S3021-095-84 (s3021-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3021-095-84 (s3021-il) Reynolds number: 200,000 Max Cl/Cd: 74.57 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3021-il-200000.txt Download as CSV file: xf-s3021-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3155 0.08651 0.08328 -0.0309 1.0000 0.0511
-8.750 -0.3245 0.08283 0.07965 -0.0345 1.0000 0.0517
-8.500 -0.3333 0.07889 0.07578 -0.0376 1.0000 0.0520
-8.250 -0.3412 0.07494 0.07188 -0.0403 1.0000 0.0521
-8.000 -0.3542 0.07102 0.06801 -0.0431 1.0000 0.0521
-7.750 -0.4130 0.07822 0.07499 -0.0422 1.0000 0.0518
-7.500 -0.4180 0.07412 0.07082 -0.0455 1.0000 0.0521
-7.250 -0.4255 0.06819 0.06492 -0.0460 1.0000 0.0528
-7.000 -0.4193 0.06565 0.06250 -0.0428 1.0000 0.0538
-6.750 -0.4164 0.06362 0.06050 -0.0405 1.0000 0.0549
-6.500 -0.4171 0.06133 0.05823 -0.0388 1.0000 0.0560
-6.250 -0.4217 0.05909 0.05600 -0.0369 1.0000 0.0572
-6.000 -0.4216 0.05639 0.05326 -0.0364 0.9989 0.0590
-5.750 -0.3848 0.04781 0.04405 -0.0478 0.9897 0.0665
-5.500 -0.3520 0.04457 0.04087 -0.0509 0.9848 0.0693
-5.250 -0.2617 0.02284 0.01905 -0.0623 0.9625 0.0821
-5.000 -0.2278 0.01882 0.01457 -0.0663 0.9571 0.0942
-4.750 -0.1974 0.01712 0.01267 -0.0675 0.9467 0.1050
-4.500 -0.2063 0.02323 0.01679 -0.0624 0.9575 0.0415
-4.250 -0.1713 0.02143 0.01470 -0.0634 0.9485 0.0395
-4.000 -0.1326 0.01884 0.01177 -0.0654 0.9435 0.0382
-3.750 -0.0999 0.01722 0.00994 -0.0659 0.9333 0.0378
-3.500 -0.0656 0.01589 0.00848 -0.0667 0.9246 0.0383
-3.250 -0.0327 0.01484 0.00733 -0.0672 0.9153 0.0395
-3.000 -0.0048 0.01387 0.00631 -0.0668 0.9031 0.0414
-2.750 0.0223 0.01318 0.00561 -0.0664 0.8908 0.0481
-2.500 0.0490 0.01255 0.00490 -0.0658 0.8786 0.0569
-2.250 0.0713 0.01117 0.00429 -0.0648 0.8665 0.2342
-2.000 0.0932 0.01035 0.00413 -0.0637 0.8547 0.4206
-1.750 0.1094 0.00941 0.00411 -0.0609 0.8427 0.6659
-1.500 0.1767 0.00890 0.00417 -0.0668 0.8347 0.9656
-1.250 0.2466 0.00881 0.00380 -0.0753 0.8259 1.0000
-1.000 0.2692 0.00885 0.00366 -0.0742 0.8131 1.0000
-0.750 0.2919 0.00891 0.00356 -0.0731 0.8002 1.0000
-0.500 0.3151 0.00899 0.00349 -0.0721 0.7878 1.0000
-0.250 0.3386 0.00907 0.00344 -0.0711 0.7760 1.0000
0.000 0.3623 0.00916 0.00339 -0.0702 0.7646 1.0000
0.250 0.3864 0.00926 0.00335 -0.0692 0.7538 1.0000
0.500 0.4103 0.00936 0.00335 -0.0683 0.7420 1.0000
0.750 0.4343 0.00946 0.00337 -0.0675 0.7303 1.0000
1.000 0.4586 0.00957 0.00339 -0.0666 0.7191 1.0000
1.250 0.4831 0.00968 0.00340 -0.0658 0.7085 1.0000
1.500 0.5077 0.00980 0.00343 -0.0650 0.6975 1.0000
1.750 0.5320 0.00991 0.00351 -0.0642 0.6858 1.0000
2.000 0.5565 0.01004 0.00358 -0.0634 0.6745 1.0000
2.250 0.5812 0.01016 0.00365 -0.0627 0.6634 1.0000
2.500 0.6061 0.01029 0.00370 -0.0619 0.6525 1.0000
2.750 0.6306 0.01041 0.00381 -0.0611 0.6402 1.0000
3.000 0.6552 0.01054 0.00392 -0.0604 0.6278 1.0000
3.250 0.6798 0.01067 0.00402 -0.0596 0.6151 1.0000
3.500 0.7045 0.01080 0.00413 -0.0589 0.6021 1.0000
3.750 0.7291 0.01093 0.00426 -0.0581 0.5887 1.0000
4.000 0.7537 0.01107 0.00439 -0.0573 0.5746 1.0000
4.250 0.7782 0.01121 0.00452 -0.0566 0.5597 1.0000
4.500 0.8025 0.01136 0.00466 -0.0558 0.5440 1.0000
4.750 0.8268 0.01152 0.00484 -0.0550 0.5276 1.0000
5.000 0.8508 0.01170 0.00499 -0.0542 0.5103 1.0000
5.250 0.8746 0.01190 0.00519 -0.0533 0.4913 1.0000
5.500 0.8981 0.01211 0.00540 -0.0525 0.4707 1.0000
5.750 0.9212 0.01237 0.00565 -0.0515 0.4494 1.0000
6.000 0.9440 0.01266 0.00592 -0.0506 0.4262 1.0000
6.250 0.9664 0.01299 0.00623 -0.0496 0.4021 1.0000
6.500 0.9882 0.01337 0.00657 -0.0486 0.3774 1.0000
6.750 1.0094 0.01381 0.00697 -0.0475 0.3518 1.0000
7.000 1.0298 0.01429 0.00739 -0.0463 0.3233 1.0000
7.250 1.0495 0.01483 0.00784 -0.0451 0.2922 1.0000
7.500 1.0686 0.01542 0.00834 -0.0438 0.2597 1.0000
7.750 1.0869 0.01608 0.00891 -0.0425 0.2275 1.0000
8.000 1.1056 0.01674 0.00951 -0.0413 0.2006 1.0000
8.250 1.1232 0.01748 0.01016 -0.0399 0.1718 1.0000
8.500 1.1400 0.01828 0.01086 -0.0385 0.1438 1.0000
8.750 1.1556 0.01920 0.01166 -0.0370 0.1148 1.0000
9.000 1.1640 0.02074 0.01286 -0.0346 0.0638 1.0000
9.250 1.1641 0.02292 0.01476 -0.0310 0.0337 1.0000
9.500 1.1732 0.02416 0.01609 -0.0285 0.0279 1.0000
9.750 1.1724 0.02581 0.01780 -0.0248 0.0251 1.0000
10.000 1.1780 0.02709 0.01922 -0.0220 0.0240 1.0000
10.250 1.1820 0.02856 0.02082 -0.0194 0.0228 1.0000
10.500 1.1857 0.03017 0.02254 -0.0171 0.0220 1.0000
10.750 1.1890 0.03194 0.02440 -0.0150 0.0212 1.0000
11.000 1.1921 0.03385 0.02641 -0.0132 0.0205 1.0000
11.250 1.1959 0.03588 0.02852 -0.0117 0.0200 1.0000
11.500 1.2008 0.03802 0.03075 -0.0102 0.0197 1.0000
11.750 1.2067 0.04046 0.03329 -0.0088 0.0192 1.0000
12.000 1.2163 0.04291 0.03586 -0.0075 0.0189 1.0000
12.250 1.2266 0.04563 0.03874 -0.0064 0.0188 1.0000
12.500 1.2339 0.04919 0.04254 -0.0052 0.0185 1.0000
12.750 1.2328 0.05187 0.04544 -0.0044 0.0184 1.0000
13.000 1.2312 0.05504 0.04883 -0.0038 0.0183 1.0000
13.250 1.2251 0.05816 0.05219 -0.0037 0.0180 1.0000
13.500 1.2179 0.06181 0.05609 -0.0039 0.0178 1.0000
13.750 1.2084 0.06597 0.06048 -0.0046 0.0177 1.0000
14.000 1.1977 0.07069 0.06542 -0.0056 0.0178 1.0000
14.250 1.1839 0.07576 0.07072 -0.0073 0.0178 1.0000
14.500 1.1690 0.08143 0.07660 -0.0094 0.0179 1.0000
14.750 1.1524 0.08759 0.08297 -0.0122 0.0180 1.0000
15.000 1.1349 0.09430 0.08987 -0.0156 0.0181 1.0000
15.250 1.1170 0.10150 0.09724 -0.0195 0.0182 1.0000
15.500 1.0977 0.10944 0.10535 -0.0241 0.0184 1.0000
15.750 1.0780 0.11800 0.11407 -0.0292 0.0185 1.0000
16.000 1.0656 0.12542 0.12165 -0.0341 0.0186 1.0000
16.250 1.0499 0.13426 0.13063 -0.0403 0.0188 1.0000
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Polar data table (+)
Polar graphs
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