BOEING-VERTOL VR-12 AIRFOIL (vr12-il)
BOEING-VERTOL VR-12 AIRFOIL - Boeing-Vertol/Dadone VR-12 rotorcraft airfoil
| Details | Dat file | Parser | |
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(vr12-il) BOEING-VERTOL VR-12 AIRFOIL Boeing-Vertol/Dadone VR-12 rotorcraft airfoil Max thickness 10.6% at 35% chord. Max camber 2.3% at 20% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING-VERTOL VR-12 AIRFOIL
43. 41.
0.00000 0.0000000
0.00012 0.0024033
0.00080 0.0062054
0.00195 0.0096880
0.00340 0.0127930
0.00520 0.0158200
0.00700 0.0183560
0.00900 0.0208130
0.01105 0.0230600
0.01415 0.0260980
0.01860 0.0299200
0.02450 0.0343400
0.03205 0.0392100
0.04160 0.0442500
0.05350 0.0497000
0.06850 0.0553000
0.08800 0.0606000
0.11400 0.0656000
0.15000 0.0700000
0.20000 0.0732000
0.25000 0.0746000
0.30000 0.0751000
0.35000 0.0748500
0.40000 0.0738000
0.45000 0.0717500
0.50000 0.0691000
0.55000 0.0653500
0.60000 0.0606660
0.65000 0.0547500
0.69000 0.0493227
0.73000 0.0433240
0.77000 0.0371040
0.81000 0.0307630
0.84500 0.0248215
0.88000 0.0187523
0.91000 0.0136160
0.93500 0.0093350
0.95500 0.0061715
0.97000 0.0042340
0.98000 0.0031240
0.99000 0.0021627
0.99500 0.0017315
1.00000 0.0015000
0.00000 0.0000000
0.00055 -.0025000
0.00200 -.0047000
0.00400 -.0067500
0.00620 -.0084000
0.00860 -.0098300
0.01100 -.0109500
0.01465 -.0123000
0.01955 -.0135000
0.02615 -.0148000
0.03430 -.0160500
0.04449 -.0174000
0.05690 -.0189000
0.07245 -.0205000
0.09240 -.0221000
0.11850 -.0238500
0.15000 -.0255500
0.20000 -.0276000
0.25000 -.0291000
0.30000 -.0301000
0.35000 -.0308000
0.40000 -.0311000
0.45000 -.0310000
0.50000 -.0306500
0.55000 -.0300000
0.60000 -.0290660
0.65000 -.0277750
0.69000 -.0264227
0.73000 -.0248240
0.77000 -.0229040
0.81000 -.0207130
0.84500 -.0185215
0.88000 -.0160523
0.91000 -.0133160
0.93500 -.0108350
0.95500 -.0087715
0.97000 -.0067840
0.98000 -.0052240
0.99000 -.0035627
0.99500 -.0025315
1.00000 -.0015000
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Polars for BOEING-VERTOL VR-12 AIRFOIL (vr12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr12-il | 50,000 | 9 | 28.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 50,000 | 5 | 28.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 100,000 | 9 | 39.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 100,000 | 5 | 39.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 200,000 | 9 | 49.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 200,000 | 5 | 53.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 500,000 | 9 | 73 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 500,000 | 5 | 75.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr12-il | 1,000,000 | 9 | 94.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr12-il | 1,000,000 | 5 | 93.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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