SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Reynolds number: 50,000 Max Cl/Cd: 23.59 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1012r8-il-50000.txt Download as CSV file: xf-sc1012r8-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3790 0.10711 0.10035 -0.0004 1.0000 0.2533
-8.000 -0.3736 0.10360 0.09692 -0.0005 1.0000 0.2627
-7.750 -0.3969 0.10284 0.09630 -0.0025 1.0000 0.2760
-7.500 -0.3633 0.09793 0.09140 0.0001 1.0000 0.2908
-7.250 -0.3538 0.09471 0.08826 0.0009 1.0000 0.3059
-7.000 -0.3480 0.09188 0.08552 0.0018 1.0000 0.3237
-6.750 -0.3418 0.08923 0.08296 0.0031 1.0000 0.3446
-6.500 -0.3487 0.08747 0.08132 0.0046 1.0000 0.3690
-6.250 -0.3236 0.08402 0.07793 0.0073 1.0000 0.3986
-6.000 -0.3108 0.08160 0.07559 0.0102 1.0000 0.4353
-5.750 -0.2931 0.07932 0.07339 0.0137 1.0000 0.4797
-5.500 -0.3040 0.07884 0.07306 0.0187 1.0000 0.5235
-5.250 -0.2378 0.07370 0.06788 0.0200 1.0000 0.5882
-5.000 -0.2084 0.07117 0.06541 0.0228 1.0000 0.6537
-4.750 -0.1570 0.06685 0.06111 0.0223 1.0000 0.7257
-3.500 -0.3364 0.04472 0.03726 -0.0136 1.0000 0.1945
-3.250 -0.3121 0.04168 0.03374 -0.0139 1.0000 0.1721
-3.000 -0.2870 0.03952 0.03095 -0.0137 1.0000 0.1581
-2.750 -0.2654 0.03751 0.02872 -0.0133 1.0000 0.1552
-2.500 -0.2427 0.03588 0.02682 -0.0130 1.0000 0.1539
-2.250 -0.2190 0.03445 0.02515 -0.0127 1.0000 0.1530
-2.000 -0.1946 0.03321 0.02366 -0.0124 1.0000 0.1519
-1.750 -0.1711 0.03223 0.02248 -0.0122 1.0000 0.1525
-1.500 -0.1489 0.03158 0.02167 -0.0119 1.0000 0.1564
-1.250 -0.1276 0.03124 0.02112 -0.0115 1.0000 0.1605
-1.000 -0.0817 0.03023 0.02023 -0.0153 0.9910 0.1689
-0.750 -0.0073 0.02936 0.01941 -0.0230 0.9694 0.1935
-0.500 0.0605 0.02789 0.01836 -0.0297 0.9455 0.2530
-0.250 0.1500 0.02494 0.01777 -0.0353 0.9236 1.0000
0.000 0.2491 0.02460 0.01702 -0.0464 0.8884 1.0000
0.250 0.3224 0.02371 0.01591 -0.0516 0.8504 1.0000
0.500 0.3666 0.02290 0.01491 -0.0515 0.8118 1.0000
0.750 0.3954 0.02231 0.01413 -0.0488 0.7724 1.0000
1.000 0.4172 0.02196 0.01357 -0.0455 0.7311 1.0000
1.250 0.4381 0.02174 0.01308 -0.0421 0.6897 1.0000
1.500 0.4588 0.02167 0.01270 -0.0389 0.6487 1.0000
1.750 0.4794 0.02179 0.01246 -0.0360 0.6083 1.0000
2.000 0.5003 0.02211 0.01240 -0.0334 0.5690 1.0000
2.250 0.5213 0.02260 0.01253 -0.0312 0.5310 1.0000
2.500 0.5425 0.02327 0.01287 -0.0293 0.4952 1.0000
2.750 0.5640 0.02406 0.01339 -0.0277 0.4625 1.0000
3.000 0.5871 0.02489 0.01384 -0.0263 0.4358 1.0000
3.250 0.6091 0.02586 0.01469 -0.0251 0.4102 1.0000
3.500 0.6320 0.02683 0.01549 -0.0240 0.3889 1.0000
3.750 0.6553 0.02789 0.01640 -0.0231 0.3709 1.0000
4.000 0.6786 0.02899 0.01738 -0.0223 0.3551 1.0000
4.250 0.7029 0.03009 0.01828 -0.0215 0.3418 1.0000
4.500 0.7254 0.03135 0.01959 -0.0208 0.3290 1.0000
4.750 0.7474 0.03278 0.02107 -0.0201 0.3180 1.0000
5.000 0.7718 0.03394 0.02207 -0.0194 0.3083 1.0000
5.250 0.7909 0.03585 0.02423 -0.0187 0.3001 1.0000
5.500 0.8133 0.03733 0.02571 -0.0181 0.2925 1.0000
5.750 0.8333 0.03919 0.02763 -0.0174 0.2859 1.0000
6.000 0.8480 0.04147 0.03020 -0.0166 0.2791 1.0000
6.250 0.8699 0.04310 0.03180 -0.0160 0.2737 1.0000
6.500 0.8891 0.04540 0.03413 -0.0155 0.2700 1.0000
6.750 0.8918 0.04921 0.03843 -0.0145 0.2670 1.0000
7.000 0.8903 0.05345 0.04305 -0.0138 0.2642 1.0000
7.250 0.8820 0.05836 0.04827 -0.0133 0.2623 1.0000
7.500 0.8521 0.06569 0.05593 -0.0137 0.2628 1.0000
7.750 0.8038 0.07544 0.06587 -0.0161 0.2669 1.0000
8.000 0.7800 0.08382 0.07432 -0.0195 0.2719 1.0000
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Polar data table (+)
Polar graphs
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