UFR 2-11 Test Case: Difference between revisions

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*Time-averaged sectional drag and lift coefficients, <math>\left.C_d,\ C_l\right.</math> integrated from pressure at individual spanwise locations near the spanwise mid-point: <math>{C_d=\frac{d}{\frac{1}{2}\rho U_\infty^2 c},\ C_l=\frac{l}{\frac{1}{2}\rho U_\infty^2 c}}</math>, where <math>d</math> and <math>l</math> are the sectional pressure drag and lift forces, respectively.
*Time-averaged sectional drag and lift coefficients, <math>\left.C_d,\ C_l\right.</math> integrated from pressure at individual spanwise locations near the spanwise mid-point: <math>{C_d=\frac{d}{\frac{1}{2}\rho U_\infty^2 c},\ C_l=\frac{l}{\frac{1}{2}\rho U_\infty^2 c}}</math>, where <math>\left.d\right.</math> and <math>\left.l\right.</math> are the sectional pressure drag and lift forces, respectively.
 
 
*Time histories of the sectional lift and drag coefficients (32,000 points total over the time interval ''T''&asymp;9000 (''c/U<sub>0</sub>'')).


== Test Case Experiments ==
== Test Case Experiments ==

Revision as of 13:44, 6 September 2011

High Reynolds Number Flow around Airfoil in Deep Stall

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Description

Test Case Studies

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Best Practice Advice

References

Flows Around Bodies

Underlying Flow Regime 2-11

Test Case Study

Brief Description of the Test Case

The following presents a precise description of the primary test case, the NACA0021 airfoil at 60° angle of attack.


A visual impression of the geometry and flow has been shown in Figure 1. The experiments were carried out in the wind tunnel of Monash University (see Figure 2). The width of the experimental section is 7.2 airfoil chord lengths, c, and its height is 16c.


UFR2-11 figure2a.jpg|UFR2-11 figure2b.gif
Figure 2: NACA0021 airfoil in wind tunnel (left) and a plan view of wind tunnel (right) [ ]


The airfoil geometry normalized with the chord length, c, is defined by:



Experimental flow parameters, needed to set up appropriate numerical simulations, are presented in Table 2.


Table 2: Flow parameters
Parameter Notation Value
Reynolds number 2.7×105
Chord length 0.125 m
Angle of attack 60°
Free stream Mach number 0.1
Free stream streamwise turbulence intensity 0.6%


The flow parameters measured in the experiments are as follows:

  • Time-averaged pressure coefficient distribution over the airfoil surface, , where is the reference pressure from the undisturbed far-field flow and is the fluid density.


  • Time-averaged sectional drag and lift coefficients, integrated from pressure at individual spanwise locations near the spanwise mid-point: , where and are the sectional pressure drag and lift forces, respectively.


  • Time histories of the sectional lift and drag coefficients (32,000 points total over the time interval T≈9000 (c/U0)).

Test Case Experiments

CFD Methods




Contributed by: Charles Mockett; Misha Strelets — CFD Software GmbH and Technische Universitaet Berlin; New Technologies and Services LLC (NTS) and Saint-Petersburg State University

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Description

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Best Practice Advice

References


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