Menu
Panel Method
NACA 0012
@
0.0
°
C
L
=
0.000
• C
M
=
0.000
• C
D
=
0.000
🔄
Kutta Condition
OFF
Add circulation for lift generation
Flow
Geometry
Panel Method
Visualization
Fields
Flow Conditions
Angle of Attack (α)
°
Airfoil Geometry
Max Camber:
0%
Camber Position:
0
Thickness:
12%
Closed Trailing Edge
Zero thickness at TE (coefficient: -0.1036 vs -0.1015)
Panel Method Settings
Panel Count:
100
Higher count = smoother geometry
Computation Quality:
5
Higher = more accurate, slower
Performance Mode
Faster rendering, lower quality
Flow Visualization
Streamlines
Show Streamlines
Adaptive Density
Density:
12
Line Thickness:
2.0
Streamline line thickness
Color Scheme
Neon (Red/Green)
Classic (Blue/Red)
Pastel (Cyan/Pink)
Dividing Streamline Precision:
15
Binary search iterations for finding dividing streamline
Stagnation Tolerance:
1.000%
Minimum distance to foil to detect stagnation (% of chord)
➕ Add Custom Streamline
Clear Custom
Visual Style
Green Screen Mode (Neon Colors)
Particles (Smoke)
Show Smoke Particles
Blob Size:
5.0
Size of individual smoke particles
Pressure
Show C
p
Vectors
Vector Scale:
0.10
Smoke Simulation
Simulation Speed:
1.0
x
Control smoke movement speed (0.1x - 3.0x)
Debug Display
Stagnation Points
Panel Normals
Panel Points
Panel Numbers
Visualization
C
p
Distribution
Basics Debugging
Inviscid Flow • Panel Method • WebGL Rendering
Pressure Coefficient Distribution
Upper Surface
Lower Surface
Elements
Source Panels
+ Add Source Panel
+ Add Symmetric Ring
🔍 Test ψ at (0,0)
Vortex Panels
+ Add Vortex Panel
Inspection
+ Add Inspection Point
🔍 Toggle Inspection Wand
Grid & Contours
X:
to
Y:
to
N
x
:
N
y
:
Create Grid
Clear Grid
Show grid
Stream function (ψ)
Velocity potential (φ)
Velocity magnitude
Levels:
Clear All
Results
NACA 0012
0.0
0.000
0.000
0.000