SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 500,000 Max Cl/Cd: 99.78 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3002-il-500000.txt Download as CSV file: xf-s3002-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3646 0.08641 0.08415 -0.0361 1.0000 0.0192
-8.500 -0.3634 0.08354 0.08132 -0.0367 1.0000 0.0196
-8.250 -0.3649 0.08044 0.07826 -0.0374 1.0000 0.0198
-8.000 -0.3700 0.07747 0.07534 -0.0376 1.0000 0.0200
-7.750 -0.3834 0.07516 0.07310 -0.0361 1.0000 0.0202
-7.500 -0.3885 0.07142 0.06941 -0.0390 0.9967 0.0204
-7.250 -0.3616 0.06198 0.05993 -0.0567 0.9885 0.0210
-7.000 -0.3317 0.04661 0.04397 -0.0773 0.9787 0.0228
-6.750 -0.3112 0.03851 0.03555 -0.0843 0.9736 0.0234
-6.500 -0.2841 0.03601 0.03301 -0.0871 0.9690 0.0239
-6.250 -0.2579 0.03349 0.03035 -0.0892 0.9620 0.0247
-6.000 -0.2374 0.02177 0.01726 -0.0911 0.9516 0.0178
-5.750 -0.2107 0.01901 0.01409 -0.0916 0.9446 0.0177
-5.500 -0.1845 0.01728 0.01200 -0.0913 0.9366 0.0180
-5.250 -0.1586 0.01554 0.01000 -0.0912 0.9293 0.0190
-5.000 -0.1327 0.01464 0.00903 -0.0908 0.9212 0.0198
-4.750 -0.1063 0.01368 0.00794 -0.0904 0.9138 0.0204
-4.500 -0.0800 0.01288 0.00701 -0.0899 0.9056 0.0214
-4.250 -0.0533 0.01227 0.00628 -0.0894 0.8981 0.0225
-4.000 -0.0275 0.01134 0.00528 -0.0889 0.8897 0.0239
-3.750 -0.0008 0.01094 0.00485 -0.0886 0.8820 0.0262
-3.500 0.0263 0.01063 0.00449 -0.0883 0.8734 0.0283
-3.250 0.0530 0.00995 0.00376 -0.0880 0.8658 0.0311
-3.000 0.0804 0.00967 0.00345 -0.0878 0.8570 0.0344
-2.750 0.1079 0.00929 0.00302 -0.0876 0.8492 0.0392
-2.500 0.1357 0.00904 0.00274 -0.0874 0.8401 0.0453
-2.250 0.1635 0.00862 0.00243 -0.0873 0.8322 0.0789
-2.000 0.1909 0.00796 0.00223 -0.0876 0.8232 0.2095
-1.750 0.2182 0.00729 0.00209 -0.0879 0.8151 0.3829
-1.500 0.2449 0.00663 0.00204 -0.0880 0.8062 0.5813
-1.250 0.2714 0.00647 0.00214 -0.0874 0.7974 0.6845
-1.000 0.2984 0.00651 0.00218 -0.0868 0.7885 0.7272
-0.750 0.3256 0.00655 0.00223 -0.0863 0.7784 0.7537
-0.500 0.3525 0.00661 0.00225 -0.0858 0.7688 0.7739
-0.250 0.3796 0.00664 0.00225 -0.0853 0.7583 0.7877
0.000 0.4070 0.00667 0.00224 -0.0849 0.7469 0.7984
0.250 0.4344 0.00671 0.00223 -0.0846 0.7353 0.8089
0.500 0.4608 0.00674 0.00223 -0.0839 0.7231 0.8212
0.750 0.4868 0.00678 0.00224 -0.0832 0.7099 0.8342
1.000 0.5130 0.00681 0.00224 -0.0826 0.6955 0.8451
1.250 0.5399 0.00687 0.00224 -0.0822 0.6797 0.8546
1.500 0.5662 0.00690 0.00224 -0.0817 0.6628 0.8614
1.750 0.5934 0.00697 0.00225 -0.0814 0.6444 0.8681
2.000 0.6197 0.00704 0.00226 -0.0809 0.6243 0.8739
2.250 0.6460 0.00715 0.00229 -0.0805 0.6032 0.8804
2.500 0.6723 0.00726 0.00234 -0.0801 0.5797 0.8868
2.750 0.6978 0.00740 0.00240 -0.0796 0.5554 0.8939
3.000 0.7232 0.00756 0.00247 -0.0790 0.5293 0.9017
3.250 0.7480 0.00772 0.00256 -0.0784 0.5026 0.9112
3.500 0.7718 0.00789 0.00266 -0.0775 0.4765 0.9235
4.000 0.8262 0.00828 0.00289 -0.0774 0.4233 1.0000
4.250 0.8540 0.00857 0.00308 -0.0776 0.3988 1.0000
4.750 0.9085 0.00919 0.00348 -0.0778 0.3529 1.0000
5.000 0.9351 0.00952 0.00372 -0.0778 0.3314 1.0000
5.250 0.9615 0.00984 0.00395 -0.0777 0.3108 1.0000
5.500 0.9877 0.01017 0.00419 -0.0776 0.2906 1.0000
5.750 1.0135 0.01052 0.00445 -0.0774 0.2710 1.0000
6.000 1.0390 0.01088 0.00474 -0.0771 0.2518 1.0000
6.250 1.0645 0.01123 0.00502 -0.0769 0.2332 1.0000
6.500 1.0895 0.01162 0.00533 -0.0766 0.2153 1.0000
6.750 1.1143 0.01202 0.00567 -0.0762 0.1986 1.0000
7.000 1.1387 0.01245 0.00602 -0.0758 0.1822 1.0000
7.250 1.1629 0.01288 0.00639 -0.0754 0.1673 1.0000
7.500 1.1869 0.01332 0.00679 -0.0749 0.1534 1.0000
7.750 1.2106 0.01378 0.00720 -0.0744 0.1398 1.0000
8.000 1.2339 0.01425 0.00763 -0.0738 0.1270 1.0000
8.250 1.2570 0.01473 0.00809 -0.0733 0.1155 1.0000
8.500 1.2796 0.01524 0.00858 -0.0726 0.1048 1.0000
8.750 1.3015 0.01580 0.00911 -0.0719 0.0947 1.0000
9.000 1.3223 0.01644 0.00971 -0.0710 0.0853 1.0000
9.250 1.3439 0.01698 0.01025 -0.0702 0.0779 1.0000
9.500 1.3641 0.01762 0.01091 -0.0692 0.0712 1.0000
9.750 1.3835 0.01828 0.01156 -0.0681 0.0652 1.0000
10.000 1.4021 0.01898 0.01231 -0.0669 0.0606 1.0000
10.250 1.4210 0.01961 0.01296 -0.0657 0.0565 1.0000
10.500 1.4339 0.02065 0.01401 -0.0638 0.0522 1.0000
10.750 1.4521 0.02119 0.01464 -0.0625 0.0500 1.0000
11.000 1.4667 0.02185 0.01536 -0.0607 0.0475 1.0000
11.250 1.4769 0.02274 0.01628 -0.0583 0.0450 1.0000
11.500 1.4818 0.02399 0.01759 -0.0554 0.0428 1.0000
11.750 1.4953 0.02473 0.01845 -0.0538 0.0414 1.0000
12.000 1.5066 0.02564 0.01944 -0.0520 0.0397 1.0000
12.250 1.5167 0.02665 0.02051 -0.0502 0.0380 1.0000
12.500 1.5217 0.02809 0.02199 -0.0481 0.0364 1.0000
12.750 1.5189 0.03022 0.02421 -0.0456 0.0349 1.0000
13.000 1.5298 0.03136 0.02547 -0.0444 0.0340 1.0000
13.250 1.5382 0.03275 0.02697 -0.0432 0.0328 1.0000
13.500 1.5453 0.03430 0.02861 -0.0420 0.0316 1.0000
13.750 1.5507 0.03605 0.03045 -0.0410 0.0305 1.0000
14.000 1.5518 0.03829 0.03277 -0.0400 0.0295 1.0000
14.250 1.5446 0.04152 0.03608 -0.0390 0.0284 1.0000
14.500 1.5453 0.04409 0.03878 -0.0384 0.0277 1.0000
14.750 1.5506 0.04625 0.04108 -0.0383 0.0268 1.0000
15.000 1.5537 0.04874 0.04368 -0.0382 0.0259 1.0000
15.250 1.5552 0.05151 0.04656 -0.0385 0.0250 1.0000
15.500 1.5545 0.05465 0.04980 -0.0389 0.0242 1.0000
15.750 1.5495 0.05853 0.05376 -0.0398 0.0235 1.0000
16.000 1.5385 0.06340 0.05872 -0.0410 0.0228 1.0000
16.250 1.5286 0.06835 0.06380 -0.0425 0.0222 1.0000
16.500 1.5262 0.07250 0.06811 -0.0441 0.0218 1.0000
16.750 1.5211 0.07716 0.07294 -0.0460 0.0213 1.0000
17.000 1.5146 0.08222 0.07813 -0.0483 0.0207 1.0000
17.250 1.5070 0.08762 0.08367 -0.0508 0.0202 1.0000
17.500 1.4981 0.09333 0.08950 -0.0535 0.0198 1.0000
17.750 1.4886 0.09931 0.09559 -0.0565 0.0194 1.0000
18.000 1.4781 0.10560 0.10199 -0.0598 0.0190 1.0000
18.250 1.4666 0.11210 0.10859 -0.0633 0.0186 1.0000
18.500 1.4541 0.11882 0.11540 -0.0669 0.0183 1.0000
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Polar data table (+)
Polar graphs
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