Dynamic stall computations using a zonal Navier-Stokes model
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Dynamic stall computations using a zonal Navier-Stokes model

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Published by Naval Postgraduate School in Monterey, California .
Written in English


  • Aeronautics

Book details:

About the Edition

A zonal Navier-Stokes model, is installed and verified on the NASA Ames Cray X/MP-48 computer and is used to calculate the flow field about a NACA 0012 airfoil oscillating in pitch. Surface pressure distributions and integrated lift, pitching moment, and drag coefficient versus angle of attack are compared to existing experimental data for four cases and existing computational data for one case. These cases involve deep dynamic stall and fully detached flow at and below a freestream Mach number of .184. The flow field about the oscillating airfoil is investigated through the study of pressure, vorticity, local velocity and stream function. Finally, the effects of pitch rate on dynamic stall are investigated. Keywords: Theses, Computer programs, Dynamic stall, Navier Stokes, Unsteady aerodynamics. (jhd)

Edition Notes

Other titlesDynamic stall calculations using a zonal Navier-Stokes model.
Statementby Jack H. Conroyd, Jr
ContributionsNaval Postgraduate School (U.S.)
The Physical Object
Paginationv, 205 p. ;
Number of Pages205
ID Numbers
Open LibraryOL25525814M

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Dynamic stall computations using a zonal Navier-Stokes model. Master's thesis. Technical Report Conroyd, J.H. A zonal Navier-Stokes model is installed and verified on the NASA Ames Cray X/MP computer and is used to calculate the flow field about a NACA airfoil oscillating in pitch. Surface-pressure distributions and integrated lift. 3D Navier–Stokes computations of a stall‐regulated wind turbine. A. Le Pape of Transitional Unsteady Boundary Layer on Wind Turbine Airfoil Using Hybrid RANS/LES Turbulence Model, Jason C. Howison and Kivanc Ekici Wind Turbine Dynamic Stall Analysis Using Harmonic Balance and Correlation-based.   The actuator surface technique is evaluated by computing the two-dimensional flow past a NACA airfoil at a Reynolds number of 10 6 and an angle of attack of 10 deg and by comparing the computed streamlines with the results from a traditional Reynolds-averaged Navier–Stokes computation. In the last part, the actuator surface technique is Cited by: DYNAMIC STALL COMPUTATIONS USING A ZONAL NAVIER-STOKES MODEL OfOSONA, AUTWOR(S) Conrovd, Jack H. r. __ _ I, Master,3 iOR s Thesis, T'M(co COVERED DATE Of REPORT (Yea, Month Oy) IS PAGE (OINT %, OM To June 6 The SLP;'LEENTARY views expressed NOTATION in this thesis are those of the author and do not reflect the rie.

  Computations of light dynamic stall of a NACA airfoil with the Johnson–King model were obtained by Dindar and Kaynak and Clarkson et al. The Reynolds number of the experiment was Re c =3×10 6, the reduced frequency k = and the oscillatory motion α(t)=10°+5° sin (ωt). Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; The Aerospace Press; Browse All Books; Meeting Papers; For Authors ; Aerospace Sciences Meetings Home; No Access. Navier-Stokes computation of airfoil in stall using algebraic Reynolds-stress model.   A new design of a Mach-scaled double-swept rotor configuration is investigated by means of unsteady Reynolds-averaged Navier-Stokes computations using the DLR-TAU Code. The investigated rotor frequency of Hz results in a Reynolds number of , and a Mach number of at \(75\%\) radius. Two highly resolved dynamic stall cases with a.   The dynamic stall has serious implications in terms of achievable performance, which needs to be predicted accurately as soon as possible in the airfoil design cycle. The account of this phenomenon is important for the design of many industrial domains, such as helicopter rotor blades (retreating blade) or jet engines (rotating stall).

  Lifting-line computations were performed for both axial and yawed operating conditions while the Navier-Stokes computations were performed for only the axial conditions. Various stall delay models and dynamic stall models were used by the CAMRAD II code. For axial operating conditions, the predicted rotor performance varied significantly. User Tools. Cart. Sign In. The objective of the work is to perform a challenging and accurate RANS/DNS computation of static stall on a fixed wing. The chosen configuration is the . Davidson, L., and Rizzi, A., “Navier-Stokes Computation of Airfoil in Stall Using Algebraic Reynolds-Stress Model”, AIAA Paper 92–, 30th Aerospace Sciences Meeting, Reno, NV, January 6–9, Google Scholar.