S2046 (s2046-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 200,000 Max Cl/Cd: 70.61 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2046-il-200000-n5.txt Download as CSV file: xf-s2046-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2046
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4850 0.08047 0.07675 -0.0360 1.0000 0.0170
-9.250 -0.4952 0.07473 0.07106 -0.0387 1.0000 0.0169
-9.000 -0.5101 0.06843 0.06484 -0.0418 1.0000 0.0168
-8.500 -0.5745 0.04564 0.04186 -0.0604 1.0000 0.0161
-8.250 -0.5865 0.03863 0.03437 -0.0636 1.0000 0.0161
-8.000 -0.5844 0.03352 0.02872 -0.0648 1.0000 0.0162
-7.750 -0.5738 0.02982 0.02451 -0.0651 1.0000 0.0164
-7.500 -0.5583 0.02708 0.02132 -0.0650 1.0000 0.0167
-7.250 -0.5286 0.02470 0.01847 -0.0670 0.9973 0.0170
-7.000 -0.4969 0.02271 0.01627 -0.0693 0.9943 0.0180
-6.750 -0.4652 0.02153 0.01493 -0.0710 0.9908 0.0189
-6.500 -0.4328 0.02018 0.01337 -0.0726 0.9872 0.0197
-6.250 -0.3994 0.01887 0.01185 -0.0743 0.9843 0.0203
-6.000 -0.3671 0.01775 0.01055 -0.0756 0.9808 0.0210
-5.750 -0.3355 0.01680 0.00945 -0.0767 0.9765 0.0219
-5.500 -0.3019 0.01588 0.00842 -0.0782 0.9730 0.0230
-5.250 -0.2668 0.01514 0.00763 -0.0800 0.9703 0.0250
-5.000 -0.2358 0.01458 0.00698 -0.0809 0.9652 0.0277
-4.750 -0.2026 0.01400 0.00640 -0.0822 0.9610 0.0335
-4.500 -0.1675 0.01343 0.00583 -0.0838 0.9578 0.0441
-4.250 -0.1341 0.01301 0.00541 -0.0851 0.9538 0.0579
-4.000 -0.1032 0.01270 0.00508 -0.0858 0.9479 0.0703
-3.750 -0.0695 0.01239 0.00483 -0.0871 0.9437 0.0894
-3.500 -0.0370 0.01206 0.00457 -0.0882 0.9389 0.1094
-3.250 -0.0062 0.01176 0.00428 -0.0888 0.9325 0.1274
-3.000 0.0275 0.01142 0.00399 -0.0900 0.9280 0.1501
-2.750 0.0574 0.01109 0.00376 -0.0905 0.9209 0.1835
-2.500 0.0893 0.01066 0.00353 -0.0914 0.9149 0.2447
-2.250 0.1191 0.01016 0.00338 -0.0920 0.9074 0.3436
-2.000 0.1495 0.00979 0.00331 -0.0924 0.8997 0.4410
-1.750 0.1774 0.00962 0.00327 -0.0922 0.8890 0.5007
-1.500 0.2056 0.00950 0.00321 -0.0919 0.8781 0.5414
-1.250 0.2337 0.00942 0.00316 -0.0915 0.8672 0.5731
-1.000 0.2615 0.00935 0.00311 -0.0911 0.8561 0.5992
-0.750 0.2887 0.00930 0.00307 -0.0906 0.8443 0.6230
-0.500 0.3158 0.00926 0.00306 -0.0901 0.8328 0.6500
-0.250 0.3425 0.00922 0.00307 -0.0894 0.8213 0.6796
0.000 0.3691 0.00919 0.00307 -0.0887 0.8094 0.7056
0.250 0.3958 0.00917 0.00306 -0.0881 0.7969 0.7250
0.500 0.4225 0.00916 0.00305 -0.0875 0.7833 0.7404
0.750 0.4492 0.00915 0.00304 -0.0869 0.7689 0.7552
1.000 0.4757 0.00916 0.00304 -0.0863 0.7536 0.7703
1.250 0.5019 0.00916 0.00304 -0.0856 0.7369 0.7860
1.500 0.5276 0.00917 0.00306 -0.0848 0.7186 0.8031
1.750 0.5530 0.00919 0.00307 -0.0840 0.6985 0.8220
2.000 0.5781 0.00921 0.00308 -0.0830 0.6766 0.8441
2.250 0.6024 0.00922 0.00308 -0.0819 0.6521 0.8743
2.500 0.6313 0.00919 0.00307 -0.0817 0.6231 0.9602
2.750 0.6581 0.00941 0.00314 -0.0814 0.5905 1.0000
3.000 0.6842 0.00969 0.00325 -0.0809 0.5534 1.0000
3.250 0.7093 0.01005 0.00341 -0.0804 0.5121 1.0000
3.500 0.7337 0.01048 0.00360 -0.0797 0.4657 1.0000
3.750 0.7579 0.01095 0.00383 -0.0791 0.4213 1.0000
4.000 0.7824 0.01140 0.00409 -0.0786 0.3844 1.0000
4.250 0.8074 0.01182 0.00438 -0.0781 0.3518 1.0000
4.500 0.8323 0.01224 0.00468 -0.0777 0.3219 1.0000
4.750 0.8573 0.01267 0.00499 -0.0772 0.2938 1.0000
5.000 0.8821 0.01311 0.00533 -0.0768 0.2660 1.0000
5.250 0.9065 0.01359 0.00570 -0.0763 0.2353 1.0000
5.500 0.9306 0.01412 0.00610 -0.0758 0.2027 1.0000
5.750 0.9540 0.01473 0.00654 -0.0753 0.1689 1.0000
6.000 0.9771 0.01539 0.00705 -0.0747 0.1361 1.0000
6.250 1.0000 0.01607 0.00760 -0.0740 0.1121 1.0000
6.500 1.0232 0.01671 0.00820 -0.0734 0.0952 1.0000
6.750 1.0462 0.01737 0.00882 -0.0728 0.0827 1.0000
7.000 1.0687 0.01807 0.00948 -0.0720 0.0733 1.0000
7.250 1.0917 0.01867 0.01015 -0.0713 0.0666 1.0000
7.500 1.1131 0.01946 0.01094 -0.0705 0.0613 1.0000
7.750 1.1356 0.02009 0.01167 -0.0697 0.0570 1.0000
8.000 1.1569 0.02083 0.01244 -0.0688 0.0528 1.0000
8.250 1.1765 0.02175 0.01339 -0.0678 0.0495 1.0000
8.500 1.1975 0.02249 0.01426 -0.0668 0.0470 1.0000
8.750 1.2178 0.02329 0.01516 -0.0658 0.0442 1.0000
9.000 1.2369 0.02416 0.01608 -0.0647 0.0416 1.0000
9.250 1.2532 0.02535 0.01731 -0.0633 0.0393 1.0000
9.500 1.2721 0.02624 0.01836 -0.0621 0.0377 1.0000
9.750 1.2901 0.02716 0.01940 -0.0609 0.0356 1.0000
10.000 1.3073 0.02805 0.02039 -0.0596 0.0335 1.0000
10.250 1.3218 0.02913 0.02154 -0.0581 0.0316 1.0000
10.500 1.3343 0.03047 0.02298 -0.0564 0.0300 1.0000
10.750 1.3478 0.03146 0.02416 -0.0546 0.0284 1.0000
11.000 1.3592 0.03252 0.02536 -0.0527 0.0267 1.0000
11.250 1.3690 0.03362 0.02656 -0.0507 0.0253 1.0000
11.500 1.3764 0.03488 0.02790 -0.0488 0.0241 1.0000
11.750 1.3804 0.03666 0.02977 -0.0467 0.0230 1.0000
12.000 1.3874 0.03824 0.03158 -0.0449 0.0219 1.0000
12.250 1.3919 0.04011 0.03367 -0.0433 0.0209 1.0000
12.500 1.3950 0.04212 0.03585 -0.0418 0.0200 1.0000
12.750 1.3971 0.04423 0.03810 -0.0406 0.0192 1.0000
13.000 1.3980 0.04652 0.04053 -0.0397 0.0185 1.0000
13.250 1.3965 0.04921 0.04334 -0.0391 0.0180 1.0000
13.500 1.3910 0.05258 0.04682 -0.0389 0.0174 1.0000
13.750 1.3868 0.05611 0.05059 -0.0390 0.0169 1.0000
14.000 1.3805 0.06010 0.05482 -0.0396 0.0164 1.0000
14.250 1.3723 0.06458 0.05952 -0.0407 0.0159 1.0000
14.500 1.3626 0.06955 0.06470 -0.0425 0.0155 1.0000
14.750 1.3511 0.07514 0.07050 -0.0450 0.0152 1.0000
15.000 1.3380 0.08135 0.07691 -0.0481 0.0149 1.0000
15.250 1.3229 0.08836 0.08412 -0.0520 0.0148 1.0000
15.500 1.3052 0.09630 0.09227 -0.0566 0.0147 1.0000
15.750 1.2847 0.10532 0.10149 -0.0620 0.0146 1.0000
16.000 1.2593 0.11592 0.11231 -0.0686 0.0147 1.0000
16.250 1.2249 0.12946 0.12609 -0.0772 0.0151 1.0000
16.500 1.1696 0.15010 0.14698 -0.0904 0.0161 1.0000
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