SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Reynolds number: 100,000 Max Cl/Cd: 33.99 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1012r8-il-100000.txt Download as CSV file: xf-sc1012r8-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1012R8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2900 0.10059 0.09591 -0.0161 1.0000 0.1065
-8.750 -0.3100 0.09731 0.09268 -0.0205 1.0000 0.1098
-8.500 -0.3463 0.09352 0.08896 -0.0276 1.0000 0.1106
-8.250 -0.3063 0.08877 0.08426 -0.0217 1.0000 0.1129
-8.000 -0.2913 0.08569 0.08121 -0.0202 1.0000 0.1157
-7.750 -0.4427 0.08821 0.08340 -0.0285 1.0000 0.1114
-7.500 -0.4087 0.08504 0.08038 -0.0222 1.0000 0.1136
-7.250 -0.3978 0.08230 0.07769 -0.0210 1.0000 0.1164
-7.000 -0.3979 0.07897 0.07440 -0.0226 1.0000 0.1199
-6.750 -0.4387 0.07711 0.07222 -0.0282 1.0000 0.1258
-6.500 -0.4348 0.07211 0.06736 -0.0268 1.0000 0.1275
-6.250 -0.4224 0.06907 0.06449 -0.0240 1.0000 0.1295
-6.000 -0.4182 0.06685 0.06234 -0.0216 1.0000 0.1325
-5.750 -0.4200 0.06467 0.06014 -0.0200 1.0000 0.1372
-5.500 -0.4328 0.06207 0.05723 -0.0199 1.0000 0.1448
-5.250 -0.4246 0.05924 0.05456 -0.0174 1.0000 0.1473
-5.000 -0.4183 0.05719 0.05256 -0.0153 1.0000 0.1520
-4.750 -0.4171 0.05484 0.04995 -0.0150 1.0000 0.1638
-4.500 -0.4076 0.05256 0.04782 -0.0128 1.0000 0.1687
-4.250 -0.4007 0.05046 0.04555 -0.0122 1.0000 0.1833
-4.000 -0.3897 0.04854 0.04372 -0.0105 1.0000 0.1915
-3.750 -0.3796 0.04636 0.04151 -0.0096 1.0000 0.2066
-3.500 -0.3477 0.04390 0.03902 -0.0122 0.9949 0.2303
-3.250 -0.2707 0.03582 0.02876 -0.0195 0.9878 0.1120
-3.000 -0.2199 0.03158 0.02406 -0.0230 0.9808 0.0929
-2.750 -0.1682 0.02918 0.02127 -0.0271 0.9729 0.0916
-2.500 -0.1189 0.02711 0.01884 -0.0304 0.9632 0.0903
-2.250 -0.0705 0.02542 0.01690 -0.0335 0.9527 0.0906
-2.000 -0.0215 0.02419 0.01551 -0.0367 0.9413 0.0951
-1.750 0.0294 0.02266 0.01400 -0.0402 0.9310 0.1003
-1.500 0.0831 0.02143 0.01281 -0.0439 0.9207 0.1093
-1.250 0.1242 0.02012 0.01172 -0.0452 0.9048 0.1223
-1.000 0.1602 0.01884 0.01060 -0.0450 0.8864 0.1443
-0.750 0.1868 0.01731 0.00949 -0.0433 0.8650 0.2100
-0.500 0.2942 0.01486 0.00940 -0.0503 0.8458 1.0000
-0.250 0.3124 0.01455 0.00890 -0.0474 0.8148 1.0000
0.000 0.3308 0.01429 0.00845 -0.0446 0.7808 1.0000
0.250 0.3496 0.01409 0.00802 -0.0420 0.7429 1.0000
0.500 0.3691 0.01398 0.00763 -0.0395 0.7009 1.0000
0.750 0.3890 0.01399 0.00733 -0.0373 0.6537 1.0000
1.000 0.4093 0.01413 0.00710 -0.0353 0.6060 1.0000
1.250 0.4299 0.01438 0.00700 -0.0335 0.5596 1.0000
1.500 0.4505 0.01472 0.00698 -0.0319 0.5175 1.0000
1.750 0.4713 0.01512 0.00704 -0.0304 0.4797 1.0000
2.000 0.4922 0.01555 0.00716 -0.0290 0.4451 1.0000
2.250 0.5131 0.01604 0.00733 -0.0276 0.4134 1.0000
2.500 0.5341 0.01655 0.00756 -0.0263 0.3837 1.0000
2.750 0.5556 0.01711 0.00785 -0.0251 0.3567 1.0000
3.000 0.5776 0.01766 0.00819 -0.0240 0.3326 1.0000
3.250 0.6002 0.01824 0.00855 -0.0230 0.3123 1.0000
3.500 0.6235 0.01883 0.00896 -0.0221 0.2949 1.0000
3.750 0.6473 0.01943 0.00941 -0.0214 0.2799 1.0000
4.000 0.6715 0.02008 0.00987 -0.0207 0.2676 1.0000
4.250 0.6961 0.02066 0.01034 -0.0201 0.2563 1.0000
4.500 0.7210 0.02134 0.01097 -0.0195 0.2462 1.0000
4.750 0.7461 0.02200 0.01144 -0.0191 0.2376 1.0000
5.000 0.7710 0.02272 0.01221 -0.0186 0.2292 1.0000
5.250 0.7965 0.02343 0.01278 -0.0182 0.2224 1.0000
5.500 0.8219 0.02437 0.01368 -0.0178 0.2166 1.0000
5.750 0.8467 0.02515 0.01453 -0.0173 0.2104 1.0000
6.000 0.8724 0.02596 0.01519 -0.0171 0.2052 1.0000
6.250 0.8971 0.02705 0.01633 -0.0167 0.2005 1.0000
6.500 0.9209 0.02802 0.01745 -0.0161 0.1959 1.0000
6.750 0.9454 0.02901 0.01846 -0.0157 0.1921 1.0000
7.000 0.9708 0.03012 0.01949 -0.0156 0.1888 1.0000
7.250 0.9937 0.03162 0.02108 -0.0151 0.1858 1.0000
7.500 1.0141 0.03296 0.02270 -0.0143 0.1825 1.0000
7.750 1.0352 0.03429 0.02419 -0.0136 0.1793 1.0000
8.000 1.0573 0.03556 0.02555 -0.0131 0.1765 1.0000
8.250 1.0793 0.03696 0.02700 -0.0127 0.1743 1.0000
8.500 1.1012 0.03877 0.02880 -0.0124 0.1724 1.0000
8.750 1.1167 0.04117 0.03145 -0.0115 0.1709 1.0000
9.000 1.1263 0.04362 0.03431 -0.0100 0.1695 1.0000
9.250 1.1321 0.04647 0.03755 -0.0085 0.1681 1.0000
9.500 1.1333 0.04972 0.04117 -0.0068 0.1667 1.0000
9.750 1.1279 0.05348 0.04528 -0.0050 0.1656 1.0000
10.000 1.1101 0.05825 0.05041 -0.0030 0.1652 1.0000
10.250 1.0588 0.06543 0.05799 -0.0006 0.1660 1.0000
10.500 0.9486 0.08218 0.07512 -0.0061 0.1698 1.0000
10.750 0.9286 0.09104 0.08406 -0.0098 0.1721 1.0000
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Polar data table (+)
Polar graphs
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