SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 200,000 Max Cl/Cd: 68.92 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2030-il-200000-n5.txt Download as CSV file: xf-sd2030-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4479 0.08769 0.08410 -0.0352 1.0000 0.0198
-8.750 -0.4560 0.08360 0.08007 -0.0361 1.0000 0.0196
-8.500 -0.4632 0.08047 0.07701 -0.0364 1.0000 0.0199
-8.250 -0.5053 0.07202 0.06871 -0.0400 1.0000 0.0177
-8.000 -0.5156 0.06769 0.06437 -0.0410 1.0000 0.0175
-7.750 -0.5297 0.06319 0.05984 -0.0409 1.0000 0.0177
-7.500 -0.5322 0.05790 0.05443 -0.0429 0.9982 0.0179
-7.250 -0.5169 0.05135 0.04764 -0.0483 0.9936 0.0182
-7.000 -0.5029 0.04343 0.03923 -0.0520 0.9879 0.0178
-6.750 -0.4810 0.03827 0.03357 -0.0545 0.9840 0.0175
-6.500 -0.4612 0.03422 0.02907 -0.0555 0.9794 0.0174
-6.250 -0.4402 0.03018 0.02446 -0.0564 0.9750 0.0175
-6.000 -0.4148 0.02657 0.02030 -0.0574 0.9720 0.0177
-5.750 -0.3872 0.02388 0.01719 -0.0584 0.9695 0.0181
-5.500 -0.3641 0.02218 0.01521 -0.0579 0.9647 0.0185
-5.250 -0.3355 0.02092 0.01375 -0.0585 0.9614 0.0194
-5.000 -0.3045 0.01994 0.01259 -0.0595 0.9590 0.0206
-4.750 -0.2722 0.01880 0.01123 -0.0606 0.9572 0.0216
-4.500 -0.2467 0.01773 0.01000 -0.0602 0.9527 0.0220
-4.250 -0.2188 0.01679 0.00894 -0.0602 0.9488 0.0224
-4.000 -0.1879 0.01595 0.00800 -0.0610 0.9460 0.0231
-3.750 -0.1553 0.01523 0.00719 -0.0620 0.9439 0.0241
-3.500 -0.1264 0.01463 0.00650 -0.0623 0.9403 0.0251
-3.250 -0.1001 0.01409 0.00593 -0.0621 0.9352 0.0274
-3.000 -0.0681 0.01369 0.00548 -0.0631 0.9322 0.0316
-2.750 -0.0351 0.01323 0.00504 -0.0642 0.9298 0.0448
-2.500 -0.0090 0.01278 0.00472 -0.0640 0.9246 0.0762
-2.000 0.0496 0.01170 0.00425 -0.0651 0.9168 0.2372
-1.750 0.0737 0.01080 0.00412 -0.0649 0.9117 0.4347
-1.500 0.0936 0.00993 0.00411 -0.0632 0.9057 0.6582
-1.250 0.1188 0.00959 0.00416 -0.0617 0.9021 0.7935
-1.000 0.1409 0.00953 0.00420 -0.0597 0.8953 0.8610
-0.750 0.1706 0.00946 0.00414 -0.0593 0.8904 0.9042
-0.500 0.2076 0.00939 0.00402 -0.0606 0.8864 0.9340
-0.250 0.2459 0.00935 0.00394 -0.0624 0.8793 0.9579
0.000 0.2937 0.00924 0.00376 -0.0663 0.8744 0.9730
0.250 0.3382 0.00915 0.00363 -0.0696 0.8661 0.9843
0.500 0.3832 0.00901 0.00343 -0.0731 0.8580 0.9914
0.750 0.4235 0.00890 0.00328 -0.0757 0.8470 0.9986
1.000 0.4504 0.00884 0.00317 -0.0754 0.8339 1.0000
1.250 0.4738 0.00880 0.00309 -0.0744 0.8200 1.0000
1.500 0.4972 0.00878 0.00303 -0.0733 0.8050 1.0000
1.750 0.5204 0.00878 0.00299 -0.0722 0.7884 1.0000
2.000 0.5426 0.00882 0.00298 -0.0709 0.7694 1.0000
2.250 0.5656 0.00886 0.00297 -0.0698 0.7483 1.0000
2.500 0.5881 0.00893 0.00299 -0.0685 0.7232 1.0000
2.750 0.6105 0.00904 0.00300 -0.0671 0.6931 1.0000
3.000 0.6323 0.00920 0.00303 -0.0657 0.6557 1.0000
3.250 0.6527 0.00947 0.00309 -0.0640 0.6082 1.0000
3.500 0.6716 0.00984 0.00320 -0.0621 0.5530 1.0000
3.750 0.6894 0.01032 0.00341 -0.0601 0.4943 1.0000
4.000 0.7075 0.01083 0.00366 -0.0583 0.4383 1.0000
4.250 0.7263 0.01135 0.00394 -0.0566 0.3866 1.0000
4.500 0.7457 0.01187 0.00425 -0.0552 0.3397 1.0000
4.750 0.7657 0.01240 0.00459 -0.0539 0.2968 1.0000
5.000 0.7864 0.01291 0.00497 -0.0528 0.2584 1.0000
5.250 0.8073 0.01342 0.00535 -0.0517 0.2252 1.0000
5.500 0.8286 0.01394 0.00574 -0.0507 0.1946 1.0000
5.750 0.8499 0.01446 0.00616 -0.0497 0.1667 1.0000
6.000 0.8712 0.01500 0.00661 -0.0488 0.1428 1.0000
6.250 0.8928 0.01553 0.00711 -0.0478 0.1216 1.0000
6.500 0.9141 0.01609 0.00762 -0.0469 0.1042 1.0000
6.750 0.9354 0.01665 0.00817 -0.0459 0.0911 1.0000
7.000 0.9566 0.01722 0.00876 -0.0449 0.0801 1.0000
7.250 0.9773 0.01783 0.00939 -0.0439 0.0709 1.0000
7.500 0.9971 0.01853 0.01008 -0.0427 0.0632 1.0000
7.750 1.0178 0.01914 0.01083 -0.0416 0.0578 1.0000
8.000 1.0367 0.01990 0.01158 -0.0404 0.0512 1.0000
8.250 1.0582 0.02040 0.01217 -0.0396 0.0441 1.0000
8.500 1.0779 0.02105 0.01284 -0.0386 0.0373 1.0000
8.750 1.0975 0.02171 0.01354 -0.0375 0.0313 1.0000
9.000 1.1159 0.02249 0.01442 -0.0362 0.0269 1.0000
9.250 1.1331 0.02336 0.01538 -0.0348 0.0219 1.0000
9.500 1.1485 0.02440 0.01655 -0.0331 0.0181 1.0000
9.750 1.1621 0.02548 0.01769 -0.0312 0.0155 1.0000
10.000 1.1735 0.02667 0.01901 -0.0289 0.0137 1.0000
10.250 1.1861 0.02772 0.02019 -0.0269 0.0121 1.0000
10.500 1.1969 0.02889 0.02146 -0.0249 0.0111 1.0000
10.750 1.2032 0.03041 0.02309 -0.0223 0.0104 1.0000
11.000 1.2102 0.03190 0.02478 -0.0200 0.0100 1.0000
11.250 1.2157 0.03356 0.02664 -0.0176 0.0095 1.0000
11.500 1.2197 0.03537 0.02864 -0.0153 0.0092 1.0000
11.750 1.2221 0.03734 0.03085 -0.0131 0.0089 1.0000
12.000 1.2233 0.03945 0.03317 -0.0111 0.0087 1.0000
12.250 1.2225 0.04181 0.03573 -0.0093 0.0084 1.0000
12.500 1.2202 0.04438 0.03850 -0.0077 0.0083 1.0000
12.750 1.2160 0.04725 0.04158 -0.0066 0.0081 1.0000
13.000 1.2096 0.05051 0.04504 -0.0058 0.0079 1.0000
13.250 1.2013 0.05418 0.04892 -0.0056 0.0078 1.0000
13.500 1.1916 0.05831 0.05326 -0.0061 0.0078 1.0000
13.750 1.1798 0.06306 0.05823 -0.0073 0.0078 1.0000
14.000 1.1654 0.06866 0.06405 -0.0095 0.0078 1.0000
14.250 1.1486 0.07525 0.07086 -0.0128 0.0078 1.0000
14.500 1.1305 0.08276 0.07859 -0.0171 0.0078 1.0000
14.750 1.1095 0.09166 0.08771 -0.0226 0.0079 1.0000
15.000 1.0848 0.10216 0.09842 -0.0293 0.0079 1.0000
15.250 1.0550 0.11468 0.11114 -0.0370 0.0081 1.0000
15.500 1.0136 0.13123 0.12785 -0.0467 0.0085 1.0000
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Polar data table (+)
Polar graphs
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