S3021-095-84 (s3021-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 100,000 Max Cl/Cd: 53.71 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3021-il-100000.txt Download as CSV file: xf-s3021-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S3021-095-84
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3970 0.10551 0.10059 -0.0228 1.0000 0.0898
-9.000 -0.4136 0.10389 0.09910 -0.0284 1.0000 0.0917
-8.750 -0.4298 0.10176 0.09709 -0.0332 1.0000 0.0921
-8.500 -0.3899 0.09522 0.09045 -0.0260 1.0000 0.0960
-8.250 -0.3846 0.09223 0.08749 -0.0262 1.0000 0.0996
-8.000 -0.3887 0.08946 0.08480 -0.0281 1.0000 0.1033
-7.750 -0.4126 0.08731 0.08282 -0.0336 1.0000 0.1055
-7.500 -0.4210 0.08305 0.07863 -0.0375 1.0000 0.1068
-7.250 -0.3990 0.08002 0.07563 -0.0306 1.0000 0.1102
-7.000 -0.3972 0.07721 0.07287 -0.0307 1.0000 0.1144
-6.750 -0.4271 0.07453 0.07003 -0.0414 1.0000 0.1203
-6.500 -0.4095 0.07017 0.06593 -0.0354 1.0000 0.1226
-6.250 -0.4033 0.06804 0.06387 -0.0324 1.0000 0.1276
-6.000 -0.4198 0.06494 0.06059 -0.0368 1.0000 0.1353
-5.750 -0.4120 0.06265 0.05852 -0.0313 1.0000 0.1389
-5.500 -0.4217 0.06034 0.05603 -0.0326 1.0000 0.1498
-5.250 -0.4186 0.05814 0.05399 -0.0285 1.0000 0.1527
-5.000 -0.4202 0.05592 0.05162 -0.0287 1.0000 0.1648
-4.750 -0.4160 0.05389 0.04971 -0.0255 1.0000 0.1689
-4.250 -0.3364 0.03965 0.03343 -0.0393 0.9889 0.1060
-4.000 -0.2963 0.03163 0.02477 -0.0417 0.9845 0.0717
-3.750 -0.2550 0.02831 0.02049 -0.0435 0.9766 0.0638
-3.500 -0.2117 0.02567 0.01740 -0.0464 0.9707 0.0624
-3.250 -0.1730 0.02399 0.01531 -0.0482 0.9617 0.0638
-3.000 -0.1313 0.02223 0.01336 -0.0508 0.9549 0.0675
-2.750 -0.0919 0.02092 0.01204 -0.0528 0.9464 0.0723
-2.500 -0.0538 0.01981 0.01087 -0.0545 0.9379 0.0796
-2.250 -0.0129 0.01852 0.00978 -0.0568 0.9305 0.1096
-2.000 0.0729 0.01476 0.00934 -0.0660 0.9363 1.0000
-1.750 0.1265 0.01467 0.00880 -0.0711 0.9294 1.0000
-1.500 0.1649 0.01463 0.00846 -0.0733 0.9179 1.0000
-1.250 0.2034 0.01459 0.00817 -0.0754 0.9072 1.0000
-1.000 0.2458 0.01447 0.00783 -0.0781 0.8985 1.0000
-0.750 0.2793 0.01444 0.00761 -0.0790 0.8871 1.0000
-0.500 0.3084 0.01448 0.00750 -0.0790 0.8747 1.0000
-0.250 0.3366 0.01453 0.00741 -0.0789 0.8627 1.0000
0.000 0.3643 0.01458 0.00734 -0.0785 0.8512 1.0000
0.250 0.3924 0.01461 0.00724 -0.0781 0.8403 1.0000
0.500 0.4176 0.01470 0.00722 -0.0772 0.8283 1.0000
0.750 0.4406 0.01486 0.00730 -0.0759 0.8154 1.0000
1.000 0.4639 0.01502 0.00738 -0.0747 0.8027 1.0000
1.250 0.4875 0.01518 0.00747 -0.0735 0.7903 1.0000
1.500 0.5115 0.01532 0.00754 -0.0724 0.7783 1.0000
1.750 0.5361 0.01544 0.00760 -0.0712 0.7665 1.0000
2.000 0.5610 0.01555 0.00764 -0.0701 0.7548 1.0000
2.250 0.5841 0.01575 0.00780 -0.0689 0.7415 1.0000
2.500 0.6076 0.01594 0.00797 -0.0678 0.7284 1.0000
2.750 0.6313 0.01612 0.00815 -0.0666 0.7152 1.0000
3.000 0.6552 0.01630 0.00831 -0.0655 0.7019 1.0000
3.250 0.6794 0.01647 0.00846 -0.0644 0.6884 1.0000
3.500 0.7037 0.01663 0.00861 -0.0633 0.6747 1.0000
3.750 0.7280 0.01678 0.00878 -0.0622 0.6606 1.0000
4.000 0.7523 0.01692 0.00893 -0.0611 0.6459 1.0000
4.250 0.7767 0.01705 0.00907 -0.0600 0.6307 1.0000
4.500 0.8011 0.01718 0.00920 -0.0590 0.6149 1.0000
4.750 0.8256 0.01729 0.00934 -0.0579 0.5986 1.0000
5.000 0.8503 0.01738 0.00942 -0.0568 0.5819 1.0000
5.250 0.8739 0.01753 0.00960 -0.0556 0.5635 1.0000
5.500 0.8970 0.01768 0.00979 -0.0544 0.5436 1.0000
5.750 0.9213 0.01779 0.00991 -0.0532 0.5241 1.0000
6.000 0.9435 0.01800 0.01017 -0.0519 0.5017 1.0000
6.250 0.9670 0.01818 0.01029 -0.0507 0.4801 1.0000
6.500 0.9881 0.01846 0.01063 -0.0493 0.4549 1.0000
6.750 1.0093 0.01879 0.01100 -0.0479 0.4295 1.0000
7.000 1.0299 0.01919 0.01137 -0.0464 0.4033 1.0000
7.250 1.0499 0.01968 0.01183 -0.0449 0.3767 1.0000
7.500 1.0689 0.02025 0.01236 -0.0434 0.3494 1.0000
7.750 1.0871 0.02092 0.01300 -0.0418 0.3219 1.0000
8.000 1.1043 0.02170 0.01371 -0.0401 0.2946 1.0000
8.250 1.1196 0.02251 0.01448 -0.0382 0.2663 1.0000
8.500 1.1326 0.02331 0.01526 -0.0362 0.2373 1.0000
8.750 1.1437 0.02411 0.01606 -0.0340 0.2080 1.0000
9.000 1.1537 0.02500 0.01695 -0.0318 0.1794 1.0000
9.250 1.1621 0.02603 0.01801 -0.0295 0.1497 1.0000
9.500 1.1659 0.02750 0.01936 -0.0268 0.1172 1.0000
9.750 1.1582 0.02982 0.02140 -0.0227 0.0800 1.0000
10.000 1.1504 0.03232 0.02371 -0.0188 0.0641 1.0000
10.250 1.1492 0.03457 0.02595 -0.0159 0.0550 1.0000
10.500 1.1547 0.03680 0.02826 -0.0136 0.0500 1.0000
10.750 1.1630 0.03890 0.03039 -0.0118 0.0461 1.0000
11.000 1.1779 0.04165 0.03309 -0.0106 0.0426 1.0000
11.250 1.1895 0.04381 0.03552 -0.0092 0.0403 1.0000
11.500 1.1996 0.04616 0.03808 -0.0079 0.0382 1.0000
11.750 1.2075 0.04871 0.04081 -0.0066 0.0365 1.0000
12.000 1.2163 0.05168 0.04402 -0.0055 0.0357 1.0000
12.250 1.2207 0.05494 0.04752 -0.0044 0.0352 1.0000
12.500 1.2199 0.05855 0.05139 -0.0034 0.0349 1.0000
12.750 1.2131 0.06231 0.05545 -0.0026 0.0349 1.0000
13.000 1.2021 0.06636 0.05979 -0.0022 0.0350 1.0000
13.250 1.1868 0.07097 0.06470 -0.0025 0.0351 1.0000
13.500 1.1677 0.07618 0.07022 -0.0037 0.0355 1.0000
13.750 1.1455 0.08214 0.07645 -0.0059 0.0358 1.0000
14.000 1.1174 0.08929 0.08389 -0.0095 0.0363 1.0000
14.250 1.0827 0.09833 0.09322 -0.0151 0.0371 1.0000
14.500 1.0467 0.10902 0.10410 -0.0223 0.0380 1.0000
14.750 1.0073 0.12239 0.11763 -0.0316 0.0393 1.0000
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Polar data table (+)
Polar graphs
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