S8064 (s8064-il)
S8064 - Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF.
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(s8064-il) S8064 Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord. Max camber 1.1% at 56.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S8064
1.000000 0.000000
0.997927 0.000125
0.991844 0.000661
0.981950 0.001759
0.968438 0.003565
0.951588 0.006193
0.931716 0.009686
0.909164 0.014035
0.884293 0.019168
0.857469 0.024954
0.829053 0.031198
0.799390 0.037630
0.768826 0.043760
0.737098 0.049161
0.703928 0.053909
0.669588 0.058180
0.634301 0.061961
0.598271 0.065229
0.561701 0.067947
0.524799 0.070079
0.487769 0.071601
0.450799 0.072500
0.414069 0.072755
0.377770 0.072374
0.342087 0.071387
0.307218 0.069831
0.273369 0.067736
0.240738 0.065134
0.209521 0.062054
0.179900 0.058531
0.152050 0.054600
0.126136 0.050302
0.102312 0.045678
0.080718 0.040772
0.061481 0.035636
0.044723 0.030322
0.030576 0.024873
0.019091 0.019310
0.010271 0.013670
0.004145 0.008047
0.000637 0.002692
0.000328 -0.001911
0.003568 -0.006325
0.009851 -0.011082
0.018933 -0.015812
0.030792 -0.020402
0.045404 -0.024768
0.062686 -0.028860
0.082555 -0.032657
0.104908 -0.036143
0.129620 -0.039299
0.156536 -0.042118
0.185485 -0.044585
0.216282 -0.046683
0.248732 -0.048388
0.282633 -0.049680
0.317775 -0.050530
0.353959 -0.050905
0.390991 -0.050795
0.428663 -0.050184
0.466779 -0.049071
0.505162 -0.047491
0.543597 -0.045496
0.581815 -0.043133
0.619551 -0.040409
0.656518 -0.037280
0.692670 -0.033539
0.728117 -0.029328
0.762681 -0.025064
0.796024 -0.020943
0.827817 -0.017097
0.857738 -0.013617
0.885475 -0.010558
0.910730 -0.007944
0.933228 -0.005769
0.952715 -0.003991
0.969006 -0.002502
0.982067 -0.001257
0.991810 -0.000404
0.997911 -0.000042
1.000000 0.000000
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Polars for S8064 (s8064-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8064-il | 50,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 50,000 | 5 | 29.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 100,000 | 9 | 48.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 200,000 | 9 | 68.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 200,000 | 5 | 55.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 500,000 | 9 | 80.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 500,000 | 5 | 65.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8064-il | 1,000,000 | 9 | 90 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8064-il | 1,000,000 | 5 | 70.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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