S4022 (s4022-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 100,000 Max Cl/Cd: 64.68 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4022-il-100000.txt Download as CSV file: xf-s4022-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4022
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4121 0.10349 0.09935 -0.0276 1.0000 0.0984
-7.250 -0.4408 0.10289 0.09887 -0.0260 1.0000 0.0990
-7.000 -0.4653 0.10124 0.09733 -0.0280 1.0000 0.0995
-6.750 -0.4708 0.09734 0.09351 -0.0273 1.0000 0.1006
-6.500 -0.4539 0.09512 0.09126 -0.0196 1.0000 0.1041
-6.250 -0.4593 0.09298 0.08918 -0.0185 1.0000 0.1070
-6.000 -0.4688 0.09017 0.08643 -0.0206 1.0000 0.1107
-5.750 -0.4779 0.08310 0.07933 -0.0352 1.0000 0.1149
-5.500 -0.4713 0.08215 0.07847 -0.0272 0.9994 0.1174
-5.250 -0.4376 0.07438 0.07053 -0.0436 0.9923 0.1299
-5.000 -0.4136 0.07186 0.06803 -0.0439 0.9868 0.1380
-4.750 -0.3782 0.06501 0.06093 -0.0577 0.9802 0.1583
-4.500 -0.3536 0.06239 0.05830 -0.0587 0.9747 0.1745
-4.250 -0.3226 0.05874 0.05452 -0.0645 0.9686 0.2018
-4.000 -0.2128 0.03999 0.03344 -0.0912 0.9692 0.0881
-3.750 -0.1638 0.03596 0.02848 -0.0951 0.9653 0.0708
-3.500 -0.1185 0.03302 0.02511 -0.0989 0.9618 0.0672
-3.250 -0.0800 0.03110 0.02275 -0.1010 0.9567 0.0653
-3.000 -0.0417 0.02968 0.02104 -0.1030 0.9515 0.0655
-2.750 0.0022 0.02877 0.01989 -0.1058 0.9477 0.0698
-2.500 0.0311 0.02782 0.01895 -0.1064 0.9405 0.0752
-2.250 0.0725 0.02705 0.01822 -0.1090 0.9359 0.0820
-2.000 0.1080 0.02640 0.01758 -0.1108 0.9297 0.0953
-1.750 0.1511 0.02422 0.01751 -0.1145 0.9259 0.5769
-1.500 0.1805 0.02478 0.01830 -0.1130 0.9206 0.6963
-1.250 0.1907 0.02513 0.01876 -0.1084 0.9106 0.7511
-1.000 0.2051 0.02535 0.01901 -0.1045 0.9027 0.7965
-0.750 0.2289 0.02535 0.01892 -0.1030 0.8954 0.8268
-0.500 0.2461 0.02537 0.01888 -0.1006 0.8866 0.8540
-0.250 0.2735 0.02518 0.01861 -0.0999 0.8805 0.8835
0.000 0.2879 0.02509 0.01849 -0.0974 0.8707 0.9137
0.250 0.3284 0.02470 0.01803 -0.0994 0.8659 0.9572
0.500 0.3648 0.02486 0.01808 -0.1025 0.8558 1.0000
0.750 0.4196 0.02482 0.01787 -0.1081 0.8520 1.0000
1.000 0.4529 0.02518 0.01812 -0.1105 0.8420 1.0000
1.250 0.5057 0.02501 0.01784 -0.1154 0.8382 1.0000
1.500 0.5371 0.02537 0.01812 -0.1171 0.8280 1.0000
1.750 0.5885 0.02505 0.01773 -0.1213 0.8243 1.0000
2.000 0.6175 0.02540 0.01803 -0.1223 0.8138 1.0000
2.250 0.6687 0.02488 0.01748 -0.1261 0.8104 1.0000
2.500 0.6965 0.02517 0.01775 -0.1265 0.7998 1.0000
2.750 0.7490 0.02443 0.01700 -0.1303 0.7966 1.0000
3.000 0.7767 0.02465 0.01724 -0.1305 0.7860 1.0000
3.250 0.8318 0.02380 0.01643 -0.1346 0.7826 1.0000
3.500 0.8606 0.02390 0.01656 -0.1348 0.7718 1.0000
3.750 0.9158 0.02294 0.01568 -0.1387 0.7678 1.0000
4.000 0.9446 0.02294 0.01574 -0.1387 0.7563 1.0000
4.250 0.9790 0.02271 0.01556 -0.1394 0.7458 1.0000
4.500 1.0319 0.02174 0.01470 -0.1429 0.7392 1.0000
4.750 1.0625 0.02159 0.01462 -0.1429 0.7264 1.0000
5.000 1.0952 0.02133 0.01443 -0.1431 0.7131 1.0000
5.250 1.1289 0.02100 0.01417 -0.1434 0.6991 1.0000
5.500 1.1627 0.02068 0.01390 -0.1438 0.6841 1.0000
5.750 1.1964 0.02035 0.01367 -0.1440 0.6681 1.0000
6.000 1.2181 0.02040 0.01381 -0.1424 0.6484 1.0000
6.250 1.2466 0.02020 0.01365 -0.1417 0.6283 1.0000
6.500 1.2700 0.02020 0.01369 -0.1403 0.6061 1.0000
6.750 1.2953 0.02017 0.01365 -0.1391 0.5826 1.0000
7.000 1.3143 0.02034 0.01391 -0.1370 0.5565 1.0000
7.250 1.3317 0.02059 0.01418 -0.1346 0.5285 1.0000
7.500 1.3477 0.02092 0.01448 -0.1321 0.4982 1.0000
7.750 1.3592 0.02140 0.01497 -0.1288 0.4648 1.0000
8.000 1.3687 0.02201 0.01549 -0.1253 0.4285 1.0000
8.250 1.3739 0.02279 0.01617 -0.1212 0.3891 1.0000
8.500 1.3743 0.02377 0.01698 -0.1164 0.3473 1.0000
8.750 1.3722 0.02505 0.01808 -0.1116 0.3037 1.0000
9.000 1.3690 0.02665 0.01940 -0.1069 0.2618 1.0000
9.250 1.3663 0.02850 0.02098 -0.1027 0.2254 1.0000
9.500 1.3654 0.03046 0.02273 -0.0989 0.1948 1.0000
9.750 1.3663 0.03245 0.02454 -0.0957 0.1701 1.0000
10.000 1.3679 0.03440 0.02637 -0.0928 0.1493 1.0000
10.250 1.3688 0.03636 0.02828 -0.0901 0.1300 1.0000
10.500 1.3688 0.03833 0.03025 -0.0876 0.1122 1.0000
10.750 1.3688 0.04058 0.03247 -0.0853 0.0970 1.0000
11.000 1.3675 0.04320 0.03502 -0.0830 0.0825 1.0000
11.250 1.3669 0.04625 0.03805 -0.0806 0.0676 1.0000
11.500 1.3727 0.04934 0.04108 -0.0787 0.0562 1.0000
11.750 1.3809 0.05189 0.04380 -0.0770 0.0493 1.0000
12.000 1.3946 0.05479 0.04679 -0.0759 0.0440 1.0000
12.250 1.4053 0.05747 0.04975 -0.0746 0.0405 1.0000
12.500 1.4185 0.06038 0.05282 -0.0735 0.0381 1.0000
12.750 1.4383 0.06415 0.05670 -0.0730 0.0361 1.0000
13.000 1.4476 0.06970 0.06259 -0.0722 0.0352 1.0000
13.250 1.4398 0.07381 0.06707 -0.0705 0.0350 1.0000
13.500 1.4288 0.07829 0.07191 -0.0692 0.0349 1.0000
13.750 1.4145 0.08310 0.07705 -0.0684 0.0349 1.0000
14.000 1.3986 0.08822 0.08248 -0.0681 0.0349 1.0000
14.250 1.3806 0.09368 0.08823 -0.0685 0.0349 1.0000
14.500 1.3612 0.09953 0.09436 -0.0695 0.0350 1.0000
14.750 1.3414 0.10580 0.10088 -0.0713 0.0351 1.0000
15.000 1.3215 0.11246 0.10776 -0.0739 0.0352 1.0000
15.250 1.0587 0.12696 0.12362 -0.0787 0.0409 1.0000
15.500 1.0182 0.13864 0.13546 -0.0867 0.0429 1.0000
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Polar data table (+)
Polar graphs
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