S4233-136-84 (s4233-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 50,000 Max Cl/Cd: 26.14 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4233-il-50000-n5.txt Download as CSV file: xf-s4233-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4233-136-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3451 0.10395 0.09703 -0.0501 1.0000 0.0484
-10.250 -0.3468 0.09982 0.09299 -0.0517 1.0000 0.0477
-10.000 -0.3507 0.09558 0.08885 -0.0533 1.0000 0.0470
-9.750 -0.3572 0.09125 0.08463 -0.0549 1.0000 0.0463
-9.500 -0.3682 0.08669 0.08022 -0.0565 1.0000 0.0456
-9.250 -0.3880 0.08146 0.07513 -0.0582 1.0000 0.0447
-9.000 -0.4231 0.07628 0.07007 -0.0595 1.0000 0.0434
-8.750 -0.4732 0.07320 0.06707 -0.0577 1.0000 0.0426
-8.500 -0.5203 0.06941 0.06307 -0.0571 0.9965 0.0416
-8.250 -0.5149 0.06417 0.05756 -0.0619 0.9853 0.0414
-8.000 -0.5082 0.05934 0.05239 -0.0654 0.9748 0.0413
-7.750 -0.4983 0.05495 0.04756 -0.0680 0.9649 0.0413
-7.500 -0.4833 0.05086 0.04297 -0.0704 0.9565 0.0416
-7.250 -0.4646 0.04795 0.03987 -0.0718 0.9483 0.0430
-7.000 -0.4422 0.04534 0.03698 -0.0733 0.9410 0.0444
-6.750 -0.4197 0.04275 0.03397 -0.0743 0.9334 0.0460
-6.500 -0.3937 0.04017 0.03094 -0.0754 0.9269 0.0473
-6.250 -0.3686 0.03796 0.02831 -0.0757 0.9195 0.0484
-6.000 -0.3336 0.03583 0.02575 -0.0773 0.9150 0.0500
-5.750 -0.3113 0.03440 0.02405 -0.0765 0.9068 0.0517
-5.500 -0.2805 0.03298 0.02258 -0.0775 0.9013 0.0554
-5.250 -0.2570 0.03200 0.02139 -0.0769 0.8937 0.0611
-5.000 -0.2304 0.03084 0.02019 -0.0771 0.8873 0.0676
-4.750 -0.2060 0.02979 0.01901 -0.0767 0.8804 0.0768
-4.500 -0.1837 0.02869 0.01796 -0.0764 0.8729 0.0974
-4.250 -0.1580 0.02700 0.01682 -0.0771 0.8674 0.1764
-4.000 -0.1446 0.02582 0.01654 -0.0759 0.8585 0.3214
-3.750 -0.1198 0.02529 0.01651 -0.0751 0.8533 0.4525
-3.500 -0.1057 0.02536 0.01672 -0.0723 0.8443 0.5224
-3.250 -0.0792 0.02540 0.01671 -0.0712 0.8388 0.5832
-3.000 -0.0621 0.02558 0.01683 -0.0688 0.8305 0.6259
-2.750 -0.0375 0.02566 0.01680 -0.0673 0.8245 0.6662
-2.500 -0.0173 0.02579 0.01683 -0.0653 0.8174 0.7006
-2.250 0.0040 0.02588 0.01682 -0.0635 0.8104 0.7326
-2.000 0.0330 0.02584 0.01664 -0.0626 0.8061 0.7640
-1.750 0.0469 0.02605 0.01676 -0.0600 0.7967 0.7911
-1.500 0.0760 0.02600 0.01657 -0.0594 0.7919 0.8200
-1.250 0.0959 0.02618 0.01667 -0.0579 0.7837 0.8474
-1.000 0.1302 0.02617 0.01652 -0.0586 0.7783 0.8751
-0.750 0.1709 0.02618 0.01637 -0.0607 0.7734 0.9020
-0.500 0.2102 0.02636 0.01642 -0.0633 0.7658 0.9289
-0.250 0.2659 0.02627 0.01615 -0.0686 0.7617 0.9511
0.000 0.3154 0.02640 0.01613 -0.0735 0.7551 0.9746
0.250 0.3666 0.02641 0.01600 -0.0787 0.7489 0.9990
0.500 0.3781 0.02654 0.01601 -0.0767 0.7417 1.0000
1.000 0.4010 0.02715 0.01639 -0.0727 0.7254 1.0000
1.250 0.4185 0.02750 0.01662 -0.0715 0.7175 1.0000
1.500 0.4417 0.02773 0.01675 -0.0710 0.7110 1.0000
1.750 0.4596 0.02819 0.01713 -0.0700 0.7025 1.0000
2.000 0.4924 0.02814 0.01699 -0.0705 0.6983 1.0000
2.500 0.5362 0.02890 0.01765 -0.0693 0.6832 1.0000
2.750 0.5477 0.02974 0.01847 -0.0676 0.6725 1.0000
3.000 0.5811 0.02967 0.01836 -0.0681 0.6681 1.0000
3.250 0.5926 0.03057 0.01926 -0.0664 0.6574 1.0000
3.500 0.6263 0.03048 0.01916 -0.0669 0.6529 1.0000
3.750 0.6374 0.03144 0.02014 -0.0653 0.6420 1.0000
4.000 0.6719 0.03128 0.01999 -0.0657 0.6376 1.0000
4.250 0.6822 0.03231 0.02106 -0.0640 0.6264 1.0000
4.500 0.7179 0.03206 0.02086 -0.0645 0.6221 1.0000
5.000 0.7483 0.03369 0.02259 -0.0620 0.6024 1.0000
5.250 0.7720 0.03403 0.02302 -0.0614 0.5945 1.0000
5.500 0.7868 0.03488 0.02394 -0.0601 0.5846 1.0000
5.750 0.8177 0.03481 0.02395 -0.0601 0.5784 1.0000
6.000 0.8279 0.03592 0.02514 -0.0584 0.5673 1.0000
6.250 0.8645 0.03548 0.02484 -0.0587 0.5621 1.0000
6.500 0.8713 0.03676 0.02621 -0.0568 0.5502 1.0000
7.000 0.9171 0.03737 0.02708 -0.0552 0.5332 1.0000
7.250 0.9236 0.03860 0.02842 -0.0531 0.5215 1.0000
7.500 0.9681 0.03758 0.02757 -0.0539 0.5162 1.0000
7.750 0.9702 0.03901 0.02911 -0.0514 0.5035 1.0000
8.000 0.9779 0.04022 0.03046 -0.0495 0.4917 1.0000
8.250 1.0057 0.04003 0.03043 -0.0488 0.4827 1.0000
8.500 1.0304 0.03999 0.03056 -0.0479 0.4725 1.0000
8.750 1.0376 0.04118 0.03189 -0.0460 0.4597 1.0000
9.000 1.0504 0.04195 0.03283 -0.0445 0.4472 1.0000
9.250 1.0694 0.04218 0.03322 -0.0431 0.4349 1.0000
9.500 1.0906 0.04213 0.03333 -0.0418 0.4218 1.0000
9.750 1.1077 0.04237 0.03371 -0.0403 0.4074 1.0000
10.000 1.1197 0.04300 0.03448 -0.0386 0.3918 1.0000
10.250 1.1290 0.04386 0.03550 -0.0369 0.3754 1.0000
10.500 1.1378 0.04477 0.03652 -0.0352 0.3580 1.0000
10.750 1.1480 0.04554 0.03737 -0.0335 0.3396 1.0000
11.000 1.1562 0.04652 0.03840 -0.0319 0.3201 1.0000
11.250 1.1547 0.04859 0.04057 -0.0305 0.3002 1.0000
11.500 1.1587 0.05004 0.04201 -0.0290 0.2785 1.0000
11.750 1.1555 0.05250 0.04451 -0.0280 0.2568 1.0000
12.000 1.1546 0.05472 0.04669 -0.0269 0.2348 1.0000
12.250 1.1498 0.05765 0.04963 -0.0262 0.2134 1.0000
12.500 1.1449 0.06063 0.05252 -0.0257 0.1926 1.0000
12.750 1.1387 0.06403 0.05587 -0.0254 0.1730 1.0000
13.000 1.1314 0.06773 0.05950 -0.0254 0.1545 1.0000
13.250 1.1237 0.07162 0.06328 -0.0257 0.1380 1.0000
13.500 1.1157 0.07573 0.06729 -0.0262 0.1233 1.0000
13.750 1.1082 0.07998 0.07147 -0.0269 0.1100 1.0000
14.000 1.1009 0.08440 0.07586 -0.0278 0.0977 1.0000
14.250 1.0951 0.08876 0.08024 -0.0288 0.0871 1.0000
14.500 1.0899 0.09313 0.08464 -0.0299 0.0780 1.0000
14.750 1.0862 0.09729 0.08875 -0.0309 0.0711 1.0000
15.000 1.0839 0.10142 0.09300 -0.0319 0.0646 1.0000
15.250 1.0832 0.10525 0.09686 -0.0328 0.0599 1.0000
15.500 1.0824 0.10936 0.10115 -0.0339 0.0552 1.0000
15.750 1.0837 0.11283 0.10458 -0.0348 0.0518 1.0000
16.000 1.0835 0.11711 0.10909 -0.0361 0.0491 1.0000
16.250 1.0810 0.12189 0.11411 -0.0379 0.0467 1.0000
16.500 1.0792 0.12644 0.11880 -0.0398 0.0445 1.0000
16.750 1.0814 0.13005 0.12244 -0.0411 0.0428 1.0000
17.000 1.0790 0.13501 0.12754 -0.0433 0.0418 1.0000
17.250 1.0688 0.14215 0.13496 -0.0471 0.0413 1.0000
17.500 1.0535 0.15092 0.14399 -0.0521 0.0411 1.0000
17.750 1.0359 0.16090 0.15416 -0.0581 0.0411 1.0000
18.000 1.0157 0.17256 0.16593 -0.0651 0.0413 1.0000
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Polar data table (+)
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