S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 200,000 Max Cl/Cd: 58.56 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8052-il-200000-n5.txt Download as CSV file: xf-s8052-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6429 0.06586 0.06191 -0.0435 1.0000 0.0134
-11.000 -0.6638 0.05915 0.05505 -0.0487 1.0000 0.0133
-10.750 -0.6859 0.05370 0.04942 -0.0518 1.0000 0.0133
-10.500 -0.7008 0.04995 0.04552 -0.0527 1.0000 0.0133
-10.250 -0.7184 0.04656 0.04192 -0.0518 1.0000 0.0133
-10.000 -0.7303 0.04387 0.03904 -0.0495 1.0000 0.0132
-9.750 -0.7376 0.04078 0.03564 -0.0475 1.0000 0.0133
-9.500 -0.7389 0.03791 0.03246 -0.0455 1.0000 0.0133
-9.250 -0.7355 0.03533 0.02955 -0.0436 1.0000 0.0133
-9.000 -0.7289 0.03308 0.02698 -0.0416 1.0000 0.0134
-8.750 -0.7182 0.03091 0.02458 -0.0402 0.9969 0.0135
-8.500 -0.6920 0.02857 0.02198 -0.0416 0.9796 0.0137
-8.250 -0.6636 0.02671 0.01992 -0.0429 0.9662 0.0140
-8.000 -0.6344 0.02512 0.01812 -0.0442 0.9542 0.0144
-7.750 -0.6059 0.02373 0.01655 -0.0450 0.9425 0.0148
-7.500 -0.5791 0.02251 0.01515 -0.0454 0.9310 0.0151
-7.250 -0.5533 0.02154 0.01403 -0.0454 0.9198 0.0160
-7.000 -0.5278 0.02067 0.01300 -0.0451 0.9096 0.0169
-6.750 -0.5040 0.01978 0.01197 -0.0446 0.8994 0.0175
-6.500 -0.4821 0.01878 0.01091 -0.0438 0.8900 0.0181
-6.250 -0.4595 0.01804 0.01010 -0.0430 0.8818 0.0187
-6.000 -0.4370 0.01737 0.00936 -0.0422 0.8730 0.0195
-5.750 -0.4140 0.01677 0.00865 -0.0413 0.8660 0.0204
-5.500 -0.3906 0.01621 0.00798 -0.0406 0.8581 0.0217
-5.250 -0.3673 0.01563 0.00731 -0.0398 0.8517 0.0235
-5.000 -0.3430 0.01515 0.00677 -0.0392 0.8448 0.0265
-4.750 -0.3190 0.01464 0.00624 -0.0385 0.8387 0.0340
-4.500 -0.2952 0.01408 0.00576 -0.0379 0.8330 0.0537
-4.250 -0.2712 0.01356 0.00536 -0.0374 0.8268 0.0852
-4.000 -0.2473 0.01305 0.00502 -0.0368 0.8218 0.1305
-3.750 -0.2252 0.01232 0.00473 -0.0363 0.8159 0.2196
-3.500 -0.2029 0.01167 0.00447 -0.0356 0.8103 0.3126
-3.250 -0.1798 0.01118 0.00423 -0.0348 0.8057 0.3932
-3.000 -0.1570 0.01071 0.00410 -0.0340 0.7997 0.4786
-2.750 -0.1336 0.01041 0.00408 -0.0329 0.7943 0.5597
-2.500 -0.1084 0.01030 0.00406 -0.0321 0.7896 0.6133
-2.250 -0.0823 0.01025 0.00405 -0.0315 0.7835 0.6495
-2.000 -0.0560 0.01023 0.00402 -0.0309 0.7782 0.6764
-1.750 -0.0293 0.01023 0.00398 -0.0304 0.7733 0.6981
-1.500 -0.0026 0.01022 0.00397 -0.0299 0.7673 0.7160
-1.250 0.0242 0.01022 0.00394 -0.0294 0.7620 0.7324
-1.000 0.0510 0.01022 0.00392 -0.0290 0.7561 0.7472
-0.750 0.0778 0.01022 0.00389 -0.0285 0.7496 0.7608
-0.500 0.1048 0.01022 0.00384 -0.0281 0.7442 0.7736
-0.250 0.1314 0.01022 0.00386 -0.0276 0.7368 0.7847
0.000 0.1583 0.01020 0.00381 -0.0271 0.7304 0.7957
0.250 0.1849 0.01020 0.00381 -0.0267 0.7222 0.8069
0.500 0.2116 0.01018 0.00376 -0.0262 0.7147 0.8180
0.750 0.2379 0.01016 0.00377 -0.0256 0.7050 0.8284
1.000 0.2644 0.01014 0.00373 -0.0251 0.6959 0.8389
1.250 0.2908 0.01013 0.00371 -0.0246 0.6857 0.8498
1.500 0.3173 0.01010 0.00371 -0.0240 0.6745 0.8590
1.750 0.3440 0.01009 0.00369 -0.0236 0.6630 0.8685
2.000 0.3709 0.01008 0.00368 -0.0232 0.6507 0.8782
2.250 0.3981 0.01007 0.00367 -0.0229 0.6361 0.8877
2.500 0.4255 0.01007 0.00367 -0.0226 0.6188 0.8980
2.750 0.4538 0.01009 0.00368 -0.0225 0.5995 0.9089
3.000 0.4834 0.01014 0.00367 -0.0227 0.5783 0.9196
3.250 0.5139 0.01023 0.00370 -0.0232 0.5538 0.9308
3.500 0.5452 0.01038 0.00377 -0.0239 0.5257 0.9426
3.750 0.5777 0.01059 0.00386 -0.0249 0.4949 0.9545
4.000 0.6106 0.01087 0.00399 -0.0262 0.4605 0.9665
4.250 0.6433 0.01119 0.00417 -0.0275 0.4242 0.9798
4.500 0.6763 0.01158 0.00441 -0.0290 0.3878 0.9933
4.750 0.7021 0.01199 0.00466 -0.0291 0.3539 1.0000
5.000 0.7207 0.01240 0.00492 -0.0277 0.3240 1.0000
5.250 0.7401 0.01283 0.00522 -0.0264 0.2963 1.0000
5.500 0.7606 0.01326 0.00553 -0.0254 0.2712 1.0000
5.750 0.7814 0.01370 0.00587 -0.0244 0.2507 1.0000
6.000 0.8029 0.01411 0.00622 -0.0235 0.2326 1.0000
6.250 0.8244 0.01453 0.00660 -0.0226 0.2158 1.0000
6.500 0.8459 0.01497 0.00699 -0.0218 0.2006 1.0000
6.750 0.8674 0.01541 0.00739 -0.0209 0.1872 1.0000
7.000 0.8887 0.01588 0.00783 -0.0201 0.1744 1.0000
7.250 0.9097 0.01636 0.00827 -0.0192 0.1622 1.0000
7.500 0.9308 0.01683 0.00873 -0.0183 0.1509 1.0000
7.750 0.9518 0.01729 0.00920 -0.0175 0.1404 1.0000
8.000 0.9722 0.01780 0.00972 -0.0165 0.1309 1.0000
8.250 0.9915 0.01837 0.01026 -0.0155 0.1214 1.0000
8.500 1.0119 0.01886 0.01079 -0.0146 0.1126 1.0000
8.750 1.0308 0.01943 0.01138 -0.0135 0.1044 1.0000
9.000 1.0488 0.02004 0.01199 -0.0123 0.0962 1.0000
9.250 1.0669 0.02063 0.01264 -0.0111 0.0890 1.0000
9.500 1.0823 0.02135 0.01334 -0.0097 0.0827 1.0000
9.750 1.0979 0.02198 0.01405 -0.0081 0.0775 1.0000
10.000 1.1106 0.02274 0.01482 -0.0063 0.0726 1.0000
10.250 1.1227 0.02356 0.01568 -0.0044 0.0687 1.0000
10.500 1.1359 0.02436 0.01658 -0.0029 0.0645 1.0000
10.750 1.1468 0.02531 0.01756 -0.0012 0.0610 1.0000
11.000 1.1562 0.02641 0.01870 0.0005 0.0582 1.0000
11.250 1.1681 0.02740 0.01981 0.0018 0.0559 1.0000
11.500 1.1788 0.02850 0.02101 0.0032 0.0535 1.0000
11.750 1.1880 0.02973 0.02231 0.0045 0.0514 1.0000
12.000 1.1946 0.03119 0.02381 0.0058 0.0495 1.0000
12.250 1.2018 0.03268 0.02538 0.0070 0.0479 1.0000
12.500 1.2113 0.03404 0.02689 0.0079 0.0463 1.0000
12.750 1.2193 0.03555 0.02853 0.0088 0.0447 1.0000
13.000 1.2262 0.03718 0.03028 0.0096 0.0434 1.0000
13.250 1.2320 0.03896 0.03215 0.0104 0.0422 1.0000
13.500 1.2358 0.04092 0.03417 0.0109 0.0407 1.0000
13.750 1.2376 0.04319 0.03652 0.0115 0.0398 1.0000
14.000 1.2414 0.04533 0.03880 0.0118 0.0384 1.0000
14.250 1.2454 0.04751 0.04114 0.0119 0.0371 1.0000
14.500 1.2482 0.04985 0.04364 0.0118 0.0356 1.0000
14.750 1.2493 0.05247 0.04639 0.0115 0.0344 1.0000
15.000 1.2486 0.05538 0.04941 0.0109 0.0332 1.0000
15.250 1.2451 0.05874 0.05286 0.0100 0.0321 1.0000
15.500 1.2399 0.06249 0.05668 0.0090 0.0312 1.0000
15.750 1.2382 0.06609 0.06049 0.0077 0.0301 1.0000
16.000 1.2340 0.07014 0.06472 0.0061 0.0294 1.0000
16.250 1.2287 0.07453 0.06928 0.0041 0.0284 1.0000
16.500 1.2214 0.07942 0.07433 0.0018 0.0275 1.0000
16.750 1.2130 0.08466 0.07972 -0.0008 0.0269 1.0000
17.000 1.2029 0.09038 0.08557 -0.0038 0.0264 1.0000
17.250 1.1911 0.09657 0.09189 -0.0073 0.0258 1.0000
17.500 1.1781 0.10314 0.09858 -0.0109 0.0253 1.0000
17.750 1.1652 0.10981 0.10537 -0.0146 0.0250 1.0000
18.000 1.1517 0.11671 0.11235 -0.0185 0.0245 1.0000
18.250 1.1360 0.12438 0.12020 -0.0230 0.0243 1.0000
18.500 1.1180 0.13278 0.12878 -0.0280 0.0240 1.0000
18.750 1.0983 0.14179 0.13795 -0.0334 0.0237 1.0000
19.000 1.0742 0.15217 0.14850 -0.0397 0.0236 1.0000
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Polar data table (+)
Polar graphs
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