I found this full size test with a complete wing with an aspect ratio of 6
https://ntrs.nasa.gov/api/citations/199 ... 091723.pdf
The NACA at 0012 look like this :
- Full Size Windtunnel tests.png (651.54 KiB) Viewed 1489 times
Converting and solving variables from the reference :
NACA 0012
87 feet ps = 26.5 M/S
Re 3.3x10^6
q = (1.2 kg/m^3) / 2 * (26.5 m/s)^2
= (1.2 / 2) * (26.5^2)
= 0.6 * 702.25
= 421.35 N/m^2
Reference area
6 foot x 36 foot = 182.88 cm x 1097.28cm = 200619.36 or just over 20m square.
Results are good, the Cl of 0.76 at 10 degrees angle ( green line above ) agrees well with the real windtunnel results, and so does the Cd
13:07:33 forces ReportingFunction write:
Sum of forces
Total : (552.2152 0.88156894 6165.8845)
Pressure : (485.04306 0.87345659 6172.4242)
Viscous : (67.172144 0.0081123454 -6.5396431)
Sum of moments
Total : (33820.04 -3027.8889 -3027.621)
Pressure : (33855.953 -3027.2752 -2658.9246)
Viscous : (-35.912867 -0.61368162 -368.69647)
writing force and moment files.
13:08:08
13:08:08 forceCoeffs ReportingFunction001 write:
Coefficient Total Pressure Viscous Internal
Cd: 0.068073866 0.0082805897 0.059793276 0
Cd(f): 2.3502242 2.3227871 0.027437122 0
Cd(r): -2.2821503 -2.3145065 0.032356154 0
Cl: 0.76009424 -0.00080616902 0.76090041 0
Cl(f): 0.1726802 -0.20772798 0.38040818 0
Cl(r): 0.58741404 0.20692181 0.38049224 0
CmPitch: -0.20736692 -0.20732489 -4.2028382e-05 0
CmRoll: 2.3161873 2.3186468 -0.0024595158 0
CmYaw: -0.20734858 -0.18209816 -0.025250416 0
Cs: 0.00010867467 1.0000426e-06 0.00010767463 0
Cs(f): -0.20729424 -0.18209766 -0.025196578 0
Cs(r): 0.20740292 0.18209866 0.025304253 0