SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 50,000 Max Cl/Cd: 38.33 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2083-il-50000-n5.txt Download as CSV file: xf-sd2083-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD2083 (9.0%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4033 0.10188 0.09516 -0.0344 1.0000 0.1172
-8.500 -0.3987 0.09336 0.08661 -0.0384 1.0000 0.0615
-8.250 -0.4000 0.09011 0.08344 -0.0389 1.0000 0.0608
-8.000 -0.4042 0.08705 0.08049 -0.0390 1.0000 0.0600
-7.750 -0.4117 0.08418 0.07773 -0.0390 1.0000 0.0590
-7.500 -0.4187 0.08103 0.07468 -0.0394 1.0000 0.0579
-7.250 -0.4268 0.07778 0.07151 -0.0397 1.0000 0.0569
-6.750 -0.4546 0.06808 0.06150 -0.0441 1.0000 0.0501
-6.500 -0.4553 0.06482 0.05817 -0.0431 1.0000 0.0499
-6.250 -0.4541 0.06154 0.05478 -0.0421 1.0000 0.0497
-6.000 -0.4506 0.05822 0.05135 -0.0411 1.0000 0.0494
-5.750 -0.4452 0.05489 0.04787 -0.0402 1.0000 0.0490
-5.500 -0.4377 0.05158 0.04433 -0.0395 1.0000 0.0485
-5.250 -0.4277 0.04822 0.04063 -0.0389 1.0000 0.0480
-5.000 -0.4153 0.04495 0.03701 -0.0383 1.0000 0.0477
-4.750 -0.4005 0.04188 0.03353 -0.0377 1.0000 0.0475
-4.500 -0.3835 0.03904 0.03025 -0.0370 1.0000 0.0474
-4.250 -0.3593 0.03623 0.02691 -0.0373 0.9980 0.0476
-4.000 -0.3271 0.03362 0.02371 -0.0387 0.9935 0.0480
-3.750 -0.2952 0.03143 0.02097 -0.0397 0.9888 0.0489
-3.500 -0.2625 0.02964 0.01881 -0.0408 0.9844 0.0512
-3.250 -0.2316 0.02845 0.01749 -0.0420 0.9795 0.0571
-3.000 -0.1994 0.02728 0.01593 -0.0426 0.9745 0.0619
-2.750 -0.1651 0.02610 0.01460 -0.0438 0.9703 0.0670
-2.500 -0.1344 0.02522 0.01348 -0.0443 0.9648 0.0762
-2.250 -0.1015 0.02429 0.01256 -0.0456 0.9596 0.1009
-2.000 -0.0683 0.02264 0.01196 -0.0477 0.9556 0.2578
-1.500 0.0133 0.02036 0.01153 -0.0513 0.9479 1.0000
-1.250 0.0497 0.02065 0.01137 -0.0534 0.9421 1.0000
-1.000 0.0773 0.02088 0.01125 -0.0538 0.9338 1.0000
-0.750 0.1126 0.02118 0.01123 -0.0556 0.9275 1.0000
-0.500 0.1408 0.02145 0.01125 -0.0561 0.9191 1.0000
-0.250 0.1733 0.02174 0.01130 -0.0574 0.9120 1.0000
0.000 0.2044 0.02202 0.01139 -0.0584 0.9040 1.0000
0.250 0.2336 0.02231 0.01153 -0.0590 0.8956 1.0000
0.500 0.2693 0.02257 0.01165 -0.0608 0.8885 1.0000
0.750 0.2954 0.02286 0.01183 -0.0607 0.8788 1.0000
1.000 0.3303 0.02310 0.01199 -0.0622 0.8712 1.0000
1.250 0.3599 0.02335 0.01218 -0.0627 0.8616 1.0000
1.500 0.3871 0.02360 0.01239 -0.0627 0.8513 1.0000
1.750 0.4192 0.02378 0.01255 -0.0635 0.8422 1.0000
2.000 0.4512 0.02392 0.01269 -0.0641 0.8325 1.0000
2.500 0.5049 0.02426 0.01310 -0.0634 0.8089 1.0000
2.750 0.5336 0.02434 0.01322 -0.0633 0.7969 1.0000
3.000 0.5629 0.02436 0.01330 -0.0631 0.7847 1.0000
3.250 0.5920 0.02433 0.01338 -0.0627 0.7718 1.0000
3.500 0.6201 0.02427 0.01342 -0.0621 0.7579 1.0000
3.750 0.6472 0.02419 0.01345 -0.0613 0.7429 1.0000
4.000 0.6742 0.02408 0.01346 -0.0604 0.7271 1.0000
4.250 0.7018 0.02391 0.01347 -0.0595 0.7107 1.0000
4.500 0.7304 0.02367 0.01336 -0.0586 0.6937 1.0000
4.750 0.7539 0.02362 0.01345 -0.0571 0.6732 1.0000
5.000 0.7812 0.02340 0.01337 -0.0559 0.6523 1.0000
5.250 0.8050 0.02333 0.01344 -0.0544 0.6274 1.0000
5.500 0.8299 0.02323 0.01353 -0.0529 0.5996 1.0000
5.750 0.8553 0.02314 0.01351 -0.0514 0.5682 1.0000
6.000 0.8777 0.02327 0.01368 -0.0496 0.5312 1.0000
6.250 0.8993 0.02351 0.01389 -0.0477 0.4909 1.0000
6.500 0.9188 0.02397 0.01426 -0.0458 0.4490 1.0000
6.750 0.9363 0.02464 0.01489 -0.0437 0.4072 1.0000
7.000 0.9520 0.02549 0.01562 -0.0417 0.3675 1.0000
7.250 0.9665 0.02646 0.01649 -0.0396 0.3309 1.0000
7.500 0.9802 0.02752 0.01750 -0.0376 0.2958 1.0000
7.750 0.9928 0.02868 0.01860 -0.0356 0.2635 1.0000
8.000 1.0044 0.02992 0.01978 -0.0335 0.2333 1.0000
8.250 1.0153 0.03124 0.02107 -0.0314 0.2041 1.0000
8.500 1.0249 0.03266 0.02248 -0.0293 0.1761 1.0000
8.750 1.0322 0.03420 0.02404 -0.0270 0.1510 1.0000
9.000 1.0376 0.03590 0.02572 -0.0247 0.1255 1.0000
9.250 1.0408 0.03780 0.02756 -0.0224 0.1007 1.0000
9.500 1.0429 0.03989 0.02958 -0.0204 0.0780 1.0000
9.750 1.0460 0.04215 0.03180 -0.0186 0.0630 1.0000
10.000 1.0513 0.04464 0.03438 -0.0168 0.0528 1.0000
10.250 1.0575 0.04719 0.03700 -0.0152 0.0472 1.0000
10.500 1.0664 0.04964 0.03972 -0.0138 0.0422 1.0000
10.750 1.0686 0.05221 0.04229 -0.0126 0.0387 1.0000
11.000 1.0767 0.05510 0.04553 -0.0113 0.0357 1.0000
11.250 1.0822 0.05825 0.04904 -0.0101 0.0337 1.0000
11.500 1.0843 0.06166 0.05276 -0.0092 0.0327 1.0000
11.750 1.0816 0.06546 0.05685 -0.0086 0.0317 1.0000
12.000 1.0757 0.06954 0.06130 -0.0084 0.0313 1.0000
12.250 1.0662 0.07406 0.06610 -0.0087 0.0310 1.0000
12.500 1.0529 0.07922 0.07151 -0.0098 0.0307 1.0000
12.750 1.0368 0.08508 0.07763 -0.0119 0.0308 1.0000
13.000 1.0175 0.09192 0.08470 -0.0151 0.0310 1.0000
13.250 0.9954 0.09998 0.09290 -0.0197 0.0314 1.0000
13.500 0.9710 0.10962 0.10272 -0.0256 0.0320 1.0000
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Polar data table (+)
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