S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 100,000 Max Cl/Cd: 46.33 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8052-il-100000-n5.txt Download as CSV file: xf-s8052-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5196 0.09441 0.08932 -0.0267 1.0000 0.0250
-10.500 -0.5908 0.06993 0.06467 -0.0448 1.0000 0.0222
-10.250 -0.6101 0.06418 0.05881 -0.0488 1.0000 0.0221
-10.000 -0.6265 0.05982 0.05435 -0.0507 1.0000 0.0220
-9.750 -0.6456 0.05602 0.05040 -0.0508 1.0000 0.0219
-9.500 -0.6610 0.05276 0.04695 -0.0493 1.0000 0.0219
-9.250 -0.6707 0.04936 0.04328 -0.0478 1.0000 0.0220
-9.000 -0.6766 0.04607 0.03962 -0.0460 1.0000 0.0221
-8.750 -0.6769 0.04319 0.03645 -0.0441 1.0000 0.0225
-8.500 -0.6711 0.04101 0.03415 -0.0425 1.0000 0.0230
-8.250 -0.6645 0.03935 0.03239 -0.0405 1.0000 0.0236
-8.000 -0.6605 0.03770 0.03059 -0.0378 1.0000 0.0242
-7.750 -0.6582 0.03612 0.02881 -0.0346 0.9996 0.0246
-7.500 -0.6310 0.03339 0.02564 -0.0361 0.9891 0.0250
-7.250 -0.6013 0.03087 0.02273 -0.0375 0.9810 0.0256
-7.000 -0.5707 0.02875 0.02028 -0.0387 0.9735 0.0263
-6.750 -0.5387 0.02691 0.01818 -0.0400 0.9671 0.0271
-6.500 -0.5074 0.02535 0.01639 -0.0410 0.9598 0.0282
-6.250 -0.4771 0.02390 0.01486 -0.0420 0.9531 0.0293
-6.000 -0.4481 0.02283 0.01376 -0.0429 0.9453 0.0316
-5.750 -0.4182 0.02191 0.01271 -0.0436 0.9385 0.0350
-5.500 -0.3916 0.02091 0.01168 -0.0439 0.9305 0.0390
-5.250 -0.3642 0.02005 0.01068 -0.0440 0.9232 0.0447
-5.000 -0.3390 0.01919 0.00980 -0.0438 0.9154 0.0556
-4.750 -0.3145 0.01824 0.00907 -0.0436 0.9082 0.0854
-4.500 -0.2920 0.01733 0.00854 -0.0432 0.9005 0.1501
-4.250 -0.2696 0.01645 0.00810 -0.0427 0.8938 0.2421
-4.000 -0.2488 0.01571 0.00779 -0.0418 0.8863 0.3386
-3.750 -0.2267 0.01505 0.00757 -0.0408 0.8804 0.4430
-3.500 -0.2067 0.01472 0.00764 -0.0390 0.8729 0.5387
-3.250 -0.1818 0.01465 0.00768 -0.0378 0.8675 0.6099
-3.000 -0.1584 0.01470 0.00773 -0.0364 0.8606 0.6556
-2.750 -0.1334 0.01475 0.00774 -0.0353 0.8546 0.6899
-2.500 -0.1080 0.01481 0.00772 -0.0342 0.8489 0.7175
-2.250 -0.0840 0.01488 0.00772 -0.0330 0.8419 0.7412
-2.000 -0.0577 0.01492 0.00769 -0.0321 0.8368 0.7614
-1.750 -0.0338 0.01500 0.00772 -0.0308 0.8295 0.7795
-1.500 -0.0080 0.01503 0.00767 -0.0299 0.8236 0.7963
-1.250 0.0174 0.01506 0.00765 -0.0289 0.8173 0.8116
-1.000 0.0428 0.01510 0.00763 -0.0281 0.8105 0.8260
-0.750 0.0702 0.01509 0.00754 -0.0274 0.8053 0.8395
-0.500 0.0951 0.01513 0.00756 -0.0266 0.7972 0.8529
-0.250 0.1228 0.01511 0.00747 -0.0261 0.7913 0.8658
0.000 0.1502 0.01514 0.00749 -0.0258 0.7830 0.8776
0.250 0.1809 0.01511 0.00740 -0.0259 0.7765 0.8884
0.500 0.2095 0.01512 0.00741 -0.0258 0.7680 0.8996
0.750 0.2396 0.01506 0.00730 -0.0259 0.7608 0.9107
1.000 0.2727 0.01506 0.00729 -0.0268 0.7508 0.9193
1.250 0.3052 0.01499 0.00719 -0.0275 0.7421 0.9285
1.500 0.3387 0.01493 0.00710 -0.0284 0.7314 0.9371
1.750 0.3728 0.01487 0.00705 -0.0296 0.7195 0.9454
2.000 0.4062 0.01480 0.00697 -0.0306 0.7073 0.9547
2.250 0.4428 0.01471 0.00688 -0.0322 0.6944 0.9621
2.500 0.4774 0.01463 0.00680 -0.0335 0.6803 0.9711
2.750 0.5137 0.01455 0.00674 -0.0352 0.6642 0.9798
3.000 0.5494 0.01448 0.00668 -0.0369 0.6459 0.9893
3.250 0.5851 0.01440 0.00661 -0.0386 0.6256 0.9996
3.500 0.6025 0.01440 0.00661 -0.0367 0.6059 1.0000
3.750 0.6200 0.01444 0.00660 -0.0348 0.5843 1.0000
4.000 0.6386 0.01450 0.00659 -0.0330 0.5605 1.0000
4.250 0.6577 0.01463 0.00662 -0.0313 0.5345 1.0000
4.500 0.6771 0.01483 0.00670 -0.0297 0.5050 1.0000
4.750 0.6967 0.01510 0.00684 -0.0282 0.4732 1.0000
5.000 0.7163 0.01546 0.00705 -0.0267 0.4405 1.0000
5.250 0.7357 0.01588 0.00734 -0.0253 0.4070 1.0000
5.500 0.7549 0.01637 0.00767 -0.0239 0.3745 1.0000
5.750 0.7741 0.01690 0.00805 -0.0226 0.3439 1.0000
6.000 0.7933 0.01746 0.00848 -0.0213 0.3154 1.0000
6.250 0.8125 0.01804 0.00897 -0.0201 0.2903 1.0000
6.500 0.8317 0.01865 0.00947 -0.0190 0.2677 1.0000
6.750 0.8511 0.01926 0.01001 -0.0179 0.2484 1.0000
7.000 0.8707 0.01987 0.01058 -0.0168 0.2309 1.0000
7.250 0.8901 0.02050 0.01120 -0.0157 0.2155 1.0000
7.500 0.9092 0.02115 0.01183 -0.0146 0.2011 1.0000
7.750 0.9279 0.02182 0.01248 -0.0135 0.1880 1.0000
8.000 0.9460 0.02253 0.01317 -0.0124 0.1759 1.0000
8.250 0.9637 0.02325 0.01391 -0.0112 0.1640 1.0000
8.500 0.9818 0.02395 0.01467 -0.0100 0.1527 1.0000
8.750 0.9988 0.02472 0.01546 -0.0088 0.1422 1.0000
9.000 1.0143 0.02555 0.01629 -0.0075 0.1330 1.0000
9.250 1.0299 0.02637 0.01717 -0.0061 0.1241 1.0000
9.500 1.0446 0.02725 0.01813 -0.0047 0.1158 1.0000
9.750 1.0559 0.02818 0.01906 -0.0029 0.1089 1.0000
10.000 1.0694 0.02914 0.02013 -0.0013 0.1021 1.0000
10.250 1.0801 0.03018 0.02120 0.0004 0.0966 1.0000
10.500 1.0917 0.03131 0.02242 0.0019 0.0910 1.0000
10.750 1.1024 0.03246 0.02366 0.0033 0.0860 1.0000
11.000 1.1106 0.03381 0.02499 0.0048 0.0821 1.0000
11.250 1.1227 0.03514 0.02652 0.0060 0.0783 1.0000
11.500 1.1325 0.03656 0.02806 0.0072 0.0749 1.0000
11.750 1.1405 0.03806 0.02961 0.0084 0.0721 1.0000
12.000 1.1487 0.03975 0.03135 0.0095 0.0694 1.0000
12.250 1.1569 0.04146 0.03330 0.0104 0.0665 1.0000
12.500 1.1636 0.04326 0.03525 0.0113 0.0640 1.0000
12.750 1.1695 0.04516 0.03726 0.0121 0.0620 1.0000
13.000 1.1752 0.04715 0.03934 0.0128 0.0604 1.0000
13.250 1.1818 0.04932 0.04155 0.0135 0.0588 1.0000
13.500 1.1823 0.05195 0.04449 0.0140 0.0573 1.0000
13.750 1.1810 0.05482 0.04761 0.0142 0.0558 1.0000
14.000 1.1783 0.05788 0.05090 0.0142 0.0544 1.0000
14.250 1.1741 0.06113 0.05434 0.0140 0.0530 1.0000
14.500 1.1695 0.06454 0.05791 0.0134 0.0519 1.0000
14.750 1.1642 0.06820 0.06174 0.0126 0.0510 1.0000
15.000 1.1589 0.07197 0.06563 0.0116 0.0501 1.0000
15.250 1.1550 0.07571 0.06947 0.0105 0.0492 1.0000
15.500 1.1468 0.08027 0.07412 0.0089 0.0484 1.0000
15.750 1.1255 0.08706 0.08119 0.0055 0.0482 1.0000
16.000 1.1000 0.09513 0.08951 0.0009 0.0480 1.0000
16.250 1.0689 0.10504 0.09966 -0.0052 0.0480 1.0000
16.500 1.0262 0.11848 0.11331 -0.0139 0.0483 1.0000
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Polar data table (+)
Polar graphs
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