An Experimental Study of the Flowfield on a Semispan Rectangular Wing with a Simulated Glaze Ice Accretion

Wind tunnel experiments were conducted in order to study the effect of a simulated glaze ice accretion on the flowfield of a semispan, reflection-plane, rectangular wing at Re = 1.5 million and M = 0.12. A laser Doppler velocimeter was used to map the flowfield on the upper surface of the model in both the clean and iced configurations at alpha = 0, 4, and 8 degrees angle of attack. At low angles of attack, the massive separation bubble aft of the leading edge ice horn was found to behave in a manner similar to laminar separation bubbles. At alpha = 0 and 4 degrees, the locations of transition and reattachment, as deduced from momentum thickness distributions, were found to be in good agreement with transition and reattachment locations in laminar separation bubbles. These values at y/b = 0.470, the centerline measurement location, matched well with data obtained on a similar but two dimensional model. The measured velocity profiles on the iced wing compared reasonably with the predicted profiles from Navier-Stokes computations. The iced-induced separation bubble was also found to have features similar to the recirculating region aft of rearward-facing steps. At alpha = 0 degrees and 4 degrees, reverse flow magnitudes and turbulence intensity levels were typical of those found in the recirculating region aft of rearward-facing steps. The calculated separation streamline aft of the ice horn at alpha = 4 degrees, y/b = 0.470 coincided with the locus of the maximum Reynolds normal stress. The maximum Reynolds normal stress peaked at two locations along the separation streamline. The location of the first peak-value coincided with the transition location, as deduced from the momentum thickness distributions. The location of the second peak was just upstream of reattachment, in good agreement with measurements of flows over similar obstacles. The intermittency factor in the vicinity of reattachment at alpha = 4 degrees, y/b = 0.470, revealed the time-dependent nature of the reattachment process. The size and extent of the separation bubble were found to be a function of angle of attack and the spanwise location. Three dimensional effects were found to be strongest at alpha = 8 degrees. The calculated separation and stagnation streamlines were found to vary little with spanwise location at alpha = 0 degrees. The calculated separation streamlines at alpha = 4 degrees revealed that the bubble was largest near the centerline measurement plane, whereas the tip-induced vortex flow and the model root-tunnel wall boundary-layer interaction reduced the size of the bubble. These effects were found to be most dramatic at alpha = 8 degrees

Effect of In-Flight Ice Accretion on the Performance of a Multi-Element Airfoil

The effects of potential in-flight ice accretion on the aerodynamic performance of a multi-element high-lift airfoil have been investigated at moderate-to-high Reynolds numbers. The investigation was conducted in the Low Turbulence Pressure Tunnel (LTPT) at NASA Langley Research Center. Simulated ice shapes obtained from earlier testing in the Icing Research Tunnel (IRT) at NASA Lewis Research Center were used on all three elements of the multi-element configuration. Incremental performance effects due to the ice accretion are presented for both smooth and rough ice accretions. Reynolds number effects on the measured performance characteristics were also assessed. The present results confirm the importance of avoiding any ice accretions on the forward element of a lifting configuration

CFD Vision 2030 Study: A Path to Revolutionary Computational Aerosciences

This report documents the results of a study to address the long range, strategic planning required by NASA's Revolutionary Computational Aerosciences (RCA) program in the area of computational fluid dynamics (CFD), including future software and hardware requirements for High Performance Computing (HPC). Specifically, the "Vision 2030" CFD study is to provide a knowledge-based forecast of the future computational capabilities required for turbulent, transitional, and reacting flow simulations across a broad Mach number regime, and to lay the foundation for the development of a future framework and/or environment where physics-based, accurate predictions of complex turbulent flows, including flow separation, can be accomplished routinely and efficiently in cooperation with other physics-based simulations to enable multi-physics analysis and design. Specific technical requirements from the aerospace industrial and scientific communities were obtained to determine critical capability gaps, anticipated technical challenges, and impediments to achieving the target CFD capability in 2030. A preliminary development plan and roadmap were created to help focus investments in technology development to help achieve the CFD vision in 2030

An Experimental Study of the Flowfield on a Semispan Rectangular Wing With a Simulated Glaze Ice Accretion

252 p.Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 1993.The effect of a simulated glaze ice accretion on the flowfield of a semispan, reflection-plane, rectangular wing at Re = 1.5 million and M = 0.12 was investigated. A laser Doppler velocimeter was used to map the flowfield on the upper surface of the model in both the clean and iced configurations at $\alpha$ = 0, 4, and 8 degrees angle of attack.At low angles of attack, the massive separation bubble aft of the leading edge ice horn behaved in a manner similar to laminar separation bubbles. At $\alpha$ = 0\sp\circ and 4\sp\circ, the locations of transition and reattachment, as deduced from momentum thickness distributions, were in good agreement with transition and reattachment locations in laminar separation bubbles. These values at y/b = 0.470, the centerline measurement location, matched well with data obtained on a similar but 2-D model. The measured velocity profiles on the iced wing compared reasonably with the predicted profiles from Navier-Stokes computations.The iced-induced separation bubble also had features similar to the recirculating region aft of rearward-facing steps. At $\alpha$ = 0\sp\circ and 4\sp\circ, reverse flow magnitudes and turbulence intensity levels were typical of those found in the recirculating region aft of rearward-facing steps. The calculated separation streamline aft of the ice horn at $\alpha$ = 4\sp\circ, y/b = 0.470 coincided with the locus of the maximum Reynolds normal stress. The maximum Reynolds normal stress peaked at two locations along the separation streamline. The location of the first peak-value coincided with the transition location, as deduced from the momentum thickness distributions. The location of the second peak was just upstream of reattachment, in good agreement with measurements of flows over similar obstacles. The intermittency factor in the vicinity of reattachment at $\alpha$ = 4\sp\circ, y/b = 0.470, revealed the time-dependent nature of the reattachment process.The size and extent of the separation bubble were a function of angle of attack and spanwise location. Three dimensional effects were strongest at $\alpha$ = 8\sp\circ. The calculated separation and stagnation streamlines varied little with spanwise location at $\alpha$ = 0\sp\circ. The calculated separation streamlines at $\alpha$ = 4\sp\circ revealed that the bubble was largest near the centerline measurement plane, whereas the tip-induced vortex flow and the model root-tunnel wall boundary layer interaction reduced the size of the bubble. These effects were most dramatic at $\alpha$ = 8\sp\circ.U of I OnlyRestricted to the U of I community idenfinitely during batch ingest of legacy ETD

Mécanismes de déshydrogénation du méthyl-cyclohexane catalysée par des agrégats sub-nanométriques de platine supportés sur alumine gamma : études couplées DFT, cinétique expérimentale et modélisation cinétique

Le reformage catalytique vise à transformer les naphtas en aromatiques à haut indice d'octane et à produire simultanément du dihydrogène. Le catalyseur utilisé est composé d’agrégats sub-nanométriques à base de platine hautement dispersées sur un support d’alumine-gamma dont le comportement en réaction pose de nombreuses questions. Nous étudions expérimentalement et théoriquement une réaction modèle qui sonde les sites métalliques, la déshydrogénation du methyl-cyclohexane en toluène. Une compréhension détaillée à l'échelle atomique des mécanismes impliqués et des paramètres cinétiques est nécessaire. Nous avons mise en œuvre des calculs DFT (PBE et PBE-dDsC) sur un modèle pertinent Pt13/alumine-gamma, afin de déterminer les intermédiaires, les états de transition et leurs enthalpies libres. Le mécanisme a été exploré via des étapes séquentielles de rupture des liaisons C-H. Une reconstruction des agrégats se produit le long du chemin réactionnel, mettant en évidence sa fluctionalité (confirmée par dynamique moléculaire). Les enthalpies libres d’activation de la rupture C-H, de migration d’hydrogène et de reconstruction de l’agrégat ont été systématiquement déterminées à T=625 K. L'enthalpie libre la plus élevée (ΔrG‡=95 kJ/mol) est trouvée pour la troisième rupture de liaison C-H sur le methyl-cyclohexène. L'intermédiaire le plus stable est le produit adsorbé {toluène+H2}. Cependant, d’autres étapes de rupture C-H ou de désorption du toluène sont compétitives. Les constantes de vitesse des étapes élémentaires obtenues par DFT sont introduites dans 8 modèles cinétiques différents de type Langmuir-Hinshelwood (LH). La nature de l'étape déterminante de la vitesse a été choisie en fonction des constantes de vitesse de chaque étape élémentaire individuelle, ou de la prise en compte de séquences d’étapes limitantes, grâce à une analyse de type « energetic span ». Nous avons finalement expérimentalement réalisé des tests catalytiques sur Pt/γ-alumine (0.3 wt% Pt) à différentes températures, temps de contact, pressions partielles d’hydrogène et de méthylcyclohexane, pour obtenir des données cinétiques expérimentales. L'enthalpie d'activation apparente de 196 kJ/mol calculée par l’un des meilleurs modèles LH (3ème rupture C-H limitante) est proche de l’expérience (195 kJ/mol). De plus, l’évolution des vitesses de réaction en fonction des pressions partielles d'hydrogène et de méthylcyclohexane est discutée au regard de l’expérience et des modèles. Même si les tendances sont recouvrées par les modèles, des écarts théorie-expérience sont mis au jour, ce qui ouvre des perspectives vers une modélisation microcinétique future.Catalytic reforming aims at transforming naphta into high octane aromatics and producing simultaneously dihydrogen. The catalyst used is composed of platinum-based sub-nanometric clusters highly dispersed on a gamma-alumina support which behavior under reaction conditions is the subject of numerous questions. We investigate experimentally and theoretically one model reaction probing the metal sites, the dehydrogenation of methyl-cyclohexane into toluene. A detailed atomic scale understanding of the mechanisms involved, and their related kinetic parameters, is required. We undertook DFT calculations with PBE and PBE-dDsC functionals on a relevant Pt13/γ-alumina model, in order to determine the intermediates, transition states and their free energies. The reaction mechanism was explored by assuming sequential C-H breaking steps. Reconstructions of the cluster and hydrogen migrations occur along the reaction pathway, highlighting its high fluctionality (also confirmed by molecular dynamics). Free energies of activation for C-H bond breaking, H migration and cluster’s reconstruction were systematically determined at T=625 K. The highest activation Gibbs free energy (ΔrG‡=95 kJ/mol) is found for the third C-H bond breaking on methyl-cyclohexene, while the most stable intermediate is the {toluene+H2} adsorbed product. However, other C-H bond breaking steps and eventually toluene desorption may compete. A comparison with the Pt (111) surface is also given. Rate constants of elementary steps estimated by DFT are introduced in 8 Langmuir-Hinshelwood (LH) kinetic models based on a single rate determining step (RDS) concept, or on a limiting steps sequence deduced from an energetic span analysis. We finally carried out experimental tests on Pt/γ-alumina catalysts (0.3 wt% Pt) at various temperatures, space times, hydrogen and methyl-cyclohexane partial pressures, to provide experimental kinetic data. The calculated apparent activation enthalpy is predicted to be 196 kJ/mol in close agreement with the experimental one (195 kJ/mol) for the best LH model (third C-H bond breaking as RDS). Moreover, the dependence of reaction rates on hydrogen and methyl-cyclohexane partial pressures are discussed with respect to experimental trends and models. Although the main trends are recovered by the kinetic model, some discrepancies are revealed. This work paves the way for a future microkinetic modeling

Progress on Experimental and Computational Investigation of Juncture Flows

This paper describes a set of measurements taken at the Caltech Lucas Wind Tunnel, along with Computational Fluid Dynamic analyses, on a wing-body configuration. The configuration is designed to produce regions of separation in the juncture where the wing meets the body. Detailed on- and off-body measurements in the juncture flow are compared with RANS predictions. The results from the experimental measurements will become part of a database of high fidelity measurements, to be used for calibration of turbulence models and validation of emerging computational prediction techniques

Progress on Experimental and Computational Investigation of Juncture Flows

This paper describes a set of measurements taken at the Caltech Lucas Wind Tunnel, along with Computational Fluid Dynamic analyses, on a wing-body configuration. The configuration is designed to produce regions of separation in the juncture where the wing meets the body. Detailed on- and off-body measurements in the juncture flow are compared with RANS predictions. The results from the experimental measurements will become part of a database of high fidelity measurements, to be used for calibration of turbulence models and validation of emerging computational prediction techniques

Progress on Experimental and Computational Investigation of Juncture Flows

This paper describes a set of measurements taken at the Caltech Lucas Wind Tunnel, along with Computational Fluid Dynamic analyses, on a wing-body configuration. The configuration is designed to produce regions of separation in the juncture where the wing meets the body. Detailed near- and off-body stereo PIV measurements in the juncture flow are compared with predictions from computational methods based on the Reynolds Average Navier Stokes formulation. The results from the experimental measurements will become part of a database of high fidelity measurements, to be used for calibration of turbulence models and validation of emerging computational techniques

Progress on Experimental and Computational Investigation of Juncture Flows

This paper describes a set of measurements taken at the Caltech Lucas Wind Tunnel, along with Computational Fluid Dynamic analyses, on a wing-body configuration. The configuration is designed to produce regions of separation in the juncture where the wing meets the body. Detailed near- and off-body stereo PIV measurements in the juncture flow are compared with predictions from computational methods based on the Reynolds Average Navier Stokes formulation. The results from the experimental measurements will become part of a database of high fidelity measurements, to be used for calibration of turbulence models and validation of emerging computational techniques