2. DD D : Diameter Z : Number of Blade Left Prop: Anti Clockwise turns
Right Prop: Clockwise Turns
Helix:
Pitch:
Sides:
Back/Suction/Low Pressure
Face/Pressure/ High Pressure

3. Skew: Joining the midpoints between leading and trailing edges at different radii.
Clearance
<90 Degrees
0 Degrees
0-30 Degrees

4. Example
SSkew: Joining the midpoints between leading and trailing edges at different radii.

5. Propeller Geometry
SCylindrical Coordinate System: (r, , z) is used.
Axial Velocity: VA
Tangential Velocity: 2nr (r)
Pitch Angle:
x=rcos, y=rsin, z=z
𝜙   =tan −1 𝑃 2𝜋𝑡

7. Example

8. Example

11. Blade Area

12. Blade Shape
The blade shape can be varied to even out the cavitation along radius and in the case of a nozzle propeller, it is advantageous to have wide-chord length at the tip (Kaplan shape).

13. Propeller Blade Sections
National Advisory Committee for Aeronautics (NACA). Old name of today’s NASA (The National Aeronautics and Space Administration)
Airfoil geometry can be characterized by the coordinates of the upper and lower surface. It is often summarized by a few parameters such as: maximum thickness, maximum camber, position of max thickness, position of max camber, and nose radius.
One can generate a reasonable airfoil section given these parameters. This was done by Eastman Jacobs in the early 1930's to create a family of airfoils known as the NACA Sections.
Public Domain Aeronautical Software -
Propeller Blade Sections

14. The NACA 4 digit and 5 digit airfoils were created by superimposing a simple meanline shape with a thickness distribution that was obtained by fitting a couple of popular airfoils of the time:
+- y = (t/0.2) * (.2969*x *x *x *x *x4)
The camberline of 4-digit sections was defined as a parabola from the leading edge to the position of maximum camber, then another parabola back to the trailing edge.
NACA 4-Digit Series: NACA 4412
max camber position max thickness
in % chord of max camber in % of chord
in 1/10 of c

15. After the 4-digit sections came the 5-digit sections such as the famous NACA These sections had the same thickness distribution, but used a camberline with more curvature near the nose. A cubic was faired into a straight line for the 5-digit sections.
The 6-series of NACA airfoils departed from this simply-defined family. These sections were generated from a more or less prescribed pressure distribution and were meant to achieve some laminar flow.
After the six-series sections, airfoil design became much more specialized for the particular application. Airfoils with good transonic performance, good maximum lift capability, very thick sections, very low drag sections are now designed for each use.
Often a wing design begins with the definition of several airfoil sections and then the entire geometry is modified based on its 3-dimensional characteristics.

17. Profile Sections
NACA16
NACAa0.8 i
X/C
T/C
F/C 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18
NACA16 AND NACA66 Thickness and NACA a0.8 Meanline distributions are commonly used in commercial design propellers

22. Profile max. thickness distribution
Then, the following geometrical parameters of the profile are to be determined;
Profile chord distribution
Mean line or camber distribution
Profile max. thickness distribution
Pitch ratio distribution
Pitch angle distribution