AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AIRFOIL 3024 9.84% (s3024-il) Reynolds number: 100,000 Max Cl/Cd: 57.73 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3024-il-100000-n5.txt Download as CSV file: xf-s3024-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AIRFOIL 3024 9.84%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3345 0.09350 0.08882 -0.0397 1.0000 0.0522
-8.250 -0.3431 0.09116 0.08658 -0.0390 1.0000 0.0520
-8.000 -0.3575 0.08941 0.08494 -0.0371 1.0000 0.0515
-7.500 -0.3732 0.07796 0.07356 -0.0454 0.9882 0.0289
-7.250 -0.3574 0.07323 0.06881 -0.0509 0.9812 0.0280
-7.000 -0.3396 0.06731 0.06281 -0.0588 0.9742 0.0268
-6.500 -0.3107 0.04850 0.04328 -0.0765 0.9566 0.0232
-6.250 -0.2919 0.04400 0.03845 -0.0793 0.9499 0.0230
-6.000 -0.2699 0.03962 0.03362 -0.0818 0.9446 0.0228
-5.750 -0.2520 0.03573 0.02914 -0.0824 0.9369 0.0231
-5.500 -0.2256 0.03261 0.02556 -0.0839 0.9326 0.0241
-5.250 -0.2043 0.03095 0.02368 -0.0837 0.9259 0.0251
-5.000 -0.1778 0.02852 0.02078 -0.0840 0.9207 0.0255
-4.750 -0.1470 0.02629 0.01808 -0.0848 0.9172 0.0259
-4.500 -0.1252 0.02478 0.01624 -0.0837 0.9099 0.0264
-4.250 -0.0958 0.02328 0.01445 -0.0839 0.9054 0.0273
-4.000 -0.0650 0.02199 0.01293 -0.0843 0.9016 0.0285
-3.750 -0.0430 0.02110 0.01194 -0.0832 0.8942 0.0305
-3.500 -0.0138 0.02035 0.01113 -0.0835 0.8896 0.0346
-3.250 0.0119 0.01962 0.01026 -0.0829 0.8839 0.0382
-3.000 0.0370 0.01892 0.00951 -0.0824 0.8775 0.0441
-2.750 0.0663 0.01807 0.00871 -0.0824 0.8732 0.0653
-2.500 0.0883 0.01740 0.00834 -0.0815 0.8658 0.1313
-2.250 0.1141 0.01657 0.00811 -0.0815 0.8603 0.2645
-2.000 0.1402 0.01598 0.00789 -0.0812 0.8550 0.3814
-1.750 0.1620 0.01541 0.00779 -0.0799 0.8478 0.5294
-1.500 0.1860 0.01465 0.00770 -0.0779 0.8433 0.7349
-1.250 0.2580 0.01416 0.00733 -0.0854 0.8423 0.9664
-1.000 0.2984 0.01416 0.00713 -0.0882 0.8349 1.0000
-0.750 0.3242 0.01413 0.00691 -0.0875 0.8286 1.0000
-0.500 0.3457 0.01423 0.00685 -0.0863 0.8197 1.0000
-0.250 0.3720 0.01419 0.00665 -0.0857 0.8134 1.0000
0.000 0.3939 0.01429 0.00664 -0.0845 0.8041 1.0000
0.250 0.4209 0.01424 0.00645 -0.0840 0.7978 1.0000
0.500 0.4431 0.01434 0.00646 -0.0829 0.7878 1.0000
0.750 0.4688 0.01433 0.00635 -0.0822 0.7801 1.0000
1.000 0.4933 0.01436 0.00631 -0.0813 0.7707 1.0000
1.250 0.5175 0.01441 0.00630 -0.0804 0.7609 1.0000
1.500 0.5447 0.01434 0.00614 -0.0799 0.7529 1.0000
1.750 0.5682 0.01442 0.00619 -0.0789 0.7413 1.0000
2.000 0.5928 0.01447 0.00620 -0.0781 0.7302 1.0000
2.250 0.6184 0.01448 0.00617 -0.0774 0.7195 1.0000
2.500 0.6448 0.01446 0.00610 -0.0767 0.7088 1.0000
2.750 0.6692 0.01453 0.00617 -0.0759 0.6958 1.0000
3.000 0.6940 0.01460 0.00624 -0.0751 0.6824 1.0000
3.250 0.7190 0.01467 0.00630 -0.0744 0.6685 1.0000
3.500 0.7441 0.01475 0.00636 -0.0736 0.6540 1.0000
3.750 0.7691 0.01484 0.00646 -0.0728 0.6386 1.0000
4.000 0.7942 0.01494 0.00654 -0.0721 0.6224 1.0000
4.250 0.8189 0.01506 0.00664 -0.0713 0.6050 1.0000
4.500 0.8428 0.01524 0.00681 -0.0704 0.5860 1.0000
4.750 0.8668 0.01543 0.00700 -0.0695 0.5663 1.0000
5.000 0.8906 0.01566 0.00718 -0.0686 0.5457 1.0000
5.250 0.9136 0.01593 0.00745 -0.0676 0.5236 1.0000
5.500 0.9364 0.01624 0.00771 -0.0666 0.5015 1.0000
5.750 0.9583 0.01660 0.00807 -0.0655 0.4776 1.0000
6.000 0.9798 0.01699 0.00842 -0.0644 0.4535 1.0000
6.250 1.0007 0.01743 0.00882 -0.0632 0.4292 1.0000
6.500 1.0210 0.01790 0.00929 -0.0620 0.4044 1.0000
6.750 1.0406 0.01843 0.00978 -0.0607 0.3802 1.0000
7.000 1.0596 0.01899 0.01031 -0.0593 0.3564 1.0000
7.250 1.0782 0.01959 0.01089 -0.0579 0.3328 1.0000
7.500 1.0956 0.02024 0.01152 -0.0564 0.3104 1.0000
7.750 1.1132 0.02090 0.01220 -0.0550 0.2884 1.0000
8.000 1.1292 0.02163 0.01291 -0.0533 0.2676 1.0000
8.250 1.1452 0.02237 0.01367 -0.0518 0.2469 1.0000
8.500 1.1598 0.02317 0.01447 -0.0500 0.2269 1.0000
8.750 1.1727 0.02403 0.01534 -0.0481 0.2051 1.0000
9.000 1.1825 0.02498 0.01621 -0.0458 0.1819 1.0000
9.250 1.1919 0.02595 0.01715 -0.0436 0.1587 1.0000
9.500 1.2001 0.02705 0.01818 -0.0413 0.1367 1.0000
9.750 1.2084 0.02824 0.01932 -0.0393 0.1163 1.0000
10.000 1.2160 0.02954 0.02057 -0.0373 0.0955 1.0000
10.250 1.2229 0.03096 0.02198 -0.0354 0.0784 1.0000
10.500 1.2278 0.03259 0.02358 -0.0334 0.0605 1.0000
10.750 1.2301 0.03451 0.02544 -0.0314 0.0460 1.0000
11.000 1.2312 0.03659 0.02753 -0.0294 0.0370 1.0000
11.250 1.2314 0.03881 0.02983 -0.0276 0.0318 1.0000
11.500 1.2313 0.04111 0.03224 -0.0260 0.0290 1.0000
11.750 1.2288 0.04373 0.03496 -0.0246 0.0271 1.0000
12.000 1.2280 0.04628 0.03770 -0.0235 0.0257 1.0000
12.250 1.2267 0.04898 0.04058 -0.0226 0.0247 1.0000
12.500 1.2239 0.05196 0.04371 -0.0219 0.0236 1.0000
12.750 1.2209 0.05507 0.04699 -0.0216 0.0230 1.0000
13.000 1.2167 0.05846 0.05052 -0.0214 0.0223 1.0000
13.250 1.2112 0.06210 0.05428 -0.0216 0.0217 1.0000
13.500 1.2078 0.06570 0.05805 -0.0218 0.0210 1.0000
13.750 1.2054 0.06929 0.06183 -0.0222 0.0205 1.0000
14.000 1.2022 0.07312 0.06585 -0.0229 0.0198 1.0000
14.250 1.1984 0.07718 0.07009 -0.0238 0.0192 1.0000
14.500 1.1945 0.08136 0.07444 -0.0249 0.0188 1.0000
14.750 1.1897 0.08582 0.07906 -0.0263 0.0184 1.0000
15.000 1.1842 0.09054 0.08394 -0.0280 0.0180 1.0000
15.250 1.1791 0.09532 0.08889 -0.0297 0.0179 1.0000
15.500 1.1732 0.10037 0.09410 -0.0317 0.0177 1.0000
15.750 1.1664 0.10570 0.09959 -0.0340 0.0175 1.0000
16.000 1.1590 0.11138 0.10544 -0.0367 0.0174 1.0000
16.250 1.1504 0.11745 0.11169 -0.0397 0.0173 1.0000
16.500 1.1404 0.12409 0.11852 -0.0433 0.0173 1.0000
16.750 1.1286 0.13140 0.12601 -0.0475 0.0173 1.0000
17.000 1.1138 0.13989 0.13471 -0.0526 0.0173 1.0000
17.250 1.0924 0.15083 0.14587 -0.0594 0.0176 1.0000
17.500 1.0565 0.16748 0.16276 -0.0696 0.0182 1.0000
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