SIKORSKY SC2110 AIRFOIL (sc2110-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC2110 AIRFOIL (sc2110-il) Reynolds number: 50,000 Max Cl/Cd: 26.51 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc2110-il-50000.txt Download as CSV file: xf-sc2110-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC2110 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5159 0.11102 0.10468 0.0036 1.0000 0.2456
-8.500 -0.5078 0.10735 0.10105 0.0040 1.0000 0.2615
-8.250 -0.5058 0.10413 0.09790 0.0037 1.0000 0.2777
-8.000 -0.4733 0.09917 0.09293 0.0072 1.0000 0.2996
-7.750 -0.4712 0.09646 0.09028 0.0076 1.0000 0.3228
-7.500 -0.4559 0.09297 0.08681 0.0094 1.0000 0.3489
-7.250 -0.4448 0.09004 0.08393 0.0114 1.0000 0.3807
-7.000 -0.4386 0.08775 0.08171 0.0138 1.0000 0.4184
-6.750 -0.4148 0.08465 0.07863 0.0172 1.0000 0.4640
-6.500 -0.3925 0.08185 0.07586 0.0209 1.0000 0.5191
-6.250 -0.3551 0.07860 0.07258 0.0244 1.0000 0.5889
-6.000 -0.3269 0.07571 0.06971 0.0272 1.0000 0.6561
-5.750 -0.2930 0.07166 0.06566 0.0273 1.0000 0.7094
-5.000 -0.3385 0.06412 0.05846 0.0246 1.0000 0.6247
-4.750 -0.4061 0.06183 0.05643 0.0256 1.0000 0.5528
-4.250 -0.4288 0.04348 0.03534 -0.0156 1.0000 0.1789
-4.000 -0.4047 0.04033 0.03178 -0.0150 1.0000 0.1583
-3.750 -0.3797 0.03791 0.02879 -0.0142 1.0000 0.1443
-3.500 -0.3531 0.03622 0.02629 -0.0130 1.0000 0.1325
-3.250 -0.3292 0.03361 0.02357 -0.0123 1.0000 0.1283
-3.000 -0.3034 0.03164 0.02129 -0.0114 1.0000 0.1240
-2.750 -0.2772 0.03002 0.01934 -0.0105 1.0000 0.1224
-2.500 -0.2516 0.02863 0.01778 -0.0096 1.0000 0.1255
-2.250 -0.2252 0.02743 0.01639 -0.0086 1.0000 0.1288
-2.000 -0.1982 0.02639 0.01519 -0.0075 1.0000 0.1318
-1.750 -0.1720 0.02525 0.01414 -0.0065 1.0000 0.1405
-1.500 -0.1473 0.02436 0.01322 -0.0055 1.0000 0.1533
-1.250 -0.1231 0.02340 0.01233 -0.0047 1.0000 0.1741
-1.000 -0.0601 0.01988 0.01180 -0.0045 1.0000 1.0000
-0.750 -0.0516 0.01986 0.01143 -0.0017 1.0000 1.0000
-0.500 -0.0398 0.01991 0.01119 0.0003 1.0000 1.0000
-0.250 -0.0250 0.02002 0.01106 0.0017 1.0000 1.0000
0.000 -0.0081 0.02019 0.01103 0.0027 1.0000 1.0000
0.250 0.0103 0.02043 0.01108 0.0034 1.0000 1.0000
0.500 0.0295 0.02072 0.01122 0.0039 1.0000 1.0000
0.750 0.0493 0.02107 0.01145 0.0042 1.0000 1.0000
1.000 0.0694 0.02149 0.01177 0.0044 1.0000 1.0000
1.250 0.0894 0.02197 0.01218 0.0044 1.0000 1.0000
1.500 0.1092 0.02254 0.01271 0.0043 1.0000 1.0000
1.750 0.1950 0.02398 0.01413 -0.0077 0.9701 1.0000
2.000 0.2894 0.02490 0.01514 -0.0197 0.9267 1.0000
2.250 0.3878 0.02454 0.01502 -0.0299 0.8770 1.0000
2.500 0.4446 0.02314 0.01382 -0.0307 0.8188 1.0000
2.750 0.4800 0.02123 0.01197 -0.0266 0.7468 1.0000
3.000 0.5052 0.01980 0.01021 -0.0212 0.6498 1.0000
3.250 0.5257 0.01983 0.00949 -0.0169 0.5672 1.0000
3.500 0.5466 0.02068 0.00976 -0.0148 0.5106 1.0000
3.750 0.5701 0.02164 0.01031 -0.0135 0.4719 1.0000
4.000 0.5946 0.02263 0.01103 -0.0126 0.4413 1.0000
4.250 0.6198 0.02368 0.01196 -0.0121 0.4167 1.0000
4.500 0.6451 0.02477 0.01290 -0.0115 0.3958 1.0000
4.750 0.6705 0.02592 0.01393 -0.0111 0.3778 1.0000
5.000 0.6959 0.02717 0.01517 -0.0108 0.3625 1.0000
5.250 0.7208 0.02848 0.01656 -0.0105 0.3482 1.0000
5.500 0.7454 0.02987 0.01801 -0.0103 0.3349 1.0000
5.750 0.7702 0.03140 0.01958 -0.0101 0.3245 1.0000
6.000 0.7944 0.03294 0.02123 -0.0098 0.3141 1.0000
6.250 0.8166 0.03474 0.02331 -0.0097 0.3040 1.0000
6.500 0.8413 0.03636 0.02482 -0.0093 0.2953 1.0000
6.750 0.8597 0.03877 0.02777 -0.0093 0.2883 1.0000
7.000 0.8825 0.04063 0.02967 -0.0089 0.2810 1.0000
7.250 0.8979 0.04337 0.03284 -0.0087 0.2741 1.0000
7.500 0.9146 0.04590 0.03564 -0.0084 0.2678 1.0000
7.750 0.9368 0.04834 0.03807 -0.0081 0.2634 1.0000
8.000 0.9383 0.05275 0.04308 -0.0081 0.2606 1.0000
8.250 0.9362 0.05751 0.04826 -0.0082 0.2577 1.0000
8.500 0.9289 0.06276 0.05383 -0.0086 0.2558 1.0000
8.750 0.9060 0.06990 0.06123 -0.0102 0.2576 1.0000
9.000 0.8885 0.07701 0.06846 -0.0123 0.2613 1.0000
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Polar data table (+)
Polar graphs
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