Browsing by Subject "Aerodynamics"
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ItemA comparative study of three methodology for modeling dynamic stall( 2002) Sankar, L.N. ; Zibi-Bailly, J. ; LeBalleur, J.C. ; Blaise, D. ; Rouzaud, O. ; Rhee, M.
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ItemA dynamic inflow-based induced power model for general and optimal rotor performance( 2016) Hong, J.S. ; Peters, D.A. ; Ormiston, R.A.
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ItemA framework for aeroelastic simulations of trimmed rotor systems in forward flight( 2004) Ven, H. van der ; Boelens, O.J.
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ItemA Large Eddy Simulation of the Fenestron® at high blade pitch angle( 2016) Marino, M. ; Gourdain, N. ; Boussuge, J.-F. ; Legras, G. ; Alfano, D.
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ItemA low cost approach to helicopter health and usage monitoring( 2006) Lee, E.C. ; Forsyth, G.F. ; Bill, C.
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ItemA review of rotorcraft wake modeling methods for flight dynamics applications( 2009) Hoydonck, W.R.M. Van ; Haverdings, H. ; Pavel, M.D.
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ItemA simple analytical fuselage-induced velocity model for comprehensive rotor codes( 2015) Wall, B.G. van der ; Wentrup, M. ; Rajagopalan, G. ; Jung, S.N.A simple analytical model to account for fuselage-induced velocities at rotor blade elements and at rotor wake nodes is described. The method is applied to three different fuselage configurations. Results obtained with a comprehensive rotor code show the fuselage effect on rotor trim controls, comparing the isolated rotor with inclusion of the fuselage for the same trim. This is compared to a simple analytical estimate of the fuselage effect using blade element/momentum theory. It is found that in forward flight the lateral control is mainly affected by fuselage effects. Rotor thrust can be varied by the presence of the fuselage, depending on its angle of attack, and the fuselage influence generally increases with flight speed.
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ItemA simple CFD/CSD loose coupling approach for rotor blade aeroelasticity( 2007) Tanabe, Y. ; Saito, S.
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ItemA small-scale tiltrotor model operating in descending flight( 2002) Abrego, A.I. ; Betzina, M.D. ; Long, K.R.
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ItemA time-dependent-coefficient reduced-order model for unsteady aerodynamics of proprotors( 2003) Gennaretti, M. ; Greco, L.
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ItemA two-grid overset method for the prediction of isolated rotor hover performance( 2008) Moulton, M.A. ; Bhagwat, M.J. ; Caradonna, F.X.
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ItemActive rotor performance investigations using CFD/CSD weak coupling( 2007) Dietz, M. ; Krämer, E. ; Wagner, S. ; Altmikus, A.
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ItemActuator design for the active trailing edge of a helicopter rotor blade( 2007) Maucher, C.K. ; Grohmann, B.A. ; Jänker, P. ; Altmikus, A. ; Jensen, F. ; Baler, H.
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ItemActuator disc modelling for helicopter rotors( 2002) Chuiton, F. Le
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ItemAdvanced rotorcraft aeromechanics studies in the french-german shanel project( 2009) Costes, M. ; Raddatz, J. ; Borie, S. ; Sudre, L. ; D´Alascio, A. ; Embacher, M. ; Spiegel, P.
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ItemAdvances in cfd & actuator disk models for helicopter aerodynamics( 2009) Filippone, A. ; Mikkelsen, R.
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ItemAeroacoustic simulation of a complete H145 helicopter in descent flight( 2015) Kowarsch, U. ; Ohrle, C. ; Keßler, M. ; Krämer, E.In the past years, the aeroacoustic noise emission of a helicopter became one of the most important, but also challenging issues in helicopter development. The blade vortex interaction phenomenon is one of the dominant phenomena characterizing the helicopter's aeroacoustic footprint, which is insufficiently predicted by low fidelity computational methods. For a high fidelity noise prediction of a helicopter configuration, a multidisciplinary CFDCSD- CAA tool chain has been established at the Institute of Aerodynamics and Gas Dynamics of the University of Stuttgart. With higher order CFD computed noise generation at the near field and the noise convection using a Ffowcs-Williams Hawkings based CAA code, very good agreement to measured aeroacoustic noise in wind tunnel as well as free flight experiments of helicopters is achieved. However, the simulations had been limited to the main rotor's geometry up to now, where some residual deviations to the experiment still exist. In this paper, we present a high fidelity aeroacoustic simulation of a complete helicopter configuration and the benefit compared to an isolated rotor simulation in predicting its aeroacoustic noise emission. Shading and reflection effects are clearly resolved, influencing the behaviour of the helicopter's noise radiation. The simulated aeroacoustic noise emission of the helicopter lies within the experimental variation and shows therefore highly promising results for the next generation of aeroacoustic noise prediction.
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ItemAeroacoustic validation of the free wake method first on the basis of a H145 main rotor in descent flight( 2016) Kranzinger, P.P. ; Kessler, M. ; Krämer, E.
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ItemAerodynamic analysis of helicopter side intake variants by full scale wind tunnel measurements( 2015) Knoth, F. ; You, J.H. ; Breitsamter, C.The work presented in this paper aims at the aerodynamic optimization of engine side air intakes of a lightweight helicopter. For this purpose wind tunnel (W/T) tests are conducted on a novel full scale model of a helicopter fuselage section at the Institute of Aerodynamics and Fluid Mechanics of the Technische Universität München (TUM-AER). The new wind tunnel model includes a duct system, venturi meter and a radial fan to provide engine mass flow rates corresponding to realistic helicopter operation conditions. With 5-hole pressure probes significant trends on the total pressure drop and distortion coefficients are found at the Aerodynamic Interface Plane (AIP) for three different air intakes tested in hover and forward flight conditions. Further investigations are conducted concerning local surface pressure distributions.
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ItemAerodynamic and structural investigation of an active back-flow flap for dynamic stall control( 2013) Opitz, S. ; Gardner, A.D. ; Kaufmann, K.