SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 100,000 Max Cl/Cd: 58.06 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2083-il-100000.txt Download as CSV file: xf-sd2083-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3910 0.10660 0.10164 -0.0302 1.0000 0.0853
-9.250 -0.4009 0.10461 0.09975 -0.0343 1.0000 0.0877
-9.000 -0.4165 0.10287 0.09814 -0.0391 1.0000 0.0883
-8.750 -0.3958 0.09692 0.09217 -0.0357 1.0000 0.0904
-8.500 -0.3839 0.09361 0.08886 -0.0342 1.0000 0.0940
-8.250 -0.3837 0.09087 0.08619 -0.0347 1.0000 0.0971
-8.000 -0.3944 0.08860 0.08404 -0.0359 1.0000 0.1001
-7.750 -0.4206 0.08732 0.08293 -0.0363 1.0000 0.1014
-7.500 -0.4472 0.08575 0.08144 -0.0382 1.0000 0.1021
-7.250 -0.4723 0.08419 0.07984 -0.0396 1.0000 0.1025
-7.000 -0.4469 0.07957 0.07539 -0.0311 1.0000 0.1057
-6.750 -0.4510 0.07750 0.07337 -0.0287 1.0000 0.1081
-6.500 -0.4593 0.07511 0.07100 -0.0280 1.0000 0.1118
-6.250 -0.4814 0.07220 0.06781 -0.0349 1.0000 0.1169
-6.000 -0.4729 0.06860 0.06443 -0.0299 1.0000 0.1190
-5.750 -0.4691 0.06633 0.06219 -0.0274 1.0000 0.1227
-5.500 -0.4695 0.06253 0.05815 -0.0310 1.0000 0.1321
-5.250 -0.4624 0.06003 0.05576 -0.0279 1.0000 0.1357
-5.000 -0.4555 0.05674 0.05227 -0.0294 1.0000 0.1471
-4.750 -0.4462 0.05416 0.04954 -0.0294 1.0000 0.1608
-4.500 -0.4359 0.05171 0.04703 -0.0286 1.0000 0.1752
-4.250 -0.4250 0.04933 0.04465 -0.0273 1.0000 0.1905
-4.000 -0.4123 0.04697 0.04226 -0.0263 1.0000 0.2060
-3.750 -0.3538 0.03469 0.02791 -0.0331 1.0000 0.0859
-3.500 -0.3273 0.03091 0.02339 -0.0324 1.0000 0.0720
-3.250 -0.2999 0.02824 0.02028 -0.0324 0.9989 0.0678
-3.000 -0.2609 0.02593 0.01732 -0.0340 0.9949 0.0652
-2.750 -0.2248 0.02444 0.01547 -0.0354 0.9902 0.0660
-2.500 -0.1867 0.02354 0.01436 -0.0374 0.9852 0.0722
-2.250 -0.1514 0.02242 0.01308 -0.0387 0.9803 0.0760
-2.000 -0.1168 0.02147 0.01222 -0.0400 0.9746 0.0851
-1.750 -0.0798 0.02049 0.01141 -0.0418 0.9700 0.1198
-1.500 -0.0242 0.01698 0.01113 -0.0463 0.9703 1.0000
-1.250 0.0077 0.01727 0.01105 -0.0476 0.9621 1.0000
-1.000 0.0482 0.01772 0.01115 -0.0505 0.9557 1.0000
-0.750 0.0804 0.01803 0.01123 -0.0519 0.9473 1.0000
-0.500 0.1168 0.01842 0.01140 -0.0540 0.9400 1.0000
-0.250 0.1532 0.01876 0.01154 -0.0561 0.9319 1.0000
0.000 0.1851 0.01910 0.01173 -0.0573 0.9231 1.0000
0.250 0.2279 0.01942 0.01192 -0.0604 0.9162 1.0000
0.500 0.2560 0.01971 0.01212 -0.0608 0.9059 1.0000
0.750 0.2942 0.01998 0.01230 -0.0629 0.8978 1.0000
1.000 0.3327 0.02016 0.01242 -0.0650 0.8890 1.0000
1.250 0.3629 0.02039 0.01261 -0.0656 0.8784 1.0000
1.500 0.4176 0.02031 0.01252 -0.0703 0.8726 1.0000
1.750 0.4466 0.02042 0.01262 -0.0705 0.8608 1.0000
2.000 0.4791 0.02046 0.01267 -0.0711 0.8496 1.0000
2.250 0.5189 0.02028 0.01253 -0.0726 0.8404 1.0000
2.500 0.5593 0.01993 0.01222 -0.0740 0.8312 1.0000
2.750 0.5886 0.01978 0.01212 -0.0736 0.8189 1.0000
3.000 0.6190 0.01955 0.01196 -0.0732 0.8068 1.0000
3.250 0.6502 0.01922 0.01170 -0.0728 0.7950 1.0000
3.500 0.6823 0.01879 0.01135 -0.0723 0.7835 1.0000
3.750 0.7146 0.01828 0.01094 -0.0718 0.7719 1.0000
4.000 0.7424 0.01789 0.01064 -0.0706 0.7573 1.0000
4.250 0.7683 0.01755 0.01038 -0.0692 0.7403 1.0000
4.500 0.7956 0.01710 0.01002 -0.0678 0.7223 1.0000
4.750 0.8248 0.01656 0.00957 -0.0665 0.7033 1.0000
5.000 0.8488 0.01628 0.00936 -0.0647 0.6779 1.0000
5.250 0.8736 0.01600 0.00911 -0.0630 0.6490 1.0000
5.500 0.8968 0.01587 0.00898 -0.0611 0.6139 1.0000
5.750 0.9188 0.01591 0.00898 -0.0592 0.5717 1.0000
6.000 0.9389 0.01617 0.00911 -0.0571 0.5228 1.0000
6.250 0.9572 0.01668 0.00941 -0.0549 0.4707 1.0000
6.500 0.9740 0.01742 0.00987 -0.0527 0.4199 1.0000
6.750 0.9899 0.01827 0.01052 -0.0506 0.3720 1.0000
7.000 1.0052 0.01921 0.01130 -0.0485 0.3280 1.0000
7.250 1.0200 0.02023 0.01214 -0.0464 0.2875 1.0000
7.500 1.0338 0.02135 0.01305 -0.0443 0.2493 1.0000
7.750 1.0462 0.02245 0.01404 -0.0421 0.2104 1.0000
8.000 1.0558 0.02349 0.01494 -0.0397 0.1698 1.0000
8.250 1.0644 0.02469 0.01595 -0.0373 0.1285 1.0000
8.500 1.0681 0.02671 0.01766 -0.0342 0.0883 1.0000
8.750 1.0725 0.02897 0.01976 -0.0310 0.0637 1.0000
9.000 1.0833 0.03110 0.02188 -0.0286 0.0532 1.0000
9.250 1.1044 0.03382 0.02463 -0.0276 0.0477 1.0000
9.500 1.1272 0.03618 0.02718 -0.0267 0.0438 1.0000
9.750 1.1485 0.03891 0.02991 -0.0263 0.0403 1.0000
10.000 1.1656 0.04206 0.03340 -0.0251 0.0381 1.0000
10.250 1.1787 0.04513 0.03688 -0.0233 0.0373 1.0000
10.500 1.1859 0.04852 0.04070 -0.0211 0.0371 1.0000
10.750 1.1866 0.05202 0.04464 -0.0185 0.0370 1.0000
11.000 1.1812 0.05542 0.04840 -0.0154 0.0372 1.0000
11.250 1.1714 0.05883 0.05212 -0.0124 0.0374 1.0000
11.500 1.1580 0.06245 0.05602 -0.0097 0.0376 1.0000
11.750 1.1422 0.06635 0.06019 -0.0077 0.0379 1.0000
12.000 1.1257 0.07050 0.06456 -0.0065 0.0382 1.0000
12.250 1.1074 0.07510 0.06938 -0.0061 0.0385 1.0000
12.500 1.0890 0.08018 0.07463 -0.0065 0.0388 1.0000
12.750 1.0705 0.08590 0.08051 -0.0078 0.0391 1.0000
13.000 1.0548 0.09150 0.08628 -0.0095 0.0395 1.0000
13.250 1.0313 0.09745 0.09242 -0.0131 0.0399 1.0000
13.500 0.9924 0.10742 0.10261 -0.0211 0.0408 1.0000
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Polar data table (+)
Polar graphs
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