SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 100,000 Max Cl/Cd: 56.37 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd2083-il-100000-n5.txt Download as CSV file: xf-sd2083-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3284 0.07744 0.07300 -0.0410 1.0000 0.0363
-8.000 -0.4097 0.08079 0.07621 -0.0407 1.0000 0.0359
-7.750 -0.4211 0.07848 0.07399 -0.0392 1.0000 0.0351
-7.500 -0.4333 0.07590 0.07149 -0.0382 1.0000 0.0343
-7.250 -0.4462 0.07312 0.06877 -0.0373 1.0000 0.0336
-7.000 -0.4556 0.06976 0.06542 -0.0374 0.9995 0.0327
-6.500 -0.4171 0.05096 0.04576 -0.0553 0.9829 0.0272
-6.250 -0.3993 0.04632 0.04083 -0.0578 0.9760 0.0269
-6.000 -0.3758 0.04157 0.03566 -0.0607 0.9709 0.0266
-5.750 -0.3545 0.03755 0.03116 -0.0620 0.9646 0.0266
-5.500 -0.3286 0.03405 0.02704 -0.0633 0.9595 0.0269
-5.250 -0.2996 0.03096 0.02350 -0.0652 0.9560 0.0286
-5.000 -0.2765 0.02920 0.02147 -0.0651 0.9496 0.0300
-4.750 -0.2460 0.02685 0.01864 -0.0660 0.9456 0.0302
-4.500 -0.2126 0.02484 0.01624 -0.0673 0.9428 0.0304
-4.250 -0.1878 0.02342 0.01454 -0.0667 0.9366 0.0309
-4.000 -0.1571 0.02208 0.01299 -0.0672 0.9324 0.0317
-3.750 -0.1241 0.02089 0.01160 -0.0682 0.9293 0.0329
-3.500 -0.0998 0.02006 0.01065 -0.0675 0.9229 0.0343
-3.250 -0.0703 0.01927 0.00972 -0.0678 0.9183 0.0367
-3.000 -0.0381 0.01851 0.00891 -0.0687 0.9150 0.0419
-2.750 -0.0156 0.01806 0.00841 -0.0677 0.9076 0.0516
-2.500 0.0141 0.01726 0.00768 -0.0680 0.9032 0.0804
-2.250 0.0396 0.01650 0.00733 -0.0679 0.8977 0.1735
-2.000 0.0625 0.01539 0.00722 -0.0676 0.8918 0.4099
-1.750 0.0863 0.01436 0.00725 -0.0661 0.8880 0.6894
-1.500 0.1615 0.01384 0.00707 -0.0740 0.8895 0.9534
-1.250 0.2215 0.01373 0.00671 -0.0807 0.8882 1.0000
-1.000 0.2428 0.01382 0.00662 -0.0796 0.8798 1.0000
-0.750 0.2709 0.01381 0.00645 -0.0796 0.8741 1.0000
-0.500 0.2922 0.01392 0.00643 -0.0784 0.8655 1.0000
-0.250 0.3204 0.01390 0.00629 -0.0783 0.8598 1.0000
0.000 0.3416 0.01401 0.00630 -0.0770 0.8507 1.0000
0.250 0.3696 0.01399 0.00617 -0.0767 0.8447 1.0000
0.500 0.3913 0.01408 0.00620 -0.0755 0.8351 1.0000
0.750 0.4159 0.01411 0.00617 -0.0747 0.8268 1.0000
1.000 0.4420 0.01409 0.00609 -0.0740 0.8188 1.0000
1.250 0.4649 0.01415 0.00612 -0.0729 0.8086 1.0000
1.500 0.4901 0.01415 0.00608 -0.0721 0.7993 1.0000
1.750 0.5164 0.01409 0.00600 -0.0713 0.7901 1.0000
2.000 0.5399 0.01411 0.00601 -0.0702 0.7783 1.0000
2.250 0.5641 0.01412 0.00602 -0.0692 0.7665 1.0000
2.500 0.5887 0.01411 0.00601 -0.0682 0.7541 1.0000
2.750 0.6135 0.01410 0.00604 -0.0673 0.7411 1.0000
3.000 0.6382 0.01411 0.00606 -0.0664 0.7273 1.0000
3.250 0.6630 0.01412 0.00610 -0.0654 0.7125 1.0000
3.500 0.6879 0.01415 0.00615 -0.0645 0.6968 1.0000
3.750 0.7130 0.01418 0.00623 -0.0636 0.6800 1.0000
4.000 0.7372 0.01425 0.00634 -0.0626 0.6603 1.0000
4.250 0.7617 0.01432 0.00642 -0.0616 0.6386 1.0000
4.500 0.7854 0.01444 0.00654 -0.0605 0.6130 1.0000
4.750 0.8090 0.01459 0.00667 -0.0593 0.5836 1.0000
5.000 0.8317 0.01482 0.00689 -0.0581 0.5492 1.0000
5.250 0.8535 0.01514 0.00710 -0.0567 0.5100 1.0000
5.500 0.8741 0.01556 0.00740 -0.0552 0.4671 1.0000
5.750 0.8935 0.01610 0.00778 -0.0537 0.4234 1.0000
6.000 0.9123 0.01673 0.00824 -0.0521 0.3816 1.0000
6.250 0.9305 0.01741 0.00879 -0.0505 0.3426 1.0000
6.500 0.9487 0.01811 0.00944 -0.0491 0.3064 1.0000
6.750 0.9664 0.01886 0.01009 -0.0475 0.2729 1.0000
7.000 0.9842 0.01961 0.01079 -0.0461 0.2419 1.0000
7.250 1.0015 0.02040 0.01153 -0.0446 0.2124 1.0000
7.500 1.0184 0.02123 0.01232 -0.0431 0.1840 1.0000
7.750 1.0335 0.02219 0.01314 -0.0415 0.1500 1.0000
8.000 1.0473 0.02329 0.01401 -0.0399 0.1116 1.0000
8.250 1.0601 0.02456 0.01507 -0.0382 0.0743 1.0000
8.500 1.0720 0.02594 0.01630 -0.0362 0.0479 1.0000
8.750 1.0822 0.02746 0.01781 -0.0340 0.0331 1.0000
9.000 1.0892 0.02912 0.01948 -0.0313 0.0269 1.0000
9.250 1.0967 0.03056 0.02111 -0.0286 0.0239 1.0000
9.500 1.1032 0.03210 0.02280 -0.0260 0.0219 1.0000
9.750 1.1085 0.03374 0.02457 -0.0236 0.0205 1.0000
10.000 1.1104 0.03578 0.02670 -0.0211 0.0192 1.0000
10.250 1.1183 0.03742 0.02856 -0.0192 0.0178 1.0000
10.500 1.1249 0.03923 0.03055 -0.0174 0.0168 1.0000
11.000 1.1348 0.04329 0.03499 -0.0141 0.0151 1.0000
11.250 1.1384 0.04562 0.03748 -0.0126 0.0147 1.0000
11.500 1.1415 0.04809 0.04013 -0.0113 0.0144 1.0000
11.750 1.1422 0.05092 0.04312 -0.0101 0.0141 1.0000
12.000 1.1423 0.05394 0.04634 -0.0091 0.0139 1.0000
12.250 1.1403 0.05727 0.04989 -0.0083 0.0137 1.0000
12.500 1.1351 0.06104 0.05390 -0.0078 0.0136 1.0000
12.750 1.1282 0.06498 0.05810 -0.0077 0.0135 1.0000
13.000 1.1188 0.06933 0.06271 -0.0082 0.0135 1.0000
13.250 1.1069 0.07419 0.06782 -0.0093 0.0135 1.0000
13.500 1.0925 0.07969 0.07357 -0.0112 0.0135 1.0000
13.750 1.0776 0.08561 0.07971 -0.0138 0.0135 1.0000
14.000 1.0623 0.09202 0.08632 -0.0170 0.0135 1.0000
14.250 1.0464 0.09906 0.09354 -0.0210 0.0136 1.0000
14.500 1.0279 0.10733 0.10199 -0.0261 0.0136 1.0000
14.750 1.0108 0.11608 0.11095 -0.0318 0.0138 1.0000
15.000 0.9822 0.12943 0.12454 -0.0406 0.0142 1.0000
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Polar data table (+)
Polar graphs
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