Book ChapterDOI
Eddy Resolving Simulations of Intake Under Crosswinds
Nagabhushana Rao Vadlamani,Paul G. Tucker +1 more
- pp 523-529
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In this article, the authors used eddy resolving simulations to capture the flow over the intake lip under cross-winds and further explore effects of the Reynolds number on fuel consumption.Abstract:
Modern aircraft engine designs with higher bypass ratio and lower fan pressure ratio offer significant fuel burn benefits of upto 25%. To compensate for the additional increase in the drag and weight, relatively shorter intakes and nacelles are employed. However, shorter intakes suffer under off-design conditions of high incidence and crosswinds. The flow experiences severe acceleration around the intake lip, relaminarization, flow separation and transition to turbulence. Using eddy resolving simulations, the current paper aims to capture the flow over the intake lip under crosswinds and further explore effects of the Reynolds number.read more
Citations
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Journal ArticleDOI
Dynamics of Bypass Transition Behind Roughness Element Subjected to Pulses of Free-Stream Turbulence
TL;DR: In this paper , the authors explored the dynamics of bypass transition of a zero pressure gradient boundary layer transitioning under the combined influence of an isolated roughness element with pulses of free-stream turbulence (FST) and found that the transition is triggered due to the interaction of the FST-induced Klebanoff streaks with the roughness-induced streamwise vortices.
Journal ArticleDOI
Quasi 3D Nacelle Design to Simulate Crosswind Flows: Merits and Challenges
TL;DR: In this paper, a numerical framework is set up to reproduce the general flow characteristics under crosswinds with increasing engine mass flow rate, which include: low-speed separation, attached flow and high speed shock-induced separation.
Journal ArticleDOI
Riblet Performance Beneath Transitional and Turbulent Boundary Layers at Low Reynolds Numbers
Sivaramakrishnan Malathi Ananth,Aditya Vaid,Nagabhushana Rao Vadlamani,Massimiliano Nardini,Melissa Kozul,Richard D. Sandberg +5 more
TL;DR: In this article , the effect of riblets on the mean and turbulent statistics of a zero-pressure-gradient boundary layer is examined. And the V-shaped riblet with both sharp and curved tips (and valleys) are also explored.
Journal ArticleDOI
Profile Loss Reduction of High Lift Turbine Blades With Rough and Ribbed Surfaces
Ananth Sivaramakrishnan Malathi,Massimiliano Nardini,Aditya Vaid,Nagabhushana Rao Vadlamani,Richard D. Sandberg +4 more
TL;DR: In this article , the authors explore a strategy where the losses in both the transitional and turbulent boundary layers can be reduced by employing surface roughness in the transitional regime to reduce the separation bubble-related losses and riblets in the turbulent regime to further reduce the losses due to the turbulent wetted area.
References
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Journal ArticleDOI
A High-Order Compact Finite-Difference Scheme for Large-Eddy Simulation of Active Flow Control
TL;DR: In this article, the authors present a computational approach for large-eddy simulation of flows with active control, where the numerical scheme is predicated upon an implicit time-marching algorithm and utilizes a high-order compact finite-difference approximation to represent spatial derivatives.
Journal ArticleDOI
Ultrashort Nacelles for Low Fan Pressure Ratio Propulsors
TL;DR: In this article, an integrated fan-nacelle design framework is presented for low-FPR propulsors where fan and nacelle are more closely coupled than in current turbofan engines, combining a spline-based inlet design tool with a fast and reliable body-force-based approach for the fan rotor and stator blade rows.
Journal ArticleDOI
Large-Eddy Simulation of Compressible Transitional Flows in a Low-Pressure Turbine Cascade
Kazuo Matsuura,Chisachi Kato +1 more
TL;DR: In this article, large-eddy simulation of compressible transitional flows in a low-pressure turbine cascade is performed by using sixth-order compact difference and a 10th-order filtering method.
Journal ArticleDOI
Investigation of the separation bubble formed behind the sharp leading edge of a flat plate at incidence
TL;DR: In this paper, the authors measured the separation bubble formed behind the sharp leading edge of a flat plate at low speeds and incidence, and found that the Reynolds number based on chord length ranged from 0.1 × 105 to 5.5 × 105.
Journal ArticleDOI
Distributed Roughness Effects on Transitional and Turbulent Boundary Layers
TL;DR: In this article, the transition of a subsonic boundary layer on a flat plate with roughness elements distributed over the entire surface was studied. And the effect of surface roughness on a spatially developing turbulent boundary layer (TBL) is explored.