S2091-101-83 (s2091-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 200,000 Max Cl/Cd: 76.35 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2091-il-200000-n5.txt Download as CSV file: xf-s2091-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2091-101-83
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3328 0.08790 0.08447 -0.0335 1.0000 0.0167
-8.500 -0.3334 0.08382 0.08045 -0.0355 1.0000 0.0166
-8.250 -0.3359 0.07990 0.07660 -0.0373 1.0000 0.0167
-8.000 -0.3381 0.07571 0.07248 -0.0399 0.9925 0.0165
-7.750 -0.3264 0.06913 0.06591 -0.0489 0.9645 0.0167
-7.500 -0.3136 0.06069 0.05742 -0.0615 0.9444 0.0171
-7.250 -0.3110 0.04723 0.04372 -0.0769 0.9219 0.0173
-7.000 -0.3243 0.02832 0.02329 -0.0870 0.9029 0.0180
-6.750 -0.3069 0.02396 0.01804 -0.0874 0.8931 0.0188
-6.500 -0.2841 0.02263 0.01654 -0.0871 0.8845 0.0194
-6.250 -0.2602 0.02141 0.01509 -0.0868 0.8757 0.0203
-6.000 -0.2360 0.02013 0.01350 -0.0863 0.8680 0.0216
-5.750 -0.2108 0.01892 0.01197 -0.0860 0.8592 0.0235
-5.500 -0.1857 0.01829 0.01125 -0.0856 0.8519 0.0250
-5.250 -0.1597 0.01742 0.01021 -0.0853 0.8431 0.0266
-5.000 -0.1339 0.01660 0.00915 -0.0847 0.8360 0.0286
-4.750 -0.1075 0.01608 0.00861 -0.0845 0.8271 0.0309
-4.500 -0.0813 0.01550 0.00787 -0.0840 0.8200 0.0333
-4.250 -0.0545 0.01490 0.00719 -0.0838 0.8112 0.0360
-4.000 -0.0279 0.01450 0.00672 -0.0834 0.8039 0.0392
-3.750 -0.0008 0.01404 0.00614 -0.0831 0.7950 0.0423
-3.500 0.0260 0.01362 0.00570 -0.0828 0.7875 0.0470
-3.250 0.0533 0.01327 0.00527 -0.0825 0.7787 0.0527
-3.000 0.0805 0.01291 0.00488 -0.0823 0.7709 0.0600
-2.750 0.1078 0.01262 0.00456 -0.0821 0.7621 0.0698
-2.500 0.1353 0.01237 0.00428 -0.0818 0.7539 0.0810
-2.250 0.1627 0.01214 0.00403 -0.0816 0.7452 0.0952
-2.000 0.1902 0.01192 0.00383 -0.0815 0.7365 0.1149
-1.750 0.2176 0.01168 0.00363 -0.0813 0.7279 0.1416
-1.500 0.2451 0.01143 0.00348 -0.0812 0.7185 0.1807
-1.250 0.2722 0.01116 0.00334 -0.0810 0.7099 0.2380
-1.000 0.2992 0.01086 0.00326 -0.0809 0.7001 0.3174
-0.750 0.3260 0.01057 0.00321 -0.0807 0.6907 0.4065
-0.500 0.3520 0.01028 0.00317 -0.0803 0.6813 0.5075
-0.250 0.3771 0.00997 0.00319 -0.0795 0.6711 0.6177
0.000 0.3994 0.00960 0.00319 -0.0778 0.6616 0.7490
0.250 0.4367 0.00919 0.00305 -0.0788 0.6510 1.0000
0.500 0.4642 0.00928 0.00301 -0.0787 0.6400 1.0000
0.750 0.4917 0.00937 0.00298 -0.0785 0.6293 1.0000
1.000 0.5190 0.00948 0.00296 -0.0782 0.6185 1.0000
1.250 0.5464 0.00959 0.00297 -0.0780 0.6066 1.0000
1.500 0.5738 0.00971 0.00300 -0.0778 0.5949 1.0000
1.750 0.6010 0.00984 0.00303 -0.0776 0.5832 1.0000
2.000 0.6282 0.00998 0.00307 -0.0774 0.5715 1.0000
2.250 0.6553 0.01013 0.00314 -0.0771 0.5590 1.0000
2.500 0.6824 0.01028 0.00322 -0.0769 0.5462 1.0000
2.750 0.7093 0.01044 0.00331 -0.0767 0.5334 1.0000
3.000 0.7362 0.01062 0.00343 -0.0765 0.5205 1.0000
3.250 0.7629 0.01081 0.00355 -0.0762 0.5075 1.0000
3.500 0.7894 0.01101 0.00368 -0.0759 0.4940 1.0000
3.750 0.8158 0.01122 0.00384 -0.0756 0.4804 1.0000
4.000 0.8421 0.01144 0.00401 -0.0753 0.4664 1.0000
4.250 0.8683 0.01167 0.00419 -0.0751 0.4523 1.0000
4.500 0.8943 0.01192 0.00441 -0.0747 0.4381 1.0000
4.750 0.9201 0.01218 0.00463 -0.0744 0.4239 1.0000
5.000 0.9458 0.01245 0.00486 -0.0741 0.4095 1.0000
5.250 0.9712 0.01275 0.00512 -0.0737 0.3951 1.0000
5.500 0.9964 0.01305 0.00541 -0.0733 0.3806 1.0000
5.750 1.0213 0.01338 0.00570 -0.0729 0.3660 1.0000
6.000 1.0459 0.01372 0.00602 -0.0724 0.3513 1.0000
6.250 1.0703 0.01408 0.00636 -0.0720 0.3366 1.0000
6.500 1.0944 0.01446 0.00672 -0.0715 0.3219 1.0000
6.750 1.1181 0.01486 0.00710 -0.0709 0.3072 1.0000
7.000 1.1414 0.01528 0.00751 -0.0703 0.2925 1.0000
7.250 1.1644 0.01573 0.00795 -0.0697 0.2779 1.0000
7.500 1.1869 0.01619 0.00840 -0.0691 0.2633 1.0000
7.750 1.2089 0.01669 0.00888 -0.0683 0.2487 1.0000
8.000 1.2304 0.01721 0.00941 -0.0676 0.2340 1.0000
8.250 1.2513 0.01776 0.00994 -0.0667 0.2195 1.0000
8.500 1.2716 0.01833 0.01052 -0.0658 0.2051 1.0000
8.750 1.2912 0.01894 0.01112 -0.0648 0.1910 1.0000
9.000 1.3100 0.01958 0.01177 -0.0638 0.1775 1.0000
9.250 1.3278 0.02027 0.01246 -0.0626 0.1639 1.0000
9.500 1.3445 0.02100 0.01319 -0.0613 0.1508 1.0000
9.750 1.3597 0.02179 0.01397 -0.0598 0.1376 1.0000
10.000 1.3728 0.02263 0.01482 -0.0581 0.1253 1.0000
10.250 1.3830 0.02354 0.01572 -0.0560 0.1138 1.0000
10.500 1.3924 0.02453 0.01672 -0.0539 0.1030 1.0000
10.750 1.4015 0.02558 0.01780 -0.0520 0.0934 1.0000
11.000 1.4095 0.02677 0.01901 -0.0501 0.0850 1.0000
11.250 1.4155 0.02815 0.02040 -0.0483 0.0775 1.0000
11.500 1.4231 0.02949 0.02183 -0.0468 0.0708 1.0000
11.750 1.4281 0.03109 0.02347 -0.0453 0.0652 1.0000
12.000 1.4337 0.03272 0.02516 -0.0440 0.0598 1.0000
12.250 1.4364 0.03467 0.02716 -0.0427 0.0557 1.0000
12.500 1.4416 0.03649 0.02910 -0.0417 0.0519 1.0000
12.750 1.4434 0.03869 0.03136 -0.0408 0.0483 1.0000
13.000 1.4442 0.04111 0.03386 -0.0401 0.0458 1.0000
13.250 1.4469 0.04341 0.03631 -0.0396 0.0432 1.0000
13.500 1.4470 0.04607 0.03907 -0.0392 0.0408 1.0000
13.750 1.4439 0.04921 0.04228 -0.0391 0.0389 1.0000
14.000 1.4424 0.05228 0.04548 -0.0392 0.0372 1.0000
14.250 1.4413 0.05540 0.04875 -0.0394 0.0355 1.0000
14.500 1.4387 0.05883 0.05231 -0.0398 0.0340 1.0000
14.750 1.4342 0.06264 0.05623 -0.0406 0.0328 1.0000
15.000 1.4273 0.06695 0.06063 -0.0416 0.0316 1.0000
15.250 1.4207 0.07135 0.06514 -0.0429 0.0306 1.0000
15.500 1.4173 0.07543 0.06938 -0.0440 0.0295 1.0000
15.750 1.4124 0.07983 0.07394 -0.0455 0.0284 1.0000
16.000 1.4068 0.08450 0.07874 -0.0471 0.0274 1.0000
16.250 1.4001 0.08947 0.08384 -0.0491 0.0266 1.0000
16.500 1.3923 0.09468 0.08916 -0.0512 0.0259 1.0000
16.750 1.3835 0.10016 0.09474 -0.0535 0.0253 1.0000
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Polar data table (+)
Polar graphs
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