5 First analysis results

Let's have a look at the results and check they are of the order expected. One thing that can be done is to compare the polar obtain by this results to the polar curve obtained in turotial-1 and in tutorial-2, as it always represent the same aircraft, bu modeled with different techniques.
 

1. Click the "Charts" tab.
2. Set the chart tool to plot the CL versus CD
3. Click "Add a curve" and set a first curve to plot the results from the tutorial-1, which was done in a 'Draft' project.
4. Click "Add a curve" and set another curve to plot the results from the tutorial-2, which was done in a 'VLM' project.
5. Set a third curve to plot results from the analysis set before, in NS_3D
6. Click "Generate graph"

 
You should obtain the following plots:
 
 

We note that past the maximum L/D point, the Lift on the NS_3D project is significantly lower than for the other models. There might be a problem.
 

Let's check what is happening on the 12° angle of attack.

1. Click the "Projects" tab.
2. In the Reference analysis, find the run having an angle of attack of 12°
3. On the image selection combobox, select "Solution-WSS-TQ3.jpg" near the bottom of the list.

You should get the following image. Red zones indicate a high air velocity attached to the surface. Blue areas corresponds either to low velocities (stagnation points) or to a flow separation away from the surfaces (stall). Here we can see a large separation appearing on the wing root.
 

 

Draft and VLM cannot predict this kind of separation. Here this is a design flaw: the shapes at the wing-fuselage junction are creating a very early stall on the root.