SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 100,000 Max Cl/Cd: 56.31 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3002-il-100000.txt Download as CSV file: xf-s3002-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3551 0.10261 0.09761 -0.0312 1.0000 0.0908
-8.750 -0.3698 0.10080 0.09592 -0.0355 1.0000 0.0932
-8.500 -0.3885 0.09902 0.09428 -0.0390 1.0000 0.0937
-8.250 -0.3544 0.09321 0.08841 -0.0336 1.0000 0.0978
-8.000 -0.3506 0.09053 0.08579 -0.0330 1.0000 0.1014
-7.750 -0.3575 0.08816 0.08352 -0.0335 1.0000 0.1050
-7.500 -0.3815 0.08666 0.08219 -0.0342 1.0000 0.1071
-7.250 -0.4098 0.08443 0.08009 -0.0390 1.0000 0.1081
-7.000 -0.4373 0.08263 0.07822 -0.0422 1.0000 0.1086
-6.750 -0.4056 0.07854 0.07435 -0.0312 1.0000 0.1122
-6.500 -0.4102 0.07651 0.07239 -0.0290 1.0000 0.1151
-6.250 -0.4199 0.07407 0.06999 -0.0292 1.0000 0.1185
-6.000 -0.4402 0.07011 0.06580 -0.0376 1.0000 0.1243
-5.750 -0.4334 0.06731 0.06318 -0.0327 1.0000 0.1265
-5.500 -0.4292 0.06516 0.06108 -0.0304 1.0000 0.1306
-5.250 -0.4262 0.06102 0.05674 -0.0351 1.0000 0.1408
-5.000 -0.4187 0.05876 0.05457 -0.0325 1.0000 0.1450
-4.750 -0.4079 0.05526 0.05091 -0.0352 1.0000 0.1573
-4.500 -0.3943 0.05242 0.04792 -0.0368 1.0000 0.1717
-4.250 -0.3814 0.05014 0.04567 -0.0357 1.0000 0.1811
-4.000 -0.3639 0.04733 0.04277 -0.0370 0.9992 0.2043
-3.750 -0.2773 0.03309 0.02601 -0.0496 0.9984 0.0786
-3.500 -0.2342 0.02919 0.02166 -0.0530 0.9946 0.0728
-3.250 -0.1911 0.02654 0.01838 -0.0556 0.9896 0.0709
-3.000 -0.1472 0.02511 0.01662 -0.0586 0.9843 0.0760
-2.750 -0.1076 0.02372 0.01489 -0.0605 0.9777 0.0786
-2.500 -0.0647 0.02246 0.01365 -0.0634 0.9722 0.0875
-2.250 -0.0284 0.02143 0.01262 -0.0649 0.9645 0.0971
-2.000 0.0155 0.02057 0.01191 -0.0680 0.9583 0.1206
-1.750 0.0473 0.01766 0.01122 -0.0695 0.9519 0.5242
-1.500 0.0664 0.01777 0.01200 -0.0650 0.9432 0.8045
-1.250 0.0770 0.01772 0.01201 -0.0597 0.9316 0.8812
-1.000 0.1334 0.01743 0.01164 -0.0632 0.9256 1.0000
-0.750 0.1733 0.01749 0.01146 -0.0660 0.9151 1.0000
-0.500 0.2120 0.01756 0.01133 -0.0684 0.9045 1.0000
-0.250 0.2652 0.01749 0.01107 -0.0731 0.8976 1.0000
0.000 0.3010 0.01750 0.01095 -0.0748 0.8858 1.0000
0.250 0.3437 0.01742 0.01075 -0.0774 0.8764 1.0000
0.500 0.3873 0.01723 0.01045 -0.0799 0.8675 1.0000
0.750 0.4210 0.01718 0.01033 -0.0808 0.8552 1.0000
1.000 0.4575 0.01703 0.01011 -0.0819 0.8443 1.0000
1.250 0.4974 0.01673 0.00974 -0.0833 0.8349 1.0000
1.500 0.5276 0.01663 0.00960 -0.0832 0.8212 1.0000
1.750 0.5582 0.01651 0.00943 -0.0831 0.8074 1.0000
2.000 0.5886 0.01636 0.00924 -0.0829 0.7932 1.0000
2.250 0.6187 0.01619 0.00904 -0.0825 0.7784 1.0000
2.500 0.6482 0.01602 0.00883 -0.0820 0.7628 1.0000
2.750 0.6773 0.01585 0.00862 -0.0814 0.7463 1.0000
3.000 0.7063 0.01568 0.00839 -0.0808 0.7289 1.0000
3.250 0.7353 0.01551 0.00815 -0.0801 0.7109 1.0000
3.500 0.7612 0.01551 0.00815 -0.0792 0.6881 1.0000
3.750 0.7890 0.01544 0.00799 -0.0784 0.6667 1.0000
4.000 0.8150 0.01550 0.00800 -0.0776 0.6418 1.0000
4.250 0.8418 0.01557 0.00796 -0.0768 0.6171 1.0000
4.500 0.8675 0.01574 0.00804 -0.0759 0.5901 1.0000
4.750 0.8925 0.01600 0.00820 -0.0750 0.5618 1.0000
5.000 0.9172 0.01632 0.00841 -0.0742 0.5334 1.0000
5.250 0.9415 0.01672 0.00870 -0.0733 0.5051 1.0000
5.500 0.9656 0.01718 0.00903 -0.0725 0.4776 1.0000
5.750 0.9894 0.01770 0.00939 -0.0716 0.4510 1.0000
6.000 1.0124 0.01827 0.00988 -0.0707 0.4237 1.0000
6.250 1.0352 0.01888 0.01043 -0.0699 0.3977 1.0000
6.500 1.0580 0.01955 0.01095 -0.0691 0.3737 1.0000
6.750 1.0799 0.02022 0.01159 -0.0681 0.3488 1.0000
7.000 1.1018 0.02097 0.01225 -0.0673 0.3260 1.0000
7.250 1.1230 0.02171 0.01295 -0.0663 0.3031 1.0000
7.500 1.1442 0.02254 0.01368 -0.0654 0.2822 1.0000
7.750 1.1643 0.02335 0.01451 -0.0643 0.2609 1.0000
8.000 1.1845 0.02423 0.01534 -0.0633 0.2417 1.0000
8.250 1.2045 0.02523 0.01622 -0.0624 0.2236 1.0000
8.500 1.2234 0.02623 0.01728 -0.0612 0.2060 1.0000
8.750 1.2422 0.02731 0.01839 -0.0601 0.1897 1.0000
9.000 1.2609 0.02849 0.01958 -0.0590 0.1751 1.0000
9.250 1.2797 0.02977 0.02085 -0.0579 0.1620 1.0000
9.500 1.2989 0.03113 0.02217 -0.0570 0.1502 1.0000
9.750 1.3182 0.03250 0.02354 -0.0561 0.1397 1.0000
10.000 1.3351 0.03407 0.02535 -0.0548 0.1304 1.0000
10.250 1.3551 0.03579 0.02704 -0.0541 0.1224 1.0000
10.500 1.3714 0.03739 0.02885 -0.0528 0.1154 1.0000
10.750 1.3911 0.03950 0.03100 -0.0522 0.1093 1.0000
11.000 1.4028 0.04129 0.03312 -0.0504 0.1038 1.0000
11.250 1.4280 0.04380 0.03545 -0.0507 0.0984 1.0000
11.500 1.4307 0.04601 0.03820 -0.0480 0.0953 1.0000
11.750 1.4371 0.04823 0.04073 -0.0460 0.0915 1.0000
12.000 1.4502 0.05023 0.04278 -0.0449 0.0877 1.0000
12.250 1.4581 0.05383 0.04657 -0.0437 0.0852 1.0000
12.500 1.4451 0.05668 0.04988 -0.0400 0.0839 1.0000
12.750 1.4285 0.05976 0.05331 -0.0366 0.0828 1.0000
13.000 1.4098 0.06328 0.05716 -0.0340 0.0818 1.0000
13.250 1.3885 0.06735 0.06153 -0.0323 0.0811 1.0000
13.500 1.3633 0.07224 0.06672 -0.0316 0.0808 1.0000
13.750 1.3324 0.07829 0.07305 -0.0323 0.0810 1.0000
14.000 1.2950 0.08598 0.08101 -0.0348 0.0818 1.0000
14.250 1.2532 0.09551 0.09077 -0.0395 0.0831 1.0000
14.500 1.2109 0.10677 0.10218 -0.0460 0.0845 1.0000
14.750 1.1721 0.11924 0.11474 -0.0535 0.0856 1.0000
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Polar data table (+)
Polar graphs
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