S4320 (s4320-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4320 (s4320-il) Reynolds number: 200,000 Max Cl/Cd: 84.42 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4320-il-200000.txt Download as CSV file: xf-s4320-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4320
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2673 0.09109 0.08790 -0.0344 1.0000 0.0374
-7.750 -0.2684 0.08880 0.08569 -0.0348 1.0000 0.0386
-7.500 -0.2822 0.08779 0.08482 -0.0325 1.0000 0.0393
-7.250 -0.2792 0.08516 0.08225 -0.0397 0.9889 0.0407
-7.000 -0.2373 0.07805 0.07508 -0.0615 0.9758 0.0414
-6.750 -0.2253 0.07303 0.07010 -0.0582 0.9728 0.0429
-6.500 -0.1996 0.06967 0.06673 -0.0607 0.9662 0.0451
-6.250 -0.1675 0.06479 0.06181 -0.0700 0.9573 0.0487
-5.000 -0.0502 0.04218 0.03848 -0.0986 0.8946 0.0691
-4.750 -0.0305 0.04001 0.03621 -0.0987 0.8847 0.0730
-4.500 -0.0053 0.03588 0.03164 -0.1019 0.8738 0.0822
-4.250 0.0160 0.03394 0.02967 -0.1016 0.8650 0.0861
-4.000 0.0415 0.03115 0.02650 -0.1029 0.8562 0.0970
-3.750 0.0796 0.02400 0.01790 -0.1035 0.8484 0.0533
-3.500 0.1054 0.02079 0.01441 -0.1033 0.8409 0.0492
-3.250 0.1334 0.01859 0.01175 -0.1030 0.8325 0.0464
-3.000 0.1610 0.01714 0.00996 -0.1023 0.8255 0.0459
-2.750 0.1884 0.01621 0.00886 -0.1019 0.8168 0.0472
-2.500 0.2156 0.01554 0.00802 -0.1013 0.8101 0.0501
-2.250 0.2429 0.01481 0.00721 -0.1008 0.8013 0.0514
-2.000 0.2700 0.01413 0.00643 -0.1002 0.7949 0.0533
-1.750 0.2971 0.01344 0.00577 -0.1000 0.7860 0.0584
-1.500 0.3248 0.01301 0.00526 -0.0997 0.7794 0.0696
-1.250 0.3517 0.01189 0.00490 -0.0998 0.7708 0.2559
-1.000 0.3772 0.01120 0.00486 -0.0995 0.7640 0.4680
-0.750 0.3955 0.01038 0.00495 -0.0971 0.7557 0.7495
-0.500 0.4278 0.00995 0.00469 -0.0969 0.7487 1.0000
-0.250 0.4556 0.01004 0.00460 -0.0967 0.7401 1.0000
0.000 0.4833 0.01014 0.00453 -0.0965 0.7323 1.0000
0.250 0.5110 0.01022 0.00445 -0.0963 0.7241 1.0000
0.500 0.5385 0.01032 0.00444 -0.0961 0.7154 1.0000
0.750 0.5663 0.01041 0.00437 -0.0958 0.7078 1.0000
1.000 0.5937 0.01051 0.00440 -0.0956 0.6983 1.0000
1.250 0.6213 0.01061 0.00437 -0.0953 0.6904 1.0000
1.500 0.6487 0.01071 0.00439 -0.0951 0.6810 1.0000
1.750 0.6761 0.01082 0.00443 -0.0949 0.6721 1.0000
2.000 0.7037 0.01092 0.00442 -0.0946 0.6637 1.0000
2.250 0.7309 0.01103 0.00450 -0.0944 0.6535 1.0000
2.500 0.7582 0.01114 0.00454 -0.0941 0.6443 1.0000
2.750 0.7855 0.01123 0.00457 -0.0938 0.6348 1.0000
3.000 0.8125 0.01134 0.00466 -0.0935 0.6237 1.0000
3.250 0.8395 0.01145 0.00474 -0.0933 0.6130 1.0000
3.500 0.8665 0.01156 0.00480 -0.0929 0.6025 1.0000
3.750 0.8933 0.01167 0.00487 -0.0926 0.5910 1.0000
4.000 0.9199 0.01179 0.00499 -0.0923 0.5783 1.0000
4.250 0.9464 0.01192 0.00511 -0.0919 0.5654 1.0000
4.500 0.9727 0.01206 0.00525 -0.0916 0.5519 1.0000
4.750 0.9988 0.01222 0.00539 -0.0912 0.5378 1.0000
5.000 1.0247 0.01238 0.00554 -0.0907 0.5227 1.0000
5.250 1.0504 0.01258 0.00571 -0.0903 0.5068 1.0000
5.500 1.0757 0.01280 0.00591 -0.0898 0.4901 1.0000
5.750 1.1007 0.01305 0.00614 -0.0893 0.4721 1.0000
6.000 1.1253 0.01333 0.00641 -0.0887 0.4527 1.0000
6.250 1.1493 0.01367 0.00669 -0.0881 0.4330 1.0000
6.500 1.1730 0.01404 0.00705 -0.0875 0.4124 1.0000
6.750 1.1961 0.01446 0.00742 -0.0868 0.3915 1.0000
7.000 1.2188 0.01493 0.00784 -0.0860 0.3710 1.0000
7.250 1.2410 0.01542 0.00830 -0.0853 0.3499 1.0000
7.500 1.2623 0.01600 0.00882 -0.0844 0.3303 1.0000
7.750 1.2836 0.01655 0.00938 -0.0836 0.3104 1.0000
8.000 1.3042 0.01717 0.00997 -0.0826 0.2919 1.0000
8.250 1.3239 0.01784 0.01060 -0.0816 0.2746 1.0000
8.500 1.3429 0.01856 0.01127 -0.0805 0.2579 1.0000
8.750 1.3618 0.01925 0.01200 -0.0794 0.2416 1.0000
9.000 1.3798 0.01999 0.01276 -0.0782 0.2262 1.0000
9.250 1.3967 0.02076 0.01354 -0.0768 0.2115 1.0000
9.500 1.4124 0.02159 0.01438 -0.0753 0.1977 1.0000
9.750 1.4267 0.02246 0.01526 -0.0737 0.1845 1.0000
10.000 1.4393 0.02336 0.01619 -0.0719 0.1715 1.0000
10.250 1.4481 0.02428 0.01711 -0.0696 0.1592 1.0000
10.500 1.4557 0.02527 0.01811 -0.0672 0.1476 1.0000
10.750 1.4647 0.02625 0.01917 -0.0652 0.1364 1.0000
11.000 1.4727 0.02738 0.02038 -0.0633 0.1266 1.0000
11.250 1.4787 0.02870 0.02172 -0.0614 0.1173 1.0000
11.500 1.4833 0.03019 0.02322 -0.0597 0.1080 1.0000
11.750 1.4915 0.03152 0.02464 -0.0584 0.0980 1.0000
12.000 1.4979 0.03307 0.02630 -0.0572 0.0888 1.0000
12.250 1.5013 0.03495 0.02823 -0.0559 0.0810 1.0000
12.500 1.5046 0.03697 0.03029 -0.0549 0.0717 1.0000
12.750 1.5061 0.03927 0.03262 -0.0541 0.0593 1.0000
13.000 1.4999 0.04251 0.03582 -0.0532 0.0418 1.0000
13.250 1.4845 0.04694 0.04019 -0.0525 0.0314 1.0000
13.500 1.4739 0.05109 0.04442 -0.0522 0.0260 1.0000
13.750 1.4596 0.05585 0.04925 -0.0524 0.0238 1.0000
14.000 1.4532 0.05983 0.05341 -0.0528 0.0220 1.0000
14.250 1.4454 0.06416 0.05788 -0.0534 0.0203 1.0000
14.500 1.4356 0.06899 0.06283 -0.0545 0.0192 1.0000
14.750 1.4230 0.07443 0.06838 -0.0560 0.0184 1.0000
15.000 1.4101 0.08010 0.07417 -0.0577 0.0177 1.0000
15.250 1.4040 0.08492 0.07917 -0.0592 0.0171 1.0000
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Polar data table (+)
Polar graphs
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