S1091 (s1091-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.69 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1091-il-1000000-n5.txt Download as CSV file: xf-s1091-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1091
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1585 0.08529 0.08371 -0.0420 0.9895 0.0042
-8.250 -0.1482 0.08201 0.08043 -0.0438 0.9883 0.0043
-8.000 -0.1371 0.07856 0.07698 -0.0459 0.9870 0.0044
-7.750 -0.1254 0.07513 0.07356 -0.0481 0.9859 0.0045
-7.500 -0.1130 0.07157 0.07001 -0.0506 0.9848 0.0046
-7.250 -0.1080 0.06881 0.06725 -0.0509 0.9806 0.0046
-7.000 -0.0979 0.06559 0.06405 -0.0527 0.9773 0.0047
-6.750 -0.0853 0.06214 0.06060 -0.0552 0.9744 0.0047
-6.500 -0.0781 0.05924 0.05771 -0.0562 0.9681 0.0047
-6.000 -0.0575 0.05306 0.05154 -0.0600 0.9510 0.0048
-5.750 -0.0369 0.04920 0.04767 -0.0647 0.9422 0.0050
-5.500 -0.0056 0.04465 0.04308 -0.0721 0.9335 0.0050
-5.250 0.0316 0.03983 0.03821 -0.0810 0.9194 0.0052
-5.000 0.0657 0.03560 0.03384 -0.0885 0.8908 0.0055
-4.750 0.0869 0.03252 0.03059 -0.0922 0.8534 0.0057
-4.500 0.1058 0.02979 0.02771 -0.0949 0.8213 0.0059
-4.250 0.1277 0.02695 0.02474 -0.0982 0.7963 0.0061
-4.000 0.1532 0.02395 0.02162 -0.1023 0.7749 0.0062
-3.750 0.1797 0.02105 0.01861 -0.1060 0.7557 0.0062
-3.500 0.2077 0.01829 0.01572 -0.1097 0.7370 0.0062
-3.250 0.2386 0.01549 0.01280 -0.1137 0.7232 0.0062
-3.000 0.2715 0.01279 0.00996 -0.1180 0.7098 0.0062
-2.750 0.3351 0.02542 0.02224 -0.1356 0.7311 0.0038
-2.500 0.3731 0.02049 0.01698 -0.1393 0.7172 0.0037
-2.250 0.4119 0.01197 0.00749 -0.1419 0.7067 0.0037
-2.000 0.4396 0.00972 0.00463 -0.1416 0.6938 0.0042
-1.750 0.4661 0.00933 0.00408 -0.1412 0.6814 0.0045
-1.500 0.4927 0.00900 0.00359 -0.1408 0.6696 0.0050
-1.250 0.5193 0.00861 0.00304 -0.1403 0.6586 0.0053
-1.000 0.5460 0.00834 0.00265 -0.1398 0.6479 0.0058
-0.750 0.5728 0.00828 0.00252 -0.1394 0.6376 0.0063
-0.500 0.5994 0.00787 0.00199 -0.1389 0.6267 0.0065
-0.250 0.6259 0.00766 0.00168 -0.1384 0.6155 0.0066
0.000 0.6524 0.00752 0.00145 -0.1379 0.6025 0.0069
0.250 0.6788 0.00746 0.00131 -0.1374 0.5881 0.0076
0.500 0.7051 0.00745 0.00121 -0.1369 0.5723 0.0096
0.750 0.7313 0.00745 0.00115 -0.1364 0.5533 0.0170
1.000 0.7567 0.00740 0.00117 -0.1358 0.5279 0.0790
1.250 0.7814 0.00753 0.00123 -0.1351 0.4908 0.1215
1.500 0.8059 0.00770 0.00133 -0.1344 0.4547 0.1668
1.750 0.8303 0.00786 0.00146 -0.1337 0.4183 0.2321
2.000 0.8548 0.00809 0.00159 -0.1330 0.3841 0.2680
2.250 0.8797 0.00828 0.00172 -0.1323 0.3556 0.3081
2.500 0.9043 0.00848 0.00188 -0.1317 0.3263 0.3602
2.750 0.9287 0.00870 0.00206 -0.1310 0.2947 0.4180
3.000 0.9533 0.00889 0.00224 -0.1304 0.2694 0.4815
3.250 0.9718 0.00833 0.00243 -0.1285 0.2523 0.8913
3.500 1.0051 0.00854 0.00259 -0.1298 0.2262 1.0000
3.750 1.0292 0.00888 0.00279 -0.1291 0.1984 1.0000
4.000 1.0537 0.00918 0.00298 -0.1284 0.1770 1.0000
4.250 1.0781 0.00949 0.00317 -0.1277 0.1589 1.0000
4.500 1.1026 0.00977 0.00337 -0.1270 0.1431 1.0000
4.750 1.1270 0.01006 0.00358 -0.1263 0.1289 1.0000
5.000 1.1514 0.01035 0.00382 -0.1257 0.1161 1.0000
5.250 1.1757 0.01065 0.00405 -0.1250 0.1048 1.0000
5.500 1.2001 0.01092 0.00427 -0.1243 0.0956 1.0000
5.750 1.2244 0.01120 0.00451 -0.1236 0.0875 1.0000
6.000 1.2481 0.01153 0.00480 -0.1229 0.0782 1.0000
6.250 1.2724 0.01180 0.00505 -0.1222 0.0726 1.0000
6.500 1.2960 0.01212 0.00534 -0.1214 0.0663 1.0000
6.750 1.3202 0.01238 0.00560 -0.1208 0.0632 1.0000
7.000 1.3439 0.01268 0.00591 -0.1200 0.0595 1.0000
7.250 1.3672 0.01301 0.00623 -0.1192 0.0557 1.0000
7.500 1.3909 0.01329 0.00654 -0.1185 0.0537 1.0000
7.750 1.4144 0.01358 0.00685 -0.1177 0.0522 1.0000
8.000 1.4375 0.01389 0.00720 -0.1169 0.0506 1.0000
8.250 1.4603 0.01423 0.00757 -0.1161 0.0488 1.0000
8.500 1.4826 0.01460 0.00796 -0.1151 0.0470 1.0000
8.750 1.5045 0.01501 0.00839 -0.1141 0.0448 1.0000
9.000 1.5267 0.01536 0.00879 -0.1132 0.0433 1.0000
9.250 1.5491 0.01566 0.00915 -0.1124 0.0420 1.0000
9.500 1.5708 0.01603 0.00954 -0.1114 0.0394 1.0000
9.750 1.5911 0.01651 0.00999 -0.1102 0.0354 1.0000
10.000 1.6119 0.01691 0.01044 -0.1091 0.0333 1.0000
10.250 1.6323 0.01734 0.01089 -0.1080 0.0301 1.0000
10.500 1.6506 0.01793 0.01146 -0.1066 0.0254 1.0000
10.750 1.6668 0.01868 0.01217 -0.1048 0.0179 1.0000
11.000 1.6766 0.01996 0.01339 -0.1021 0.0078 1.0000
11.250 1.6852 0.02120 0.01465 -0.0991 0.0024 1.0000
11.500 1.6949 0.02215 0.01567 -0.0962 0.0011 1.0000
11.750 1.7049 0.02304 0.01665 -0.0934 0.0007 1.0000
12.000 1.7151 0.02388 0.01759 -0.0907 0.0006 1.0000
12.250 1.7244 0.02480 0.01861 -0.0880 0.0005 1.0000
12.500 1.7321 0.02585 0.01977 -0.0853 0.0004 1.0000
12.750 1.7381 0.02705 0.02111 -0.0824 0.0003 1.0000
13.000 1.7429 0.02839 0.02257 -0.0795 0.0002 1.0000
13.250 1.7497 0.02957 0.02385 -0.0771 0.0002 1.0000
13.500 1.7547 0.03094 0.02533 -0.0747 0.0002 1.0000
13.750 1.7589 0.03244 0.02694 -0.0724 0.0002 1.0000
14.000 1.7613 0.03417 0.02880 -0.0702 0.0002 1.0000
14.250 1.7620 0.03615 0.03091 -0.0682 0.0002 1.0000
14.500 1.7623 0.03826 0.03315 -0.0664 0.0002 1.0000
14.750 1.7605 0.04073 0.03575 -0.0649 0.0002 1.0000
15.000 1.7580 0.04342 0.03858 -0.0637 0.0002 1.0000
15.250 1.7540 0.04645 0.04174 -0.0628 0.0001 1.0000
15.500 1.7477 0.04996 0.04540 -0.0624 0.0001 1.0000
15.750 1.7409 0.05370 0.04929 -0.0623 0.0001 1.0000
16.000 1.7306 0.05818 0.05392 -0.0627 0.0001 1.0000
16.250 1.7206 0.06287 0.05877 -0.0636 0.0001 1.0000
16.500 1.7083 0.06818 0.06423 -0.0650 0.0001 1.0000
16.750 1.6922 0.07446 0.07068 -0.0672 0.0001 1.0000
17.000 1.6746 0.08143 0.07782 -0.0700 0.0001 1.0000
17.250 1.6560 0.08902 0.08557 -0.0735 0.0001 1.0000
17.500 1.6317 0.09822 0.09495 -0.0782 0.0001 1.0000
17.750 1.6070 0.10795 0.10486 -0.0833 0.0001 1.0000
18.000 1.5775 0.11912 0.11619 -0.0895 0.0001 1.0000
18.250 1.5452 0.13135 0.12860 -0.0966 0.0001 1.0000
18.500 1.5116 0.14424 0.14167 -0.1042 0.0001 1.0000
18.750 1.4772 0.15779 0.15538 -0.1124 0.0002 1.0000
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