SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Reynolds number: 200,000 Max Cl/Cd: 46.36 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc1012r8-il-200000.txt Download as CSV file: xf-sc1012r8-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4084 0.09790 0.09434 -0.0098 1.0000 0.0548
-8.500 -0.4124 0.09308 0.08956 -0.0148 1.0000 0.0567
-8.250 -0.4552 0.08344 0.07984 -0.0323 1.0000 0.0576
-8.000 -0.4438 0.07976 0.07625 -0.0311 1.0000 0.0581
-7.750 -0.4273 0.07809 0.07467 -0.0281 1.0000 0.0587
-7.500 -0.4194 0.07551 0.07212 -0.0279 1.0000 0.0596
-7.250 -0.4168 0.07229 0.06890 -0.0290 1.0000 0.0607
-7.000 -0.4198 0.06895 0.06555 -0.0296 1.0000 0.0621
-6.750 -0.4632 0.06531 0.06133 -0.0292 1.0000 0.0654
-6.500 -0.4629 0.06143 0.05754 -0.0272 1.0000 0.0660
-6.250 -0.4581 0.05905 0.05526 -0.0249 1.0000 0.0664
-6.000 -0.4548 0.05708 0.05333 -0.0225 1.0000 0.0670
-5.750 -0.4514 0.05520 0.05147 -0.0203 1.0000 0.0678
-5.500 -0.4263 0.05231 0.04850 -0.0224 0.9966 0.0700
-5.250 -0.3894 0.04710 0.04278 -0.0281 0.9900 0.0760
-5.000 -0.3472 0.04404 0.03974 -0.0325 0.9844 0.0783
-4.750 -0.3088 0.04064 0.03583 -0.0363 0.9772 0.0865
-4.500 -0.2696 0.03782 0.03307 -0.0398 0.9734 0.0890
-4.250 -0.2335 0.03562 0.03045 -0.0422 0.9668 0.0988
-4.000 -0.1914 0.02640 0.01990 -0.0425 0.9632 0.0568
-3.750 -0.1552 0.02406 0.01735 -0.0440 0.9564 0.0557
-3.500 -0.1160 0.02173 0.01472 -0.0456 0.9506 0.0539
-3.250 -0.0831 0.02014 0.01290 -0.0458 0.9412 0.0537
-3.000 -0.0492 0.01892 0.01154 -0.0462 0.9329 0.0544
-2.750 -0.0189 0.01804 0.01053 -0.0457 0.9223 0.0564
-2.500 0.0076 0.01715 0.00960 -0.0447 0.9097 0.0586
-2.250 0.0330 0.01638 0.00887 -0.0433 0.8960 0.0608
-2.000 0.0569 0.01568 0.00815 -0.0414 0.8793 0.0632
-1.750 0.0802 0.01500 0.00743 -0.0394 0.8604 0.0662
-1.500 0.1037 0.01442 0.00691 -0.0377 0.8407 0.0711
-1.250 0.1281 0.01383 0.00631 -0.0362 0.8209 0.0765
-1.000 0.1530 0.01339 0.00585 -0.0349 0.7991 0.0849
-0.750 0.1777 0.01280 0.00533 -0.0336 0.7751 0.1029
-0.500 0.2023 0.01197 0.00482 -0.0326 0.7475 0.1837
-0.250 0.2068 0.00975 0.00493 -0.0270 0.7211 0.8203
0.000 0.2229 0.00985 0.00501 -0.0224 0.6873 0.9075
0.250 0.2511 0.01010 0.00502 -0.0206 0.6449 0.9598
0.500 0.3325 0.01062 0.00501 -0.0300 0.5702 0.9906
0.750 0.3823 0.01098 0.00492 -0.0344 0.5095 1.0000
1.000 0.4051 0.01120 0.00485 -0.0336 0.4689 1.0000
1.250 0.4275 0.01144 0.00483 -0.0327 0.4348 1.0000
1.500 0.4499 0.01168 0.00484 -0.0318 0.4046 1.0000
1.750 0.4719 0.01193 0.00488 -0.0308 0.3780 1.0000
2.000 0.4938 0.01218 0.00494 -0.0298 0.3526 1.0000
2.250 0.5154 0.01247 0.00504 -0.0287 0.3285 1.0000
2.500 0.5369 0.01279 0.00516 -0.0276 0.3057 1.0000
2.750 0.5589 0.01309 0.00531 -0.0265 0.2838 1.0000
3.000 0.5809 0.01342 0.00549 -0.0254 0.2641 1.0000
3.250 0.6032 0.01377 0.00568 -0.0244 0.2472 1.0000
3.500 0.6260 0.01416 0.00591 -0.0235 0.2330 1.0000
3.750 0.6495 0.01456 0.00616 -0.0227 0.2208 1.0000
4.000 0.6740 0.01492 0.00645 -0.0221 0.2105 1.0000
4.250 0.6979 0.01544 0.00680 -0.0214 0.2019 1.0000
4.500 0.7232 0.01580 0.00713 -0.0209 0.1941 1.0000
4.750 0.7473 0.01643 0.00757 -0.0204 0.1870 1.0000
5.000 0.7731 0.01677 0.00794 -0.0200 0.1809 1.0000
5.250 0.7983 0.01723 0.00833 -0.0195 0.1753 1.0000
5.500 0.8231 0.01794 0.00891 -0.0191 0.1704 1.0000
5.750 0.8488 0.01837 0.00938 -0.0187 0.1660 1.0000
6.000 0.8743 0.01886 0.00984 -0.0184 0.1620 1.0000
6.250 0.8994 0.01952 0.01039 -0.0180 0.1583 1.0000
6.500 0.9247 0.02027 0.01111 -0.0177 0.1549 1.0000
6.750 0.9500 0.02075 0.01166 -0.0173 0.1516 1.0000
7.000 0.9752 0.02129 0.01221 -0.0170 0.1485 1.0000
7.250 1.0005 0.02189 0.01277 -0.0167 0.1458 1.0000
7.500 1.0257 0.02277 0.01356 -0.0164 0.1433 1.0000
7.750 1.0506 0.02373 0.01457 -0.0162 0.1412 1.0000
8.000 1.0750 0.02437 0.01532 -0.0157 0.1393 1.0000
8.250 1.0992 0.02509 0.01613 -0.0153 0.1373 1.0000
8.500 1.1232 0.02581 0.01691 -0.0149 0.1352 1.0000
8.750 1.1471 0.02652 0.01763 -0.0145 0.1333 1.0000
9.000 1.1713 0.02728 0.01837 -0.0142 0.1315 1.0000
9.250 1.1956 0.02842 0.01948 -0.0140 0.1298 1.0000
9.500 1.2179 0.02990 0.02105 -0.0136 0.1283 1.0000
9.750 1.2388 0.03083 0.02215 -0.0129 0.1273 1.0000
10.000 1.2590 0.03190 0.02340 -0.0121 0.1261 1.0000
10.250 1.2786 0.03308 0.02474 -0.0113 0.1248 1.0000
10.500 1.2976 0.03432 0.02613 -0.0105 0.1237 1.0000
10.750 1.3160 0.03560 0.02754 -0.0097 0.1226 1.0000
11.000 1.3339 0.03688 0.02894 -0.0089 0.1215 1.0000
11.250 1.3511 0.03810 0.03027 -0.0080 0.1204 1.0000
11.500 1.3682 0.03932 0.03156 -0.0072 0.1193 1.0000
11.750 1.3856 0.04064 0.03294 -0.0064 0.1184 1.0000
12.000 1.4021 0.04239 0.03475 -0.0058 0.1175 1.0000
12.250 1.4135 0.04512 0.03760 -0.0049 0.1167 1.0000
12.500 1.4150 0.04773 0.04047 -0.0030 0.1162 1.0000
12.750 1.4107 0.05008 0.04310 -0.0005 0.1158 1.0000
13.000 1.3975 0.05271 0.04600 0.0027 0.1155 1.0000
13.250 1.3763 0.05595 0.04950 0.0056 0.1153 1.0000
13.500 1.3469 0.06025 0.05409 0.0075 0.1151 1.0000
13.750 1.3027 0.06663 0.06077 0.0076 0.1151 1.0000
14.000 1.2024 0.08175 0.07636 0.0008 0.1156 1.0000
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Polar data table (+)
Polar graphs
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