S2050 8.93% (s2050-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.47 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2050-il-1000000.txt Download as CSV file: xf-s2050-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6133 0.08898 0.08732 -0.0195 1.0000 0.0086
-10.750 -0.7118 0.06133 0.05967 -0.0355 1.0000 0.0075
-10.500 -0.8334 0.03797 0.03562 -0.0510 1.0000 0.0066
-10.250 -0.8267 0.03683 0.03444 -0.0498 1.0000 0.0068
-10.000 -0.8515 0.03067 0.02773 -0.0476 1.0000 0.0066
-9.750 -0.8478 0.02779 0.02455 -0.0460 1.0000 0.0066
-9.500 -0.8385 0.02539 0.02188 -0.0446 1.0000 0.0066
-9.250 -0.8247 0.02356 0.01985 -0.0434 1.0000 0.0067
-9.000 -0.8096 0.02165 0.01771 -0.0422 1.0000 0.0067
-8.750 -0.7921 0.02011 0.01597 -0.0412 1.0000 0.0067
-8.500 -0.7736 0.01857 0.01421 -0.0402 1.0000 0.0068
-8.250 -0.7533 0.01738 0.01288 -0.0394 1.0000 0.0069
-8.000 -0.7319 0.01646 0.01184 -0.0386 1.0000 0.0070
-7.750 -0.7100 0.01559 0.01086 -0.0378 1.0000 0.0073
-7.500 -0.6876 0.01473 0.00990 -0.0371 1.0000 0.0075
-7.250 -0.6649 0.01385 0.00891 -0.0364 1.0000 0.0076
-7.000 -0.6417 0.01304 0.00799 -0.0358 1.0000 0.0078
-6.750 -0.6180 0.01234 0.00720 -0.0352 1.0000 0.0080
-6.500 -0.5939 0.01176 0.00654 -0.0346 1.0000 0.0083
-6.250 -0.5634 0.01130 0.00601 -0.0353 0.9993 0.0086
-6.000 -0.5297 0.01037 0.00496 -0.0369 0.9979 0.0096
-5.750 -0.4947 0.00997 0.00452 -0.0386 0.9964 0.0105
-5.500 -0.4592 0.00963 0.00414 -0.0403 0.9950 0.0115
-5.250 -0.4244 0.00920 0.00368 -0.0419 0.9936 0.0139
-5.000 -0.3912 0.00869 0.00326 -0.0432 0.9914 0.0281
-4.750 -0.3566 0.00838 0.00301 -0.0448 0.9892 0.0423
-4.500 -0.3209 0.00812 0.00282 -0.0466 0.9872 0.0545
-4.250 -0.2842 0.00789 0.00264 -0.0486 0.9855 0.0678
-4.000 -0.2468 0.00765 0.00246 -0.0507 0.9841 0.0834
-3.750 -0.2153 0.00740 0.00228 -0.0515 0.9803 0.1017
-3.500 -0.1815 0.00710 0.00210 -0.0529 0.9768 0.1288
-3.250 -0.1454 0.00683 0.00193 -0.0548 0.9741 0.1576
-3.000 -0.1078 0.00652 0.00176 -0.0570 0.9720 0.1953
-2.750 -0.0773 0.00619 0.00159 -0.0576 0.9656 0.2409
-2.500 -0.0437 0.00582 0.00142 -0.0589 0.9597 0.3008
-2.250 -0.0131 0.00539 0.00126 -0.0597 0.9501 0.3818
-2.000 0.0211 0.00495 0.00110 -0.0611 0.9393 0.4736
-1.750 0.0552 0.00457 0.00098 -0.0625 0.9228 0.5637
-1.500 0.0869 0.00443 0.00091 -0.0632 0.8985 0.6221
-1.250 0.1151 0.00445 0.00088 -0.0630 0.8685 0.6465
-1.000 0.1420 0.00453 0.00086 -0.0626 0.8380 0.6665
-0.750 0.1686 0.00462 0.00086 -0.0621 0.8092 0.6809
-0.500 0.1952 0.00472 0.00087 -0.0616 0.7817 0.6940
-0.250 0.2218 0.00482 0.00089 -0.0612 0.7556 0.7065
0.000 0.2488 0.00491 0.00091 -0.0609 0.7309 0.7171
0.250 0.2759 0.00501 0.00093 -0.0606 0.7073 0.7269
0.750 0.3300 0.00521 0.00099 -0.0600 0.6577 0.7439
1.250 0.3837 0.00543 0.00109 -0.0594 0.6029 0.7631
1.500 0.4107 0.00558 0.00115 -0.0591 0.5734 0.7719
1.750 0.4373 0.00572 0.00121 -0.0588 0.5418 0.7805
2.000 0.4640 0.00588 0.00130 -0.0585 0.5116 0.7893
2.250 0.4908 0.00605 0.00138 -0.0582 0.4813 0.7982
2.500 0.5174 0.00621 0.00147 -0.0579 0.4510 0.8060
2.750 0.5441 0.00642 0.00158 -0.0577 0.4183 0.8144
3.000 0.5700 0.00665 0.00170 -0.0573 0.3784 0.8228
3.250 0.5964 0.00687 0.00183 -0.0570 0.3467 0.8323
3.500 0.6228 0.00708 0.00197 -0.0567 0.3185 0.8424
3.750 0.6485 0.00733 0.00213 -0.0563 0.2829 0.8521
4.000 0.6737 0.00765 0.00231 -0.0559 0.2415 0.8630
4.250 0.6990 0.00794 0.00250 -0.0554 0.2082 0.8755
4.500 0.7234 0.00824 0.00271 -0.0547 0.1758 0.8902
4.750 0.7471 0.00852 0.00294 -0.0539 0.1476 0.9080
5.000 0.7693 0.00878 0.00315 -0.0527 0.1230 0.9317
5.250 0.7928 0.00901 0.00334 -0.0517 0.0996 0.9791
5.500 0.8202 0.00940 0.00362 -0.0518 0.0771 1.0000
5.750 0.8462 0.00981 0.00393 -0.0516 0.0583 1.0000
6.000 0.8721 0.01022 0.00426 -0.0514 0.0421 1.0000
6.250 0.8970 0.01078 0.00470 -0.0510 0.0245 1.0000
6.500 0.9221 0.01129 0.00518 -0.0505 0.0187 1.0000
6.750 0.9481 0.01166 0.00560 -0.0502 0.0171 1.0000
7.000 0.9735 0.01211 0.00605 -0.0498 0.0156 1.0000
7.250 0.9971 0.01282 0.00684 -0.0491 0.0139 1.0000
7.500 1.0220 0.01328 0.00736 -0.0487 0.0135 1.0000
7.750 1.0467 0.01377 0.00791 -0.0482 0.0131 1.0000
8.000 1.0708 0.01431 0.00852 -0.0476 0.0125 1.0000
8.250 1.0944 0.01490 0.00917 -0.0470 0.0121 1.0000
8.500 1.1176 0.01553 0.00986 -0.0463 0.0116 1.0000
8.750 1.1406 0.01615 0.01053 -0.0456 0.0112 1.0000
9.000 1.1620 0.01695 0.01139 -0.0447 0.0106 1.0000
9.250 1.1770 0.01862 0.01321 -0.0429 0.0100 1.0000
9.500 1.1956 0.01979 0.01451 -0.0417 0.0097 1.0000
9.750 1.2174 0.02045 0.01525 -0.0409 0.0095 1.0000
10.000 1.2378 0.02127 0.01616 -0.0399 0.0093 1.0000
10.250 1.2566 0.02225 0.01725 -0.0387 0.0090 1.0000
10.500 1.2753 0.02318 0.01828 -0.0376 0.0087 1.0000
10.750 1.2934 0.02410 0.01929 -0.0364 0.0084 1.0000
11.000 1.3106 0.02503 0.02031 -0.0352 0.0081 1.0000
11.250 1.3278 0.02584 0.02119 -0.0340 0.0078 1.0000
11.500 1.3421 0.02689 0.02233 -0.0325 0.0076 1.0000
11.750 1.3535 0.02812 0.02365 -0.0306 0.0074 1.0000
12.000 1.3573 0.02972 0.02536 -0.0278 0.0072 1.0000
12.250 1.3488 0.03216 0.02799 -0.0237 0.0070 1.0000
12.500 1.3259 0.03615 0.03227 -0.0192 0.0068 1.0000
12.750 1.3219 0.03830 0.03459 -0.0170 0.0068 1.0000
13.000 1.3221 0.04019 0.03660 -0.0158 0.0067 1.0000
13.250 1.3195 0.04262 0.03918 -0.0150 0.0066 1.0000
13.500 1.3111 0.04606 0.04277 -0.0149 0.0066 1.0000
13.750 1.3076 0.04924 0.04609 -0.0156 0.0065 1.0000
14.000 1.2958 0.05397 0.05098 -0.0173 0.0065 1.0000
14.250 1.2826 0.05942 0.05660 -0.0199 0.0064 1.0000
14.500 1.2690 0.06550 0.06283 -0.0234 0.0064 1.0000
14.750 1.2514 0.07283 0.07032 -0.0279 0.0064 1.0000
15.000 1.2284 0.08174 0.07941 -0.0336 0.0064 1.0000
15.250 1.2046 0.09140 0.08923 -0.0398 0.0064 1.0000
15.500 1.1777 0.10230 0.10028 -0.0467 0.0065 1.0000
15.750 1.1459 0.11495 0.11309 -0.0546 0.0066 1.0000
16.000 1.0990 0.13231 0.13062 -0.0653 0.0067 1.0000
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Polar data table (+)
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