FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX S 02-196 AIRFOIL (fxs02196-il) Reynolds number: 200,000 Max Cl/Cd: 68.41 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs02196-il-200000.txt Download as CSV file: xf-fxs02196-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02-196 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.1357 0.10846 0.10489 -0.0856 0.8546 0.0760
-12.750 -0.2202 0.10739 0.10403 -0.0838 0.9294 0.0726
-12.500 -0.4830 0.05727 0.05283 -0.1165 0.9246 0.0362
-12.250 -0.4798 0.05263 0.04791 -0.1205 0.9030 0.0360
-12.000 -0.4881 0.04902 0.04400 -0.1216 0.8807 0.0358
-11.750 -0.4992 0.04618 0.04089 -0.1207 0.8610 0.0357
-11.500 -0.5169 0.04366 0.03803 -0.1185 0.8432 0.0358
-11.250 -0.5396 0.04170 0.03569 -0.1147 0.8277 0.0360
-11.000 -0.5573 0.03975 0.03320 -0.1111 0.8154 0.0363
-10.750 -0.5259 0.03845 0.03216 -0.1120 0.8044 0.0382
-10.500 -0.5300 0.03665 0.02988 -0.1094 0.7947 0.0395
-10.250 -0.5215 0.03467 0.02766 -0.1080 0.7842 0.0407
-10.000 -0.5027 0.03324 0.02608 -0.1074 0.7758 0.0418
-9.750 -0.4867 0.03163 0.02421 -0.1064 0.7668 0.0426
-9.500 -0.4704 0.03021 0.02247 -0.1053 0.7583 0.0434
-9.250 -0.4481 0.02892 0.02104 -0.1049 0.7512 0.0448
-9.000 -0.4252 0.02801 0.02012 -0.1046 0.7429 0.0462
-8.750 -0.4051 0.02710 0.01895 -0.1038 0.7361 0.0477
-8.500 -0.3799 0.02614 0.01794 -0.1037 0.7301 0.0489
-8.250 -0.3536 0.02520 0.01697 -0.1034 0.7231 0.0492
-8.000 -0.3269 0.02434 0.01605 -0.1030 0.7172 0.0493
-7.750 -0.3015 0.02363 0.01526 -0.1025 0.7122 0.0496
-7.500 -0.2789 0.02298 0.01464 -0.1018 0.7064 0.0500
-7.250 -0.2581 0.02237 0.01403 -0.1009 0.7007 0.0505
-7.000 -0.2384 0.02179 0.01341 -0.1000 0.6958 0.0511
-6.750 -0.2192 0.02125 0.01280 -0.0991 0.6916 0.0517
-6.500 -0.2009 0.02072 0.01227 -0.0983 0.6870 0.0525
-6.250 -0.1818 0.02021 0.01179 -0.0976 0.6822 0.0535
-6.000 -0.1611 0.01974 0.01128 -0.0972 0.6779 0.0550
-5.750 -0.1389 0.01931 0.01075 -0.0968 0.6741 0.0570
-5.500 -0.1160 0.01892 0.01028 -0.0967 0.6707 0.0601
-5.250 -0.0934 0.01851 0.00984 -0.0965 0.6668 0.0650
-5.000 -0.0710 0.01791 0.00921 -0.0964 0.6624 0.0735
-4.750 -0.0474 0.01729 0.00873 -0.0966 0.6583 0.1032
-4.500 -0.0244 0.01628 0.00808 -0.0972 0.6549 0.1975
-4.250 -0.0014 0.01499 0.00760 -0.0982 0.6518 0.3856
-4.000 0.0272 0.01512 0.00776 -0.0985 0.6486 0.4454
-3.750 0.0548 0.01523 0.00789 -0.0986 0.6448 0.4631
-3.500 0.0830 0.01534 0.00795 -0.0988 0.6408 0.4767
-3.250 0.1118 0.01541 0.00792 -0.0991 0.6371 0.4863
-3.000 0.1411 0.01548 0.00788 -0.0994 0.6337 0.4958
-2.750 0.1707 0.01557 0.00783 -0.0998 0.6300 0.5048
-2.500 0.1979 0.01566 0.00791 -0.0997 0.6251 0.5112
-2.250 0.2258 0.01565 0.00783 -0.0999 0.6194 0.5177
-2.000 0.2548 0.01559 0.00767 -0.1000 0.6141 0.5229
-1.750 0.2841 0.01561 0.00758 -0.1002 0.6094 0.5277
-1.500 0.3117 0.01572 0.00767 -0.1003 0.6053 0.5334
-1.250 0.3397 0.01580 0.00771 -0.1006 0.6013 0.5394
-1.000 0.3673 0.01590 0.00783 -0.1006 0.5977 0.5454
-0.750 0.3959 0.01605 0.00796 -0.1008 0.5945 0.5558
-0.500 0.4246 0.01617 0.00803 -0.1010 0.5918 0.5631
-0.250 0.4533 0.01632 0.00815 -0.1012 0.5891 0.5695
0.000 0.4818 0.01651 0.00830 -0.1015 0.5864 0.5758
0.250 0.5085 0.01660 0.00843 -0.1015 0.5832 0.5813
0.500 0.5344 0.01670 0.00862 -0.1011 0.5787 0.5886
1.000 0.5901 0.01680 0.00868 -0.1009 0.5699 0.6065
1.250 0.6187 0.01687 0.00870 -0.1012 0.5660 0.6114
1.500 0.6452 0.01694 0.00881 -0.1013 0.5626 0.6159
1.750 0.6726 0.01700 0.00889 -0.1015 0.5593 0.6205
2.000 0.6987 0.01706 0.00902 -0.1012 0.5559 0.6261
2.250 0.7262 0.01713 0.00909 -0.1011 0.5521 0.6353
2.500 0.7541 0.01713 0.00905 -0.1010 0.5478 0.6441
2.750 0.7785 0.01722 0.00923 -0.1004 0.5430 0.6515
3.000 0.8045 0.01727 0.00932 -0.1004 0.5379 0.6586
3.250 0.8308 0.01722 0.00931 -0.1003 0.5337 0.6629
3.500 0.8577 0.01721 0.00933 -0.1002 0.5303 0.6669
3.750 0.8861 0.01725 0.00934 -0.1005 0.5274 0.6711
4.000 0.9136 0.01733 0.00944 -0.1008 0.5245 0.6754
4.250 0.9394 0.01744 0.00962 -0.1010 0.5213 0.6795
4.500 0.9647 0.01750 0.00978 -0.1009 0.5182 0.6829
4.750 0.9901 0.01756 0.00994 -0.1007 0.5152 0.6865
5.000 1.0162 0.01762 0.01005 -0.1007 0.5121 0.6909
5.250 1.0434 0.01766 0.01012 -0.1009 0.5092 0.6958
5.500 1.0722 0.01773 0.01016 -0.1014 0.5065 0.7009
5.750 1.0955 0.01784 0.01041 -0.1010 0.5036 0.7054
6.000 1.1179 0.01798 0.01070 -0.1004 0.4999 0.7107
6.250 1.1411 0.01807 0.01088 -0.0999 0.4951 0.7170
6.500 1.1658 0.01809 0.01095 -0.0997 0.4907 0.7234
6.750 1.1912 0.01811 0.01101 -0.0994 0.4872 0.7298
7.000 1.2126 0.01830 0.01133 -0.0987 0.4832 0.7377
7.250 1.2313 0.01848 0.01167 -0.0976 0.4778 0.7457
7.500 1.2506 0.01858 0.01187 -0.0964 0.4720 0.7545
7.750 1.2732 0.01861 0.01191 -0.0957 0.4663 0.7649
8.000 1.2845 0.01891 0.01245 -0.0933 0.4596 0.7756
8.250 1.2949 0.01913 0.01282 -0.0907 0.4521 0.7886
8.500 1.3063 0.01937 0.01317 -0.0883 0.4451 0.8045
8.750 1.3122 0.01980 0.01381 -0.0852 0.4369 0.8222
9.000 1.3188 0.02017 0.01430 -0.0822 0.4276 0.8466
9.250 1.3183 0.02061 0.01492 -0.0780 0.4173 0.8869
9.500 1.3214 0.02109 0.01549 -0.0751 0.4042 1.0000
9.750 1.3269 0.02220 0.01654 -0.0735 0.3801 1.0000
10.000 1.3193 0.02399 0.01810 -0.0706 0.3542 1.0000
10.250 1.3101 0.02619 0.02017 -0.0679 0.3349 1.0000
10.500 1.3028 0.02854 0.02246 -0.0658 0.3087 1.0000
10.750 1.2899 0.03144 0.02524 -0.0635 0.2918 1.0000
11.000 1.2830 0.03408 0.02784 -0.0619 0.2788 1.0000
11.250 1.2751 0.03695 0.03068 -0.0605 0.2495 1.0000
11.500 1.2575 0.04076 0.03434 -0.0588 0.2330 1.0000
11.750 1.2483 0.04404 0.03754 -0.0578 0.2200 1.0000
12.000 1.2467 0.04678 0.04027 -0.0571 0.1907 1.0000
12.250 1.2362 0.05044 0.04380 -0.0564 0.1795 1.0000
12.500 1.2333 0.05346 0.04679 -0.0559 0.1672 1.0000
12.750 1.2330 0.05630 0.04961 -0.0556 0.1411 1.0000
13.000 1.2254 0.05998 0.05314 -0.0553 0.1313 1.0000
13.250 1.2227 0.06323 0.05638 -0.0552 0.1211 1.0000
13.500 1.2264 0.06584 0.05898 -0.0552 0.0996 1.0000
13.750 1.2216 0.06948 0.06250 -0.0553 0.0920 1.0000
14.000 1.2157 0.07333 0.06629 -0.0554 0.0868 1.0000
14.250 1.2186 0.07619 0.06923 -0.0555 0.0805 1.0000
14.500 1.2249 0.07872 0.07186 -0.0558 0.0742 1.0000
14.750 1.2312 0.08125 0.07443 -0.0561 0.0696 1.0000
15.000 1.2367 0.08390 0.07708 -0.0564 0.0665 1.0000
15.250 1.2406 0.08678 0.07996 -0.0569 0.0644 1.0000
15.500 1.2437 0.08977 0.08295 -0.0574 0.0627 1.0000
15.750 1.2464 0.09280 0.08594 -0.0579 0.0612 1.0000
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Polar data table (+)
Polar graphs
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