S4083 (8%) (s4083-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 200,000 Max Cl/Cd: 73.3 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4083-il-200000.txt Download as CSV file: xf-s4083-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4083 (8%)
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3703 0.08747 0.08414 -0.0181 1.0000 0.0354
-7.000 -0.3735 0.08497 0.08170 -0.0179 1.0000 0.0363
-6.750 -0.3730 0.08205 0.07885 -0.0190 1.0000 0.0372
-6.500 -0.3696 0.07874 0.07558 -0.0218 1.0000 0.0385
-6.250 -0.3588 0.07472 0.07158 -0.0298 1.0000 0.0400
-6.000 -0.3419 0.07020 0.06699 -0.0376 1.0000 0.0406
-5.750 -0.3272 0.06597 0.06265 -0.0417 1.0000 0.0408
-5.500 -0.3280 0.06012 0.05691 -0.0410 1.0000 0.0419
-5.250 -0.3210 0.05772 0.05455 -0.0391 1.0000 0.0430
-5.000 -0.3095 0.05502 0.05186 -0.0390 1.0000 0.0445
-4.750 -0.2942 0.05176 0.04854 -0.0405 1.0000 0.0468
-4.500 -0.2722 0.04763 0.04426 -0.0439 1.0000 0.0505
-4.250 -0.2445 0.04160 0.03777 -0.0491 1.0000 0.0549
-4.000 -0.2307 0.03934 0.03559 -0.0483 1.0000 0.0569
-3.750 -0.2126 0.03710 0.03327 -0.0483 1.0000 0.0605
-3.500 -0.1684 0.03290 0.02867 -0.0539 0.9960 0.0709
-3.250 -0.1250 0.03006 0.02561 -0.0586 0.9904 0.0854
-3.000 -0.0802 0.02725 0.02252 -0.0630 0.9849 0.0996
-2.750 -0.0294 0.01933 0.01303 -0.0633 0.9814 0.0371
-2.500 0.0144 0.01685 0.01006 -0.0657 0.9754 0.0343
-2.250 0.0553 0.01518 0.00815 -0.0677 0.9663 0.0343
-2.000 0.0966 0.01388 0.00676 -0.0698 0.9565 0.0369
-1.750 0.1381 0.01270 0.00557 -0.0721 0.9455 0.0450
-1.500 0.1782 0.01140 0.00435 -0.0740 0.9316 0.0816
-1.250 0.2151 0.00950 0.00398 -0.0764 0.9138 0.4664
-1.000 0.2724 0.00795 0.00368 -0.0813 0.8960 1.0000
-0.750 0.3297 0.00781 0.00317 -0.0870 0.8588 1.0000
-0.250 0.4077 0.00811 0.00269 -0.0907 0.7570 1.0000
0.000 0.4336 0.00840 0.00263 -0.0899 0.7161 1.0000
0.250 0.4584 0.00869 0.00262 -0.0890 0.6826 1.0000
0.500 0.4830 0.00896 0.00264 -0.0881 0.6546 1.0000
0.750 0.5079 0.00923 0.00268 -0.0873 0.6307 1.0000
1.000 0.5329 0.00949 0.00275 -0.0865 0.6099 1.0000
1.250 0.5582 0.00975 0.00283 -0.0859 0.5918 1.0000
1.500 0.5837 0.00999 0.00293 -0.0852 0.5746 1.0000
1.750 0.6092 0.01023 0.00304 -0.0847 0.5590 1.0000
2.000 0.6349 0.01048 0.00319 -0.0841 0.5448 1.0000
2.250 0.6606 0.01072 0.00333 -0.0835 0.5314 1.0000
2.500 0.6863 0.01097 0.00348 -0.0830 0.5188 1.0000
3.000 0.7377 0.01145 0.00385 -0.0820 0.4946 1.0000
3.250 0.7634 0.01169 0.00405 -0.0815 0.4830 1.0000
3.500 0.7891 0.01194 0.00426 -0.0810 0.4722 1.0000
3.750 0.8149 0.01222 0.00448 -0.0805 0.4621 1.0000
4.000 0.8405 0.01246 0.00471 -0.0800 0.4515 1.0000
4.250 0.8660 0.01270 0.00500 -0.0794 0.4408 1.0000
4.500 0.8914 0.01297 0.00526 -0.0789 0.4305 1.0000
4.750 0.9168 0.01325 0.00550 -0.0783 0.4204 1.0000
5.000 0.9418 0.01347 0.00577 -0.0777 0.4094 1.0000
5.250 0.9667 0.01373 0.00610 -0.0771 0.3986 1.0000
5.500 0.9916 0.01400 0.00640 -0.0765 0.3881 1.0000
5.750 1.0163 0.01428 0.00669 -0.0758 0.3774 1.0000
6.000 1.0406 0.01453 0.00698 -0.0751 0.3656 1.0000
6.250 1.0646 0.01476 0.00732 -0.0743 0.3530 1.0000
6.500 1.0884 0.01501 0.00765 -0.0735 0.3404 1.0000
6.750 1.1121 0.01528 0.00799 -0.0727 0.3273 1.0000
7.000 1.1353 0.01554 0.00833 -0.0718 0.3131 1.0000
7.250 1.1580 0.01581 0.00870 -0.0708 0.2976 1.0000
7.500 1.1798 0.01612 0.00903 -0.0697 0.2799 1.0000
7.750 1.2014 0.01639 0.00938 -0.0686 0.2566 1.0000
8.000 1.2218 0.01679 0.00977 -0.0674 0.2285 1.0000
8.250 1.2410 0.01737 0.01027 -0.0661 0.1959 1.0000
8.500 1.2587 0.01820 0.01095 -0.0647 0.1592 1.0000
8.750 1.2758 0.01914 0.01183 -0.0632 0.1263 1.0000
9.000 1.2889 0.02053 0.01299 -0.0613 0.0832 1.0000
9.250 1.2871 0.02343 0.01543 -0.0572 0.0342 1.0000
9.500 1.2921 0.02538 0.01748 -0.0539 0.0267 1.0000
9.750 1.2994 0.02694 0.01921 -0.0510 0.0238 1.0000
10.000 1.3069 0.02835 0.02074 -0.0483 0.0215 1.0000
10.250 1.3082 0.02994 0.02242 -0.0448 0.0198 1.0000
10.500 1.3043 0.03195 0.02452 -0.0409 0.0190 1.0000
10.750 1.2974 0.03453 0.02721 -0.0371 0.0183 1.0000
11.000 1.2994 0.03656 0.02938 -0.0346 0.0179 1.0000
11.250 1.3025 0.03867 0.03164 -0.0325 0.0176 1.0000
11.500 1.3057 0.04099 0.03416 -0.0307 0.0172 1.0000
11.750 1.3088 0.04354 0.03688 -0.0291 0.0170 1.0000
12.000 1.3111 0.04631 0.03984 -0.0277 0.0168 1.0000
12.250 1.3116 0.04938 0.04312 -0.0266 0.0165 1.0000
12.500 1.3103 0.05274 0.04671 -0.0257 0.0165 1.0000
12.750 1.3063 0.05641 0.05062 -0.0254 0.0165 1.0000
13.000 1.2991 0.06057 0.05502 -0.0255 0.0165 1.0000
13.250 1.2897 0.06513 0.05983 -0.0262 0.0166 1.0000
13.500 1.2782 0.07012 0.06505 -0.0276 0.0167 1.0000
13.750 1.2649 0.07557 0.07073 -0.0296 0.0167 1.0000
14.000 1.2501 0.08150 0.07688 -0.0322 0.0169 1.0000
14.250 1.2337 0.08794 0.08352 -0.0354 0.0170 1.0000
14.500 1.2165 0.09479 0.09057 -0.0391 0.0171 1.0000
14.750 1.1987 0.10209 0.09805 -0.0433 0.0172 1.0000
15.000 1.1802 0.10992 0.10605 -0.0481 0.0174 1.0000
15.250 1.1617 0.11824 0.11452 -0.0533 0.0175 1.0000
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Polar data table (+)
Polar graphs
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