S2050 8.93% (s2050-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 200,000 Max Cl/Cd: 63.53 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2050-il-200000.txt Download as CSV file: xf-s2050-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5260 0.08699 0.08343 -0.0237 1.0000 0.0549
-8.750 -0.5295 0.08276 0.07925 -0.0256 1.0000 0.0559
-8.500 -0.5368 0.07810 0.07464 -0.0282 1.0000 0.0571
-8.250 -0.5508 0.07285 0.06947 -0.0320 1.0000 0.0575
-8.000 -0.5671 0.06689 0.06352 -0.0369 1.0000 0.0580
-7.750 -0.6331 0.04312 0.03860 -0.0439 1.0000 0.0290
-7.500 -0.6306 0.03809 0.03325 -0.0432 1.0000 0.0280
-7.250 -0.6233 0.03318 0.02784 -0.0423 1.0000 0.0270
-7.000 -0.6102 0.02899 0.02309 -0.0412 1.0000 0.0265
-6.750 -0.5925 0.02582 0.01943 -0.0402 1.0000 0.0266
-6.500 -0.5718 0.02368 0.01691 -0.0392 1.0000 0.0278
-6.250 -0.5491 0.02257 0.01548 -0.0383 1.0000 0.0296
-6.000 -0.5281 0.01981 0.01248 -0.0374 1.0000 0.0313
-5.750 -0.5056 0.01842 0.01101 -0.0366 1.0000 0.0335
-5.500 -0.4822 0.01727 0.00975 -0.0357 1.0000 0.0371
-5.250 -0.4592 0.01590 0.00836 -0.0349 1.0000 0.0435
-5.000 -0.4353 0.01511 0.00758 -0.0343 1.0000 0.0581
-4.750 -0.4110 0.01453 0.00693 -0.0337 1.0000 0.0751
-4.500 -0.3871 0.01390 0.00638 -0.0333 1.0000 0.0933
-4.250 -0.3628 0.01343 0.00594 -0.0329 1.0000 0.1116
-4.000 -0.3382 0.01292 0.00545 -0.0324 1.0000 0.1314
-3.750 -0.3135 0.01238 0.00503 -0.0322 1.0000 0.1559
-3.500 -0.2886 0.01187 0.00465 -0.0320 1.0000 0.1892
-3.250 -0.2634 0.01128 0.00434 -0.0319 1.0000 0.2425
-3.000 -0.2382 0.01057 0.00411 -0.0321 1.0000 0.3443
-2.750 -0.2142 0.00977 0.00405 -0.0319 1.0000 0.5089
-2.500 -0.1935 0.00958 0.00429 -0.0304 1.0000 0.6344
-2.250 -0.1728 0.00965 0.00446 -0.0289 1.0000 0.6897
-2.000 -0.1528 0.00977 0.00462 -0.0273 1.0000 0.7259
-1.750 -0.1242 0.00995 0.00481 -0.0275 0.9969 0.7569
-1.500 -0.0833 0.01012 0.00499 -0.0300 0.9886 0.7844
-1.250 -0.0436 0.01022 0.00511 -0.0320 0.9802 0.8072
-1.000 -0.0029 0.01027 0.00514 -0.0343 0.9718 0.8293
-0.750 0.0323 0.01019 0.00509 -0.0353 0.9610 0.8474
-0.500 0.0679 0.01007 0.00499 -0.0363 0.9506 0.8638
-0.250 0.1060 0.00992 0.00486 -0.0378 0.9423 0.8797
0.000 0.1400 0.00972 0.00468 -0.0383 0.9318 0.8964
0.250 0.1719 0.00950 0.00449 -0.0383 0.9201 0.9133
0.500 0.2044 0.00927 0.00428 -0.0384 0.9077 0.9288
0.750 0.2396 0.00905 0.00406 -0.0391 0.8939 0.9429
1.000 0.2796 0.00886 0.00387 -0.0410 0.8777 0.9539
1.250 0.3225 0.00871 0.00369 -0.0436 0.8589 0.9624
1.500 0.3625 0.00863 0.00357 -0.0457 0.8346 0.9715
1.750 0.4047 0.00861 0.00348 -0.0483 0.8080 0.9788
2.000 0.4453 0.00863 0.00343 -0.0508 0.7786 0.9873
2.250 0.4857 0.00869 0.00340 -0.0532 0.7474 0.9965
2.500 0.5091 0.00881 0.00341 -0.0526 0.7172 1.0000
2.750 0.5267 0.00896 0.00346 -0.0507 0.6876 1.0000
3.000 0.5490 0.00916 0.00356 -0.0498 0.6559 1.0000
3.250 0.5735 0.00938 0.00366 -0.0492 0.6220 1.0000
3.500 0.5987 0.00963 0.00378 -0.0487 0.5860 1.0000
3.750 0.6239 0.00992 0.00393 -0.0482 0.5490 1.0000
4.000 0.6488 0.01024 0.00413 -0.0477 0.5098 1.0000
4.250 0.6734 0.01060 0.00435 -0.0471 0.4683 1.0000
4.500 0.6977 0.01100 0.00459 -0.0465 0.4256 1.0000
4.750 0.7219 0.01143 0.00489 -0.0459 0.3830 1.0000
5.000 0.7460 0.01190 0.00522 -0.0453 0.3411 1.0000
5.250 0.7698 0.01242 0.00559 -0.0447 0.2978 1.0000
5.500 0.7929 0.01303 0.00599 -0.0441 0.2501 1.0000
5.750 0.8157 0.01372 0.00647 -0.0435 0.2002 1.0000
6.000 0.8384 0.01446 0.00701 -0.0429 0.1566 1.0000
6.250 0.8606 0.01531 0.00766 -0.0422 0.1181 1.0000
6.500 0.8818 0.01634 0.00849 -0.0413 0.0837 1.0000
6.750 0.9016 0.01763 0.00967 -0.0401 0.0597 1.0000
7.000 0.9216 0.01890 0.01097 -0.0388 0.0492 1.0000
7.250 0.9406 0.02037 0.01243 -0.0375 0.0434 1.0000
7.500 0.9628 0.02142 0.01358 -0.0366 0.0394 1.0000
7.750 0.9838 0.02277 0.01495 -0.0356 0.0368 1.0000
8.000 1.0036 0.02553 0.01775 -0.0346 0.0347 1.0000
8.250 1.0265 0.02711 0.01953 -0.0337 0.0339 1.0000
8.500 1.0485 0.02882 0.02151 -0.0328 0.0327 1.0000
8.750 1.0690 0.03048 0.02342 -0.0317 0.0310 1.0000
9.000 1.0880 0.03260 0.02580 -0.0306 0.0300 1.0000
9.250 1.1045 0.03521 0.02873 -0.0293 0.0294 1.0000
9.500 1.1172 0.03832 0.03222 -0.0276 0.0292 1.0000
9.750 1.1237 0.04213 0.03651 -0.0254 0.0294 1.0000
10.000 1.1212 0.04685 0.04177 -0.0227 0.0300 1.0000
10.250 1.1119 0.05176 0.04715 -0.0200 0.0308 1.0000
10.500 1.0976 0.05618 0.05191 -0.0174 0.0312 1.0000
10.750 1.0772 0.06016 0.05614 -0.0146 0.0317 1.0000
11.000 1.0550 0.06438 0.06057 -0.0132 0.0321 1.0000
11.250 1.0313 0.06932 0.06570 -0.0140 0.0325 1.0000
11.500 1.0070 0.07541 0.07194 -0.0169 0.0330 1.0000
11.750 0.9821 0.08273 0.07938 -0.0217 0.0334 1.0000
12.000 0.9594 0.09124 0.08797 -0.0273 0.0341 1.0000
12.250 0.7811 0.11352 0.11069 -0.0410 0.0370 1.0000
12.500 0.7925 0.11331 0.11049 -0.0400 0.0359 1.0000
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Polar data table (+)
Polar graphs
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