Inventor 刘强 刘欣煜 陈广强 Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Active Application number CN201320833592.6U Other languages Chinese ( zh)
#HIGH LIFT AIRFOIL PDF#
Google Patents Airfoil with high lift force and high lift-drag ratioĭownload PDF Info Publication number CN203681864U CN203681864U CN201320833592.6U CN201320833592U CN203681864U CN 203681864 U CN203681864 U CN 203681864U CN 201320833592 U CN201320833592 U CN 201320833592U CN 203681864 U CN203681864 U CN 203681864U Authority CN China Prior art keywords airfoil base profile lift high lift maximum Prior art date Legal status (The legal status is an assumption and is not a legal conclusion. Google Patents CN203681864U - Airfoil with high lift force and high lift-drag ratio I encourage people to contribute their validation solutions to this repository by creating new folders and including their own READMEs and solution files.CN203681864U - Airfoil with high lift force and high lift-drag ratio The 30P-30N airfoil is challenging to mesh and simulate because of its unique geometry and the airflows around those geometries. The reference pressure (rho/2*V^2) of std air at 90m/s is 4961 pa. The air velocity for Re = 5,000,000 flowing past a 1m airfoil is 90m/sec. If one simulates a normalized 30P-30N airfoil, one will need to multiply the forces and coefficients by ~1.2 to get the values used in industry. All 30P-30N lift and drag figures are with respect to the nominal chord, not the actual chord. Note: The 30P-30N wing has a nominal chord of 1.0 when the slat and flap are retracted but an actual chord of ~1.2 when extended. I included normalized dat files because some airfoil tools expect airfoils to have a chord greater than 0 and less than 1.0. The wing and wind tunnel models are not normalized. The non normalized dat files have a chord of ~1.2 with the slat starting prior to x=0 and the flap going beyond x=1. The normalized dat files have an overall chord of 1.0. The other files are stl, iges and brep representations of the wind tunnel solid and the wing solid and wing profile files to recreate a 30P-30N airfoil. The first file is a FreeCAD model of a 1m(nominal) 30P-30N wing and windtunnel along with a 2D CfdOF analysis object. I am starting the repository out with the following files so that others may use them to validate various meshing and simulation tools they may be using.
#HIGH LIFT AIRFOIL DOWNLOAD#
Wolf Dynamics graciously provides a link to download the case file on their web page.
Numerical study to assess sulfur hexafluoride as a medium for testing multi-element airfoils.
2002.Ĭomparative results from a CFD challenge over a 2D three-element high-lift airfoil. Progress in Aerospace Sciences, 38:145-180. Prediction of high lift: review of present CFD capability. They obtained a Cd of 2.237588 and a CL of 0.034598 versus the experimental values of 2.167089 and 0.033243 respectively.
In their validation case WD meshed and simulated a 30P-30N airfoil at a 0 degree AoA at a Reynolds number of 5,000,000 using the Spalart-Allmaras turbulence model. The impetus for this activity came from Wolf Dynamics 30P-30N validation case available here: This repository contains various resources necessary/helpful to validate the meshing and CFD simulation of a 30P-30N airfoil.
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