SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 100,000 Max Cl/Cd: 52.8 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2030-il-100000-n5.txt Download as CSV file: xf-sd2030-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD2030-086-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4463 0.10360 0.09849 -0.0360 1.0000 0.0581
-9.250 -0.4514 0.10025 0.09521 -0.0379 1.0000 0.0583
-9.000 -0.4573 0.09677 0.09181 -0.0395 1.0000 0.0584
-8.750 -0.3805 0.07799 0.07329 -0.0395 1.0000 0.0334
-8.500 -0.4629 0.08370 0.07879 -0.0403 1.0000 0.0336
-8.250 -0.4680 0.08092 0.07607 -0.0391 1.0000 0.0329
-8.000 -0.4790 0.07792 0.07316 -0.0387 1.0000 0.0325
-7.750 -0.4874 0.07435 0.06963 -0.0390 1.0000 0.0319
-7.500 -0.4955 0.07067 0.06595 -0.0391 1.0000 0.0313
-7.250 -0.5026 0.06682 0.06209 -0.0390 1.0000 0.0308
-7.000 -0.5080 0.06280 0.05800 -0.0388 1.0000 0.0302
-6.750 -0.5114 0.05854 0.05363 -0.0384 1.0000 0.0296
-6.500 -0.5121 0.05408 0.04899 -0.0379 1.0000 0.0290
-6.250 -0.5098 0.04948 0.04412 -0.0373 1.0000 0.0284
-6.000 -0.5039 0.04497 0.03928 -0.0365 1.0000 0.0279
-5.750 -0.4944 0.04081 0.03471 -0.0356 1.0000 0.0277
-5.500 -0.4744 0.03713 0.03058 -0.0362 0.9981 0.0281
-5.250 -0.4459 0.03414 0.02711 -0.0378 0.9946 0.0301
-5.000 -0.4177 0.03115 0.02356 -0.0388 0.9912 0.0310
-4.750 -0.3884 0.02841 0.02028 -0.0397 0.9878 0.0312
-4.500 -0.3574 0.02621 0.01761 -0.0405 0.9849 0.0315
-4.250 -0.3260 0.02444 0.01541 -0.0413 0.9822 0.0320
-4.000 -0.2970 0.02300 0.01369 -0.0416 0.9784 0.0328
-3.750 -0.2664 0.02184 0.01232 -0.0421 0.9750 0.0338
-3.500 -0.2352 0.02062 0.01104 -0.0430 0.9720 0.0356
-3.250 -0.2047 0.01998 0.01039 -0.0439 0.9683 0.0401
-3.000 -0.1763 0.01938 0.00963 -0.0442 0.9635 0.0449
-2.750 -0.1452 0.01859 0.00882 -0.0450 0.9597 0.0514
-2.500 -0.1115 0.01793 0.00816 -0.0463 0.9566 0.0685
-2.250 -0.0859 0.01731 0.00774 -0.0462 0.9508 0.1146
-2.000 -0.0585 0.01609 0.00757 -0.0470 0.9467 0.3254
-1.750 -0.0342 0.01486 0.00768 -0.0462 0.9434 0.6512
-1.500 -0.0141 0.01465 0.00791 -0.0431 0.9377 0.8422
-1.250 0.0404 0.01469 0.00789 -0.0475 0.9370 0.9596
-1.000 0.0970 0.01471 0.00768 -0.0535 0.9356 1.0000
-0.750 0.1314 0.01473 0.00753 -0.0551 0.9304 1.0000
-0.500 0.1577 0.01475 0.00741 -0.0550 0.9225 1.0000
-0.250 0.1923 0.01475 0.00729 -0.0566 0.9169 1.0000
0.000 0.2201 0.01476 0.00720 -0.0567 0.9088 1.0000
0.250 0.2567 0.01471 0.00707 -0.0584 0.9030 1.0000
0.500 0.2852 0.01468 0.00698 -0.0585 0.8940 1.0000
1.000 0.3511 0.01448 0.00671 -0.0603 0.8777 1.0000
1.250 0.3829 0.01437 0.00658 -0.0608 0.8686 1.0000
1.500 0.4186 0.01418 0.00638 -0.0619 0.8601 1.0000
1.750 0.4464 0.01407 0.00628 -0.0616 0.8480 1.0000
2.000 0.4754 0.01395 0.00619 -0.0614 0.8354 1.0000
2.250 0.5046 0.01382 0.00608 -0.0613 0.8219 1.0000
2.500 0.5338 0.01370 0.00598 -0.0610 0.8070 1.0000
2.750 0.5634 0.01357 0.00587 -0.0609 0.7904 1.0000
3.000 0.5896 0.01351 0.00588 -0.0601 0.7701 1.0000
3.250 0.6180 0.01343 0.00581 -0.0597 0.7477 1.0000
3.500 0.6442 0.01341 0.00580 -0.0588 0.7203 1.0000
3.750 0.6704 0.01342 0.00582 -0.0580 0.6863 1.0000
4.000 0.6970 0.01348 0.00580 -0.0571 0.6428 1.0000
4.250 0.7220 0.01369 0.00582 -0.0560 0.5879 1.0000
4.500 0.7439 0.01409 0.00595 -0.0545 0.5247 1.0000
4.750 0.7633 0.01466 0.00621 -0.0527 0.4614 1.0000
5.000 0.7816 0.01531 0.00662 -0.0510 0.4022 1.0000
5.250 0.7999 0.01600 0.00706 -0.0493 0.3490 1.0000
5.500 0.8186 0.01669 0.00756 -0.0478 0.3015 1.0000
5.750 0.8375 0.01741 0.00809 -0.0464 0.2593 1.0000
6.000 0.8566 0.01814 0.00867 -0.0451 0.2223 1.0000
6.250 0.8761 0.01887 0.00930 -0.0439 0.1906 1.0000
6.500 0.8954 0.01964 0.01003 -0.0426 0.1624 1.0000
6.750 0.9144 0.02046 0.01076 -0.0414 0.1396 1.0000
7.000 0.9337 0.02127 0.01157 -0.0401 0.1214 1.0000
7.250 0.9525 0.02213 0.01243 -0.0388 0.1061 1.0000
7.500 0.9709 0.02304 0.01336 -0.0375 0.0941 1.0000
7.750 0.9885 0.02407 0.01441 -0.0361 0.0857 1.0000
8.000 1.0064 0.02505 0.01551 -0.0347 0.0774 1.0000
8.250 1.0244 0.02611 0.01669 -0.0333 0.0698 1.0000
8.500 1.0409 0.02729 0.01791 -0.0319 0.0640 1.0000
8.750 1.0587 0.02848 0.01928 -0.0305 0.0574 1.0000
9.000 1.0734 0.02971 0.02053 -0.0290 0.0513 1.0000
9.250 1.0899 0.03065 0.02170 -0.0276 0.0435 1.0000
9.500 1.1029 0.03194 0.02310 -0.0259 0.0377 1.0000
9.750 1.1157 0.03334 0.02474 -0.0240 0.0327 1.0000
10.000 1.1233 0.03496 0.02641 -0.0218 0.0291 1.0000
10.250 1.1342 0.03662 0.02838 -0.0198 0.0252 1.0000
10.500 1.1415 0.03835 0.03028 -0.0176 0.0231 1.0000
10.750 1.1457 0.04035 0.03240 -0.0153 0.0218 1.0000
11.000 1.1479 0.04301 0.03525 -0.0130 0.0207 1.0000
11.250 1.1497 0.04581 0.03842 -0.0108 0.0198 1.0000
11.500 1.1476 0.04884 0.04179 -0.0087 0.0192 1.0000
11.750 1.1415 0.05213 0.04540 -0.0067 0.0186 1.0000
12.000 1.1326 0.05569 0.04926 -0.0053 0.0183 1.0000
12.250 1.1204 0.05964 0.05350 -0.0044 0.0180 1.0000
12.500 1.1058 0.06406 0.05819 -0.0044 0.0178 1.0000
12.750 1.0885 0.06916 0.06355 -0.0054 0.0178 1.0000
13.000 1.0682 0.07527 0.06990 -0.0078 0.0177 1.0000
13.250 1.0451 0.08266 0.07751 -0.0118 0.0179 1.0000
13.500 1.0191 0.09178 0.08685 -0.0177 0.0183 1.0000
13.750 0.9913 0.10275 0.09797 -0.0252 0.0189 1.0000
14.000 0.9621 0.11549 0.11082 -0.0335 0.0196 1.0000
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Polar data table (+)
Polar graphs
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