SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Reynolds number: 200,000 Max Cl/Cd: 45.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1094r8-il-200000.txt Download as CSV file: xf-sc1094r8-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SC1094 R8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5069 0.10383 0.10023 0.0067 1.0000 0.0468
-8.750 -0.5062 0.09965 0.09608 0.0035 1.0000 0.0485
-8.500 -0.5202 0.09291 0.08940 -0.0064 1.0000 0.0493
-8.250 -0.5049 0.09096 0.08747 -0.0026 1.0000 0.0500
-8.000 -0.4991 0.08767 0.08420 -0.0038 1.0000 0.0509
-7.750 -0.4980 0.08357 0.08014 -0.0072 1.0000 0.0519
-7.500 -0.4993 0.07767 0.07422 -0.0151 1.0000 0.0533
-7.250 -0.5001 0.07078 0.06719 -0.0226 1.0000 0.0544
-7.000 -0.4881 0.06816 0.06461 -0.0220 1.0000 0.0551
-6.750 -0.4771 0.06486 0.06127 -0.0231 1.0000 0.0565
-6.500 -0.4709 0.05870 0.05477 -0.0278 1.0000 0.0596
-6.250 -0.4565 0.05619 0.05232 -0.0272 1.0000 0.0604
-6.000 -0.4435 0.05267 0.04851 -0.0282 1.0000 0.0646
-5.750 -0.4314 0.04932 0.04511 -0.0278 1.0000 0.0657
-5.500 -0.4191 0.04707 0.04244 -0.0269 1.0000 0.0709
-5.250 -0.4064 0.04397 0.03945 -0.0258 1.0000 0.0717
-5.000 -0.3930 0.04260 0.03767 -0.0242 1.0000 0.0775
-4.750 -0.3803 0.03953 0.03473 -0.0230 1.0000 0.0785
-4.500 -0.3666 0.03773 0.03298 -0.0214 1.0000 0.0804
-4.250 -0.3524 0.03574 0.03079 -0.0200 1.0000 0.0865
-4.000 -0.3370 0.03417 0.02899 -0.0186 1.0000 0.0937
-3.750 -0.3212 0.03250 0.02739 -0.0173 1.0000 0.0966
-3.500 -0.3023 0.03080 0.02552 -0.0165 0.9997 0.1039
-3.250 -0.2510 0.02261 0.01566 -0.0168 0.9965 0.0536
-3.000 -0.2072 0.02008 0.01281 -0.0194 0.9920 0.0503
-2.750 -0.1630 0.01840 0.01071 -0.0218 0.9878 0.0494
-2.500 -0.1227 0.01739 0.00980 -0.0243 0.9812 0.0519
-2.250 -0.0778 0.01637 0.00859 -0.0271 0.9759 0.0539
-2.000 -0.0312 0.01527 0.00760 -0.0307 0.9722 0.0562
-1.750 0.0080 0.01447 0.00683 -0.0325 0.9626 0.0599
-1.500 0.0505 0.01369 0.00617 -0.0349 0.9513 0.0662
-1.250 0.0846 0.01297 0.00555 -0.0354 0.9344 0.0730
-1.000 0.1126 0.01240 0.00506 -0.0346 0.9161 0.0853
-0.750 0.1377 0.01168 0.00456 -0.0333 0.8973 0.1223
-0.500 0.1399 0.00892 0.00456 -0.0270 0.8792 0.8469
-0.250 0.1653 0.00887 0.00455 -0.0238 0.8567 0.9616
0.000 0.2343 0.00880 0.00426 -0.0309 0.8262 1.0000
0.250 0.2560 0.00875 0.00403 -0.0291 0.7918 1.0000
0.500 0.2781 0.00877 0.00381 -0.0274 0.7516 1.0000
0.750 0.3005 0.00885 0.00363 -0.0258 0.7034 1.0000
1.000 0.3231 0.00904 0.00348 -0.0244 0.6453 1.0000
1.250 0.3458 0.00932 0.00340 -0.0231 0.5809 1.0000
1.500 0.3687 0.00969 0.00339 -0.0220 0.5173 1.0000
1.750 0.3920 0.01008 0.00343 -0.0210 0.4612 1.0000
2.000 0.4159 0.01049 0.00352 -0.0203 0.4126 1.0000
2.250 0.4404 0.01089 0.00364 -0.0197 0.3701 1.0000
2.500 0.4652 0.01130 0.00380 -0.0192 0.3305 1.0000
2.750 0.4903 0.01174 0.00398 -0.0187 0.2939 1.0000
3.000 0.5158 0.01216 0.00420 -0.0183 0.2623 1.0000
3.250 0.5412 0.01263 0.00444 -0.0179 0.2383 1.0000
3.500 0.5671 0.01306 0.00472 -0.0176 0.2196 1.0000
3.750 0.5928 0.01354 0.00504 -0.0172 0.2050 1.0000
4.000 0.6191 0.01393 0.00537 -0.0169 0.1935 1.0000
4.250 0.6449 0.01445 0.00577 -0.0166 0.1841 1.0000
4.500 0.6710 0.01490 0.00614 -0.0163 0.1759 1.0000
4.750 0.6969 0.01546 0.00663 -0.0160 0.1690 1.0000
5.000 0.7232 0.01591 0.00704 -0.0157 0.1630 1.0000
5.250 0.7486 0.01667 0.00765 -0.0154 0.1579 1.0000
5.500 0.7752 0.01709 0.00814 -0.0151 0.1534 1.0000
5.750 0.8014 0.01758 0.00860 -0.0148 0.1491 1.0000
6.000 0.8271 0.01836 0.00925 -0.0146 0.1452 1.0000
6.250 0.8533 0.01895 0.00991 -0.0143 0.1421 1.0000
6.500 0.8795 0.01952 0.01055 -0.0140 0.1390 1.0000
6.750 0.9056 0.02013 0.01115 -0.0138 0.1362 1.0000
7.000 0.9314 0.02085 0.01181 -0.0136 0.1336 1.0000
7.250 0.9570 0.02187 0.01284 -0.0134 0.1312 1.0000
7.500 0.9825 0.02251 0.01363 -0.0130 0.1289 1.0000
7.750 1.0078 0.02327 0.01449 -0.0127 0.1268 1.0000
8.000 1.0331 0.02407 0.01535 -0.0124 0.1249 1.0000
8.250 1.0582 0.02490 0.01622 -0.0122 0.1231 1.0000
8.500 1.0834 0.02590 0.01720 -0.0120 0.1215 1.0000
8.750 1.1073 0.02737 0.01873 -0.0118 0.1198 1.0000
9.000 1.1301 0.02832 0.01994 -0.0112 0.1183 1.0000
9.250 1.1524 0.02951 0.02135 -0.0106 0.1169 1.0000
9.500 1.1744 0.03080 0.02282 -0.0101 0.1155 1.0000
9.750 1.1960 0.03212 0.02431 -0.0096 0.1143 1.0000
10.000 1.2178 0.03338 0.02568 -0.0091 0.1131 1.0000
10.250 1.2393 0.03458 0.02697 -0.0086 0.1118 1.0000
10.500 1.2607 0.03596 0.02840 -0.0083 0.1106 1.0000
10.750 1.2793 0.03849 0.03102 -0.0079 0.1096 1.0000
11.000 1.2911 0.04057 0.03349 -0.0066 0.1089 1.0000
11.250 1.2992 0.04314 0.03645 -0.0052 0.1081 1.0000
11.500 1.3021 0.04616 0.03988 -0.0035 0.1073 1.0000
11.750 1.2989 0.04959 0.04369 -0.0017 0.1064 1.0000
12.000 1.2880 0.05359 0.04806 0.0002 0.1057 1.0000
12.250 1.2604 0.05855 0.05337 0.0026 0.1056 1.0000
12.500 1.2035 0.06585 0.06102 0.0037 0.1060 1.0000
12.750 1.0320 0.09819 0.09379 -0.0173 0.1101 1.0000
13.000 1.0423 0.10011 0.09571 -0.0162 0.1096 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)