S4022 (s4022-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4022 (s4022-il) Reynolds number: 100,000 Max Cl/Cd: 65.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4022-il-100000-n5.txt Download as CSV file: xf-s4022-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3539 0.11193 0.10726 -0.0364 1.0000 0.0554
-8.750 -0.3641 0.10979 0.10521 -0.0361 1.0000 0.0567
-8.500 -0.3742 0.10695 0.10246 -0.0409 0.9974 0.0581
-8.250 -0.3679 0.10237 0.09790 -0.0476 0.9920 0.0584
-8.000 -0.3617 0.09770 0.09326 -0.0533 0.9859 0.0585
-7.750 -0.3563 0.09276 0.08833 -0.0592 0.9785 0.0586
-7.500 -0.3382 0.08424 0.07973 -0.0561 0.9778 0.0323
-7.250 -0.3295 0.07963 0.07513 -0.0606 0.9720 0.0313
-7.000 -0.3214 0.07426 0.06978 -0.0664 0.9635 0.0304
-6.750 -0.3103 0.06629 0.06176 -0.0773 0.9542 0.0295
-6.500 -0.2919 0.05743 0.05264 -0.0892 0.9477 0.0282
-6.250 -0.2788 0.05069 0.04556 -0.0956 0.9386 0.0275
-6.000 -0.2491 0.04502 0.03943 -0.1026 0.9347 0.0285
-5.750 -0.2266 0.04100 0.03496 -0.1058 0.9276 0.0298
-5.500 -0.1932 0.03675 0.03012 -0.1101 0.9238 0.0301
-5.250 -0.1556 0.03302 0.02578 -0.1141 0.9214 0.0298
-5.000 -0.1267 0.03051 0.02279 -0.1155 0.9161 0.0298
-4.750 -0.0935 0.02831 0.02012 -0.1172 0.9120 0.0299
-4.500 -0.0577 0.02646 0.01791 -0.1191 0.9093 0.0304
-4.250 -0.0206 0.02491 0.01608 -0.1210 0.9071 0.0311
-4.000 0.0042 0.02391 0.01493 -0.1206 0.9004 0.0320
-3.750 0.0378 0.02298 0.01384 -0.1218 0.8967 0.0335
-3.500 0.0743 0.02186 0.01273 -0.1240 0.8942 0.0386
-3.250 0.1029 0.02123 0.01201 -0.1244 0.8884 0.0412
-3.000 0.1365 0.02058 0.01120 -0.1256 0.8839 0.0444
-2.750 0.1748 0.01980 0.01034 -0.1278 0.8812 0.0520
-2.500 0.2160 0.01873 0.00953 -0.1309 0.8792 0.1176
-2.250 0.2441 0.01755 0.00948 -0.1324 0.8723 0.3866
-2.000 0.2755 0.01728 0.00985 -0.1326 0.8683 0.5890
-1.750 0.3102 0.01721 0.00978 -0.1332 0.8655 0.6418
-1.500 0.3322 0.01731 0.00980 -0.1319 0.8570 0.6655
-1.000 0.3940 0.01717 0.00950 -0.1324 0.8467 0.7071
-0.750 0.4247 0.01709 0.00934 -0.1327 0.8411 0.7237
-0.500 0.4617 0.01689 0.00906 -0.1342 0.8376 0.7394
-0.250 0.4847 0.01694 0.00908 -0.1331 0.8289 0.7528
0.000 0.5202 0.01675 0.00882 -0.1344 0.8245 0.7662
0.250 0.5451 0.01678 0.00881 -0.1337 0.8162 0.7790
0.500 0.5792 0.01661 0.00860 -0.1347 0.8109 0.7921
0.750 0.6046 0.01661 0.00860 -0.1341 0.8027 0.8054
1.000 0.6374 0.01645 0.00842 -0.1348 0.7968 0.8190
1.250 0.6614 0.01645 0.00844 -0.1339 0.7881 0.8334
1.500 0.6936 0.01627 0.00826 -0.1345 0.7820 0.8485
1.750 0.7149 0.01628 0.00832 -0.1330 0.7724 0.8662
2.000 0.7443 0.01611 0.00817 -0.1330 0.7654 0.8874
2.250 0.7672 0.01602 0.00814 -0.1319 0.7559 0.9187
2.500 0.7982 0.01593 0.00810 -0.1326 0.7465 1.0000
2.750 0.8367 0.01591 0.00803 -0.1347 0.7388 1.0000
3.000 0.8650 0.01608 0.00820 -0.1351 0.7278 1.0000
3.250 0.8949 0.01621 0.00834 -0.1357 0.7171 1.0000
3.500 0.9263 0.01630 0.00845 -0.1364 0.7067 1.0000
3.750 0.9583 0.01637 0.00851 -0.1372 0.6960 1.0000
4.000 0.9860 0.01652 0.00869 -0.1372 0.6834 1.0000
4.250 1.0133 0.01668 0.00887 -0.1371 0.6701 1.0000
4.500 1.0404 0.01685 0.00910 -0.1369 0.6563 1.0000
4.750 1.0673 0.01702 0.00929 -0.1367 0.6417 1.0000
5.000 1.0941 0.01719 0.00948 -0.1364 0.6261 1.0000
5.250 1.1181 0.01742 0.00974 -0.1356 0.6085 1.0000
5.500 1.1419 0.01766 0.01001 -0.1348 0.5899 1.0000
5.750 1.1660 0.01792 0.01032 -0.1340 0.5706 1.0000
6.000 1.1876 0.01823 0.01066 -0.1327 0.5492 1.0000
6.250 1.2091 0.01858 0.01098 -0.1314 0.5260 1.0000
6.500 1.2281 0.01899 0.01139 -0.1298 0.5005 1.0000
6.750 1.2460 0.01946 0.01183 -0.1280 0.4733 1.0000
7.000 1.2624 0.02000 0.01232 -0.1259 0.4441 1.0000
7.250 1.2770 0.02062 0.01293 -0.1236 0.4137 1.0000
7.500 1.2890 0.02131 0.01355 -0.1208 0.3817 1.0000
7.750 1.2992 0.02211 0.01426 -0.1179 0.3476 1.0000
8.250 1.3156 0.02409 0.01601 -0.1119 0.2787 1.0000
8.500 1.3222 0.02527 0.01706 -0.1088 0.2459 1.0000
8.750 1.3280 0.02656 0.01824 -0.1059 0.2157 1.0000
9.000 1.3337 0.02794 0.01952 -0.1030 0.1876 1.0000
9.250 1.3397 0.02937 0.02094 -0.1004 0.1633 1.0000
9.500 1.3455 0.03087 0.02242 -0.0979 0.1439 1.0000
9.750 1.3511 0.03246 0.02400 -0.0954 0.1264 1.0000
10.000 1.3555 0.03418 0.02569 -0.0931 0.1101 1.0000
10.500 1.3640 0.03782 0.02926 -0.0890 0.0781 1.0000
10.750 1.3686 0.03972 0.03115 -0.0872 0.0638 1.0000
11.000 1.3722 0.04177 0.03324 -0.0854 0.0541 1.0000
11.250 1.3735 0.04411 0.03559 -0.0837 0.0459 1.0000
11.500 1.3760 0.04645 0.03810 -0.0820 0.0385 1.0000
11.750 1.3738 0.04933 0.04109 -0.0804 0.0334 1.0000
12.000 1.3729 0.05221 0.04414 -0.0789 0.0292 1.0000
12.250 1.3688 0.05549 0.04750 -0.0778 0.0264 1.0000
12.500 1.3665 0.05873 0.05090 -0.0768 0.0242 1.0000
12.750 1.3660 0.06186 0.05423 -0.0760 0.0221 1.0000
13.000 1.3647 0.06516 0.05768 -0.0756 0.0204 1.0000
13.250 1.3613 0.06884 0.06149 -0.0754 0.0192 1.0000
13.500 1.3554 0.07299 0.06578 -0.0754 0.0183 1.0000
13.750 1.3520 0.07697 0.06993 -0.0754 0.0177 1.0000
14.000 1.3504 0.08085 0.07403 -0.0755 0.0172 1.0000
14.250 1.3485 0.08489 0.07830 -0.0758 0.0167 1.0000
14.500 1.3459 0.08912 0.08275 -0.0764 0.0162 1.0000
14.750 1.3424 0.09359 0.08745 -0.0772 0.0158 1.0000
15.000 1.3380 0.09834 0.09243 -0.0783 0.0154 1.0000
15.250 1.3323 0.10342 0.09774 -0.0798 0.0151 1.0000
15.500 1.3252 0.10886 0.10341 -0.0818 0.0149 1.0000
15.750 1.3167 0.11472 0.10950 -0.0843 0.0148 1.0000
16.000 1.3069 0.12103 0.11604 -0.0874 0.0146 1.0000
16.250 1.2957 0.12787 0.12311 -0.0911 0.0145 1.0000
16.500 1.2830 0.13534 0.13080 -0.0955 0.0144 1.0000
16.750 1.2683 0.14369 0.13938 -0.1008 0.0145 1.0000
17.000 1.2513 0.15311 0.14902 -0.1070 0.0147 1.0000
17.250 1.2311 0.16420 0.16031 -0.1146 0.0149 1.0000
17.500 1.2060 0.17806 0.17433 -0.1241 0.0154 1.0000
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