partially scale-resolving transition computations on the NASA PSP rotor, for instance by Coder (2017) and Vieira et al (2017) have shown the potential of a very detailed transition modeling. Nevertheless, the computational costs of these kind of investigations are still too high for industry-relevant computations.…”

Section: Numerical Setupmentioning

confidence: 99%

“…Current approaches to boundary-layer-transition modeling for computational fluid dynamics (CFD) codes face difficult challenges when implemented into rotating systems. Recent activities focused on boundary-layer transition computations of NASA's 'PSP-rotor' experiment in hover (see Coder 2017;Vieira et al 2017;Parwani and Coder 2018;Zhao et al 2018) and forward flight (Carnes and Coder 2019), as well as on the S-76 rotor in hover (Min et al 2018).…”

Section: Introductionmentioning

confidence: 99%

Unsteady boundary-layer transition measurements and computations on a rotating blade under cyclic pitch conditions

et al. 2020

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The presented work tackles the lack of experimental investigations of unsteady laminar-turbulent boundary-layer transition on rotor blades at cyclic pitch actuation, which are important for accurate performance predictions of helicopters in forward flight. Unsteady transition positions were measured on the blade suction side of a four-bladed subscale rotor by means of non-intrusive differential infrared thermography (DIT). Experiments were conducted at different rotation rates corresponding to Mach and Reynolds numbers at 75% rotor radius of up to M 75 = 0.21 and Re 75 = 3.3 × 10 5 and with varying cyclic blade pitch settings. The setup allowed transition to be measured across the outer 54% of the rotor radius. For comparison, transition was also measured using conventional infrared thermography for steady cases with collective pitch settings only. The study is complemented by numerical simulations including boundary-layer transition modeling based on semi-empirical criteria. DIT results reveal the upstream and downstream motion of boundary-layer transition during upstroke and downstroke, a reasonable comparison to experimental results obtained using the already established c p method, and noticeable agreement with numerical simulations. The result is the first systematic study of unsteady boundary-layer transition on a rotor suction side by means of DIT including a comparison to numerical computations. Abbreviations AHD Boundary-layer transition criterion according to Arnal, Habiballah and Delcourt CFD Computational fluid dynamics DIT Differential infrared thermography

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“…Wong et al [14,15] Comparisons for the integrated blade loads are given in Figure 14. Due to the lack of test data, comparisons are shown against published numerical data [42]. Figure 15 shows comparisons with the S-76 tests and predictions, showing the higher performance of the PSP rotor.…”

Section: Effect Of the Turbulence Modelmentioning

confidence: 99%

“…(d) θ 75 -C Q /σ. FoM as function of the thrust coefficient for the 1/4.71 model-scale S-76 rotor with 60% taper and 35• swept tip and PSP rotor computed with HMB and OVERFLOW CFD solvers[42].…”

mentioning

confidence: 99%