S8037 (16%) (s8037-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 100,000 Max Cl/Cd: 48.32 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8037-il-100000-n5.txt Download as CSV file: xf-s8037-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8037 (16%)
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4565 0.08924 0.08397 -0.0595 1.0000 0.0266
-12.000 -0.4936 0.07786 0.07251 -0.0667 1.0000 0.0262
-11.750 -0.5242 0.07018 0.06475 -0.0714 1.0000 0.0258
-11.500 -0.5514 0.06451 0.05896 -0.0738 1.0000 0.0255
-11.250 -0.5804 0.05975 0.05404 -0.0745 1.0000 0.0254
-11.000 -0.6059 0.05618 0.05033 -0.0732 1.0000 0.0254
-10.750 -0.6310 0.05336 0.04738 -0.0702 1.0000 0.0254
-10.500 -0.6555 0.05133 0.04523 -0.0656 1.0000 0.0253
-10.250 -0.6821 0.05023 0.04409 -0.0593 0.9998 0.0253
-10.000 -0.6774 0.04608 0.03948 -0.0604 0.9825 0.0257
-9.750 -0.6704 0.04263 0.03554 -0.0602 0.9637 0.0264
-9.500 -0.6562 0.03984 0.03231 -0.0604 0.9503 0.0275
-9.250 -0.6312 0.03808 0.03044 -0.0616 0.9410 0.0286
-9.000 -0.6058 0.03589 0.02795 -0.0627 0.9319 0.0296
-8.750 -0.5795 0.03364 0.02536 -0.0635 0.9227 0.0306
-8.500 -0.5491 0.03145 0.02274 -0.0647 0.9151 0.0320
-8.250 -0.5205 0.03002 0.02128 -0.0657 0.9058 0.0333
-8.000 -0.4896 0.02877 0.01989 -0.0670 0.8980 0.0355
-7.750 -0.4612 0.02745 0.01831 -0.0674 0.8886 0.0379
-7.500 -0.4325 0.02619 0.01706 -0.0682 0.8808 0.0397
-7.250 -0.4093 0.02526 0.01604 -0.0678 0.8707 0.0422
-7.000 -0.3829 0.02430 0.01497 -0.0679 0.8631 0.0457
-6.750 -0.3636 0.02357 0.01421 -0.0667 0.8532 0.0496
-6.500 -0.3407 0.02272 0.01324 -0.0660 0.8459 0.0542
-6.250 -0.3232 0.02211 0.01259 -0.0643 0.8365 0.0607
-6.000 -0.3020 0.02139 0.01184 -0.0633 0.8295 0.0706
-5.750 -0.2854 0.02080 0.01127 -0.0615 0.8210 0.0836
-5.500 -0.2659 0.02014 0.01068 -0.0602 0.8141 0.1044
-5.250 -0.2487 0.01955 0.01022 -0.0585 0.8068 0.1353
-5.000 -0.2324 0.01889 0.00978 -0.0566 0.7995 0.1818
-4.750 -0.2166 0.01811 0.00935 -0.0547 0.7937 0.2559
-4.500 -0.2064 0.01747 0.00913 -0.0517 0.7858 0.3429
-4.250 -0.1911 0.01695 0.00897 -0.0492 0.7799 0.4369
-4.000 -0.1745 0.01673 0.00898 -0.0467 0.7735 0.5080
-3.750 -0.1553 0.01665 0.00899 -0.0447 0.7669 0.5602
-3.500 -0.1321 0.01660 0.00891 -0.0433 0.7619 0.6026
-3.250 -0.1122 0.01663 0.00895 -0.0414 0.7554 0.6354
-3.000 -0.0892 0.01666 0.00896 -0.0400 0.7494 0.6639
-2.750 -0.0636 0.01666 0.00888 -0.0391 0.7447 0.6908
-2.500 -0.0404 0.01675 0.00898 -0.0378 0.7385 0.7142
-2.250 -0.0165 0.01682 0.00900 -0.0366 0.7326 0.7383
-2.000 0.0116 0.01684 0.00893 -0.0361 0.7281 0.7589
-1.750 0.0369 0.01692 0.00898 -0.0354 0.7219 0.7753
-1.500 0.0666 0.01699 0.00899 -0.0355 0.7162 0.7895
-1.250 0.1001 0.01701 0.00891 -0.0364 0.7116 0.8022
-1.000 0.1283 0.01709 0.00895 -0.0363 0.7056 0.8150
-0.750 0.1557 0.01716 0.00895 -0.0362 0.6996 0.8283
-0.500 0.1940 0.01721 0.00891 -0.0380 0.6949 0.8383
-0.250 0.2253 0.01733 0.00899 -0.0387 0.6888 0.8498
0.000 0.2545 0.01741 0.00904 -0.0390 0.6826 0.8624
0.250 0.2966 0.01748 0.00902 -0.0416 0.6778 0.8700
0.500 0.3266 0.01763 0.00915 -0.0422 0.6713 0.8812
0.750 0.3645 0.01775 0.00923 -0.0442 0.6651 0.8892
1.000 0.4008 0.01778 0.00917 -0.0458 0.6603 0.8986
1.250 0.4363 0.01799 0.00940 -0.0475 0.6528 0.9067
1.500 0.4713 0.01807 0.00943 -0.0490 0.6468 0.9156
1.750 0.5096 0.01817 0.00949 -0.0511 0.6408 0.9227
2.000 0.5416 0.01832 0.00966 -0.0522 0.6331 0.9321
2.250 0.5803 0.01832 0.00959 -0.0543 0.6273 0.9395
2.500 0.6121 0.01850 0.00983 -0.0555 0.6187 0.9490
2.750 0.6462 0.01852 0.00979 -0.0568 0.6120 0.9587
3.000 0.6813 0.01864 0.00995 -0.0587 0.6033 0.9670
3.250 0.7175 0.01863 0.00992 -0.0605 0.5960 0.9753
3.500 0.7510 0.01875 0.01008 -0.0621 0.5868 0.9845
3.750 0.7898 0.01866 0.00994 -0.0645 0.5788 0.9915
4.000 0.8265 0.01874 0.01009 -0.0669 0.5682 0.9991
4.250 0.8460 0.01873 0.01005 -0.0656 0.5604 1.0000
4.500 0.8583 0.01886 0.01022 -0.0629 0.5509 1.0000
4.750 0.8736 0.01895 0.01030 -0.0607 0.5424 1.0000
5.000 0.8881 0.01907 0.01043 -0.0584 0.5329 1.0000
5.250 0.9018 0.01925 0.01062 -0.0559 0.5229 1.0000
5.500 0.9194 0.01932 0.01066 -0.0540 0.5136 1.0000
5.750 0.9314 0.01956 0.01095 -0.0512 0.5022 1.0000
6.000 0.9456 0.01976 0.01116 -0.0488 0.4912 1.0000
6.250 0.9613 0.01993 0.01129 -0.0466 0.4803 1.0000
6.500 0.9746 0.02017 0.01156 -0.0440 0.4684 1.0000
6.750 0.9868 0.02045 0.01185 -0.0412 0.4559 1.0000
7.000 0.9995 0.02074 0.01213 -0.0386 0.4437 1.0000
7.250 1.0120 0.02103 0.01240 -0.0359 0.4314 1.0000
7.500 1.0233 0.02136 0.01271 -0.0330 0.4184 1.0000
7.750 1.0321 0.02178 0.01313 -0.0298 0.4051 1.0000
8.000 1.0401 0.02221 0.01356 -0.0265 0.3917 1.0000
8.250 1.0455 0.02266 0.01399 -0.0227 0.3786 1.0000
8.500 1.0504 0.02313 0.01444 -0.0189 0.3663 1.0000
8.750 1.0551 0.02367 0.01493 -0.0152 0.3534 1.0000
9.000 1.0595 0.02429 0.01552 -0.0117 0.3402 1.0000
9.250 1.0639 0.02499 0.01622 -0.0085 0.3271 1.0000
9.500 1.0683 0.02578 0.01700 -0.0054 0.3140 1.0000
9.750 1.0732 0.02663 0.01783 -0.0026 0.3016 1.0000
10.000 1.0783 0.02756 0.01872 0.0000 0.2898 1.0000
10.250 1.0832 0.02856 0.01971 0.0024 0.2782 1.0000
10.500 1.0887 0.02963 0.02080 0.0046 0.2670 1.0000
10.750 1.0940 0.03076 0.02194 0.0066 0.2564 1.0000
11.000 1.0991 0.03196 0.02311 0.0086 0.2465 1.0000
11.250 1.1046 0.03322 0.02443 0.0103 0.2363 1.0000
11.500 1.1099 0.03453 0.02574 0.0119 0.2273 1.0000
11.750 1.1149 0.03592 0.02715 0.0135 0.2182 1.0000
12.000 1.1197 0.03737 0.02866 0.0149 0.2094 1.0000
12.250 1.1237 0.03890 0.03017 0.0162 0.2013 1.0000
12.500 1.1285 0.04048 0.03183 0.0174 0.1930 1.0000
12.750 1.1318 0.04213 0.03346 0.0186 0.1857 1.0000
13.000 1.1359 0.04387 0.03531 0.0196 0.1778 1.0000
13.250 1.1383 0.04568 0.03710 0.0206 0.1711 1.0000
13.500 1.1421 0.04754 0.03908 0.0214 0.1641 1.0000
13.750 1.1440 0.04952 0.04108 0.0222 0.1579 1.0000
14.000 1.1471 0.05151 0.04316 0.0229 0.1517 1.0000
14.250 1.1488 0.05366 0.04538 0.0234 0.1458 1.0000
14.500 1.1508 0.05582 0.04754 0.0239 0.1406 1.0000
14.750 1.1520 0.05820 0.05006 0.0242 0.1348 1.0000
15.000 1.1529 0.06055 0.05243 0.0245 0.1301 1.0000
15.250 1.1545 0.06298 0.05496 0.0247 0.1254 1.0000
15.500 1.1545 0.06565 0.05775 0.0247 0.1207 1.0000
15.750 1.1549 0.06823 0.06035 0.0247 0.1166 1.0000
16.000 1.1552 0.07097 0.06320 0.0246 0.1126 1.0000
16.250 1.1539 0.07399 0.06636 0.0243 0.1086 1.0000
16.500 1.1529 0.07693 0.06936 0.0240 0.1050 1.0000
16.750 1.1537 0.07965 0.07209 0.0237 0.1017 1.0000
17.000 1.1500 0.08322 0.07586 0.0230 0.0985 1.0000
17.250 1.1462 0.08679 0.07955 0.0222 0.0952 1.0000
17.500 1.1449 0.08996 0.08278 0.0215 0.0923 1.0000
17.750 1.1451 0.09293 0.08579 0.0209 0.0897 1.0000
18.000 1.1368 0.09746 0.09053 0.0195 0.0872 1.0000
18.250 1.1291 0.10192 0.09514 0.0180 0.0846 1.0000
18.500 1.1244 0.10588 0.09919 0.0166 0.0822 1.0000
18.750 1.1271 0.10852 0.10182 0.0159 0.0799 1.0000
19.000 1.1176 0.11346 0.10692 0.0140 0.0780 1.0000
19.250 1.0982 0.12039 0.11408 0.0108 0.0762 1.0000
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Polar data table (+)
Polar graphs
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