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  • Study of the Flow over an Oscillating NACA 0012 Airfoil
    This paper provides a study of the NACA0012 dynamic stall at Reynolds numbers 10 5 and 10 6 by means of two-and three-dimensional numerical simulations reported in this paper, have shown that the rig, and the associated measurement instrumentation, should be able to resolve the effect of flow control, if that effect is relatively large
  • 2D Numerical Study of Heat Transfer Enhancement Using Fish-Tail . . .
    A numerical simulation is performed to study the effect of two types vortex generators (VGs) on heat transfer coefficient and pressure drop in duct There are two types of V G , one is concave V G
  • An experimental investigation on the unsteady heat transfer process . . .
    In the present study, a NACA0012 airfoil wing model with a chord length C = 150 mm was used for the experimental study The airfoil wing model was 3D printed by using a rapid prototyping machine (i e , 3D printer) Heat transfer coefficient measurement on iced airfoil in small icing wind tunnel J Thermophys Heat Transf , 14 (2000), pp
  • Pressure-Sensitive Paint calibration system. - ResearchGate
    A dual wavelength laser system providing emissions of 1064 nm and 532 nm was developed for cleaning applications In this study, cleaning of surface layers of paints with the dual wavelength laser
  • Quantitative Measurement Method for Ice Roughness on an Aircraft . . . - MDPI
    When an aircraft passes through clouds containing supercooled water droplets, the leading edge’s surface will gradually accumulate ice Ice surface roughness is an important parameter affecting the local convective heat transfer coefficient and the water collection coefficient, which in turn affect the ice’s shape However, because the surface roughness of aircraft icing is a transient
  • simulation naca0012 airfoil | PDF | Vortices | Boundary Layer
    simulation naca0012 airfoil - Free download as PDF File ( pdf), Text File ( txt) or read online for free This document presents a direct numerical simulation (DNS) study of flow separation and transition around a NACA 0012 airfoil at a 4° attack angle and a Reynolds number of 105 The simulation captures key phenomena such as flow separation, vortex shedding, and turbulence transition
  • Direct Numerical Simulation of Flows over an NACA-0012 . . . - ResearchGate
    The pressure-side boundary layer and suction-side boundary layer create different wall friction stresses Direct numerical flow simulations (DNSs) of a NACA 0012 profile at an angle of attack of 5
  • (PDF) Experimental and computational ice shapes and . . . - ResearchGate
    measurement Ice shapes and In most works on the simulation of icing on a NACA0012 airfoil leading to significant improvements in heat transfer coefficients that match the experimental


















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