UFR 2-11 Test Case: Difference between revisions
Jump to navigation
Jump to search
| Line 21: | Line 21: | ||
{|align="center" border=" | {|align="center" border="0" | ||
|[[Image:UFR2-11_figure2a.jpg|172px]]|[[Image:UFR2-11_figure2b.gif|593px]] | |[[Image:UFR2-11_figure2a.jpg|172px]]|[[Image:UFR2-11_figure2b.gif|593px]] | ||
|- | |- | ||
!align="center" colspan="2"|Figure 2: NACA0021 airfoil in wind tunnel (left) and a plan view of wind tunnel (right) [] | !align="center" colspan="2"|Figure 2: NACA0021 airfoil in wind tunnel (left) and a plan view of wind tunnel (right) [ ] | ||
|} | |} | ||
Revision as of 13:05, 6 September 2011
High Reynolds Number Flow around Airfoil in Deep Stall
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.
 |
| |
| Figure 2: NACA0021 airfoil in wind tunnel (left) and a plan view of wind tunnel (right) [ ] | |
|---|---|
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
© copyright ERCOFTAC 2024