0808
OTHER:
Aerodynamics - Blade Profile - NACA 23012
Drawing:
Notes:
NACA 230xx series airfoil is asymmetrical.
NACA 23017 was used on the Flettner-282 intermeshing helicopter. On this helicopter it has 4 degrees twist.
KM230XX 11.47% (@ tip) and NACA 230 14.86% (@ root) is used on the Kaman Seasprite. On this helicopter it has 10 degree of linear twist.
NACA 230?? was probably used on the used on the K-Max.
Aerodynamics:
Alpha @ zero lift
[AlphaL0] came from NVFoil calculation.|
Airfoil |
|
23012 |
23017 |
|
Alpha @ zero lift [AlphaL0] |
|
-1.5 |
-1.5 approx. |
|
Thickness |
|
0.1201 |
|
|
Leading edge radius |
|
0.0171 |
|
|
Camber |
|
0.0146 |
|
|
Trailing edge angle[deg] |
|
15.7567 |
|
The NACA 23012 airfoil's coefficient of lift appears to be roughly 8.5% greater than the NACA 0012
The NACA 23012 airfoil's coefficient of drag is very close to the NACA 0012's
The NACA 23017 airfoil's coefficient of lift appears to be roughly 10.5% greater than the NACA 0012
The NACA 23017 airfoil's coefficient of drag is very close to the NACA 0012's
What's with using 23017? Why not the 23018. And also it should be compared to the 0018.
For simplicity and expedience all database calculations using the NACA 230XX airfoil will be the NACA 0012 algorithms, with Cl adjusted as per the above.
|
Airfoil: |
Alpha |
Cl |
Cd |
cl3/2/cd |
Cm |
Ctr of Lift: |
|
0012 |
2 |
0.239 |
0 |
-0.002 |
26 |
|
|
0012 |
4 |
0.47 |
0 |
-0.005 |
26.5 |
|
|
0012 |
6 |
0.715 |
0 |
-0.007 |
26.5 |
|
|
0012 |
8 |
0.952 |
0.001 |
-0.009 |
26.5 |
|
|
0012 |
10 |
1.187 |
0.001 |
-0.012 |
26.5 |
|
|
0012 |
12 |
1.422 |
0.002 |
-0.014 |
26.5 |
|
|
0012 |
1 |
0.119 |
0 |
-0.001 |
26 |
|
|
0012 |
0 |
0 |
0 |
0 |
26 |
|
|
23012 |
0 |
0.133 |
0.001 |
-0.012 |
34 |
|
|
23012 |
1 |
0.253 |
0.001 |
-0.013 |
30.5 |
|
|
23012 |
2 |
0.372 |
0 |
-0.015 |
29 |
|
|
23012 |
4 |
0.611 |
0 |
-0.017 |
28 |
|
|
23012 |
12 |
1.557 |
0.001 |
-0.03 |
27.5 |
|
|
23012 |
6 |
0.85 |
0 |
-0.02 |
27.5 |
|
|
23012 |
8 |
1.087 |
0 |
-0.023 |
27.5 |
|
|
23012 |
10 |
1.323 |
0 |
-0.027 |
27.5 |
|
|
23017 |
12 |
1.607 |
0.001 |
-0.037 |
27.5 |
|
|
23017 |
10 |
1.366 |
0.001 |
-0.032 |
27.5 |
|
|
23017 |
0 |
0.139 |
0.001 |
-0.011 |
33 |
|
|
23017 |
6 |
0.878 |
0.001 |
-0.024 |
27.5 |
|
|
23017 |
4 |
0.632 |
0.001 |
-0.019 |
28 |
|
|
23017 |
2 |
0.386 |
0.001 |
-0.015 |
29 |
|
|
23017 |
1 |
0.263 |
0.001 |
-0.013 |
30 |
|
|
23017 |
8 |
1.122 |
0.001 |
-0.028 |
27.5 |
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Last Revised: Sunday, February 11, 2009