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Sunday, July 19, 2020 | History

3 edition of Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover found in the catalog.

Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover

Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover

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Published by National Aeronautics and Space Administration, Ames Research Center, National Technical Information Service, distributor in Moffett Field, Calif, [Springfield, Va .
Written in English

    Subjects:
  • Fluid dynamics.,
  • Rotors -- Dynamics.,
  • Airplanes -- Wings.

  • Edition Notes

    StatementIan G. Fejtek.
    SeriesNASA contractor report -- 4532., NASA contractor report -- NASA CR-4532.
    ContributionsAmes Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18060967M

    = air density, kg/m3 Introduction Rotor/wing aerodynamic interactions can have a dramatic effect on the hover performance of a tilt rotor aircraft or compound helicopter. For example, the download on the wing of a tilt rotor aircraft in hover can be as large as 15% of the total rotor thrust (Refs. 1 and 2).File Size: 1MB. about helicopter rotor in forward flight using Navier-Stokes equations with Baldwin-Lomax turbulence model. A model helicopter rotor was used for the computation, which was studied experimentally by caradonna [9] they tested a stiff, two-bladed untwisted rotor with constant chord and an NACA profile. The figure 1a shows.

    Averaged Navier-Stokes) o --,-a- p—+pu vu=— 71 A-1 (—)¥- u t) = A f (O) sin(wt) (3) synthetic jetgl "Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover," NASA TM [2] , Maisel, M. and Harris, D, "Hover tests of the X V NASA CONTRACTOR REPORT Calculation of Helicopter Rotor Blade/Vortex Interaction by Navier-Stokes Procedures Y. -N. Kim S. J. Shamroth R, C. Buggeln {N&SA^CBU41) CftLCOLATlOS OF HELICOPTER N ROTOR BLADE/VOBTEX INTERACTION Bt NAVIEB-STOKES PROCEDORES Final Report {Scientific Research Associates) 38 p .

    Smith, M.J., and Sankar, L.N. “ Evaluation of a Fourth-Order Compact Operator Scheme for Euler/Navier-Stokes Simulations of a Rotor in Hover.” AIAA Paper No. , January Snel, H., and van Holten, T. “ Review of Recent Aerodynamic Research on Wind Turbines with Relevance to Rotorcraft.”. The steady flows over the XV tilt rotor in hover are studied in this work using Reynolds-averaged Navier–Stokes methods with a three-equation k-ω-γ transition model. It is seen that the numerical results, including pressure coefficients and skin friction coefficients, are in good agreement with the available measurements. This model successfully captures the transition Cited by: 9.


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Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover Download PDF EPUB FB2

Navier-Stokes computation of wing/rotor interaction for a tilt rotor in hover. Navier-Stokes computation of wing leading edge tangential blowing for a tilt rotor in hover Vrishank Raghav; AIAA Scitech Forum January Euler/Navier-Stokes Computations of the Flowfield of a Helicopter Rotor in Hover and Forward Flight.

Applied Cited by: focuses specifically on the wing/rotor interaction of a tilt rotor aircraft in hover. The three-dimensional, unsteady, thin-layer compressible Navier-Stokes equations are solved using a time-accurate, implicit, finite difference scheme that employs LU-ADI factorization.

The rotor is modeled as an actuator disk which imparts both a radial. A rotor CFD solver is developed for simulating the aerodynamic interaction phenomenon among rotor, wing and fuselage of a tilt rotor aircraft in its helicopter mode. The unsteady Navier–Stokes equations are discretized in inertial frame and embedded grid system is adopted for describing the relative motion among blades and nacelle/wing/ by: Abstract A method has been developed to analyze the wing/rotor interaction of tilt rotor aircraft in hover.

The unsteady, thin-layer compressible Navier-Stokes equations are solved using an implicit, finite difference scheme that employs LU-ADI : Ian Fejtek and Leonard Roberts.

Hover predictions of tiltrotor aircraft are hampered by the lack of accurate and computationally efficient models for rotor/wing interactional aerodynamics. This paper summarizes the development of. A new model for rotor/wing aero-interaction in tilt-rotor aircraft is established by parametirc modeling method, which suits to flight dynamic analysis.

The flow over a wing-fuselage-nacelle configuration of the V tilt rotor aircraft in forward flight was simulated by Tai 5 with a multi-zone, thin-layer Navier–Stokes method, and major flow features including the three-dimensional flow separation due to viscous-vortex interactions observed experimentally were by: 6.

Flow Field and Performance Analysis of an Annular-Type Aerospike Nozzle with Base Bleeding. Navier-Stokes computation of wing/rotor interaction for a tilt rotor in hover. Navier-Stokes computation of wing leading edge tangential blowing for a tilt rotor in hover.

17 August Navier-Stokes computations of two- and three-dimensional. To numerically simulate aerodynamics of rotor-airframe interaction in a rigorous manner, we need to solve the Navier-Stokes system for a rotor-airframe combination in a single computational domain.

The rotor performance and flow field of characteristics of Harington rotor-2 in single and coaxial configurations are investigated in hover. In order to clarify the doubt about the blade thickness effect in Ref. [17], special one-rotor-stay cases are carried out to make a better understanding for the aerodynamic interaction mechanism of Cited by: 4.

Because of the complexities associated with modeling the complete configuration, this work focuses specifically on the wing/rotor interaction of a tilt rotor aircraft in hover. The three-dimensional, unsteady, thin-layer compressible Navier-Stokes equations are solved using a time-accurate, implicit, finite difference scheme that employs LU-ADI factorization.

Based on the grid method for a conventional rotor developed by the corresponding author of this paper, for a tilt-rotor in a conversion mode, the rigid blade flapping, pitching, rotational motion, and tilting and translational motions are described as follows (1) θ (t) = θ 0-θ 1 c cos ψ (t)-θ 1 s sin ψ (t) β (t) = A 0-A 1 cos ψ (t)-B 1 Cited by: 9.

In this paper, the rotor–wing aerodynamic interaction of a scaled V Osprey tiltrotor, both in the helicopter and transition modes, are studied by computational fluid dynamics (CFD) numerical simulation.

The flow field is discretized via the chimera mesh technique and then solved with the Reynolds-averaged Navier–Stokes (RANS) : Zhenlong Wu, Can Li, Yihua Cao. An image plane was used to simulate the two rotor-wing flow phenomena.

The study of reference (10) attempts to analytically study the flow of a tilt rotor XV in hover by numerically solving the unsteady, thin layer compressible Navier-Stokes Equation. Numerical simulations based on the solver ROSITA are performed to estimate the wing download due to the interaction with the rotor wake in hover condition.

Several wing configurations for different. A framework is developed for the computational fluid dynamics (CFD) analyses of a series of helicopter rotor flowfields in hover and in forward flight.

Fejtek, I., "Navier-Stokes Flowfield Computation of Wing/Rotor Interaction for a Tiltrotor Aircraft in Hover," NASA CRJuly Coffen, C., "Tilt Rotor Hover Aeroacoustics," NASA CRJune File Size: 2MB.

Using the Navier-Stokes equations, and together with free-wake method, NASA Ames research center established a rotor flowfield code known as TURNS, and the numerical results demonstrated the capabilities of this hybrid CFD methodology in calculating helicopter rotor aerodynamic flowfield in both hover and forward flight.

4 Nevertheless, since TURNS Cited by: A method has been developed to analyze the wing/rotor interaction of tilt rotor aircraft in hover.

The unsteady, thin-layer compressible Navier-Stokes equations are. Get this from a library. Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover. [Ian G Fejtek; Ames Research Center.]. rotor blades, thus avoiding significant blade/wake interaction.

Two examples are shown in Fig. 1 for a UHA rotor in hover and forward flight. The forward flight conditions described in this paper are summarized in Table 1.

† Senior Research Scientist, M/[email protected], Member AHS. a) Hover (C T/σ=), ∆S=5% c tip. We investigated the aerodynamic interference between the prop-rotor and the tail-wing, and its effect on the lateral stability of a tiltrotor UAV configuration during transient flight modes.

Unsteady flow calculations were conducted using an unstructured mesh flow solver, coupled with an overset mesh technique. It was shown that as the sideslip angle increases, Cited by: 3. This paper focuses on one of the most prominent flow features of the hovering rotor wake, the close interaction of the tip vortex with a following blade.

Such vortex interactions are fundamental determinants of rotor performance, loads, and noise. Yet, they are not completely understood, largely due to the lack of sufficiently comprehensive experimental Cited by: 5.