FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX S 02-196 AIRFOIL (fxs02196-il) Reynolds number: 500,000 Max Cl/Cd: 53.06 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs02196-il-500000.txt Download as CSV file: xf-fxs02196-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.4895 0.10475 0.10213 -0.0662 1.0000 0.0156
-15.750 -0.5220 0.09379 0.09104 -0.0725 1.0000 0.0155
-15.500 -0.5237 0.08981 0.08707 -0.0743 1.0000 0.0153
-15.250 -0.5567 0.08003 0.07711 -0.0804 1.0000 0.0152
-15.000 -0.5828 0.07248 0.06939 -0.0849 1.0000 0.0151
-14.750 -0.6028 0.06651 0.06328 -0.0880 1.0000 0.0149
-14.500 -0.6276 0.06056 0.05711 -0.0910 1.0000 0.0150
-14.250 -0.6414 0.05363 0.04986 -0.0981 0.9650 0.0151
-14.000 -0.6484 0.04574 0.04134 -0.1113 0.9399 0.0155
-13.750 -0.6217 0.04165 0.03703 -0.1178 0.9149 0.0163
-13.500 -0.6038 0.03960 0.03480 -0.1197 0.8854 0.0166
-13.250 -0.6009 0.03776 0.03275 -0.1195 0.8598 0.0172
-13.000 -0.6054 0.03578 0.03048 -0.1186 0.8390 0.0177
-12.750 -0.6237 0.03383 0.02814 -0.1172 0.8194 0.0182
-12.500 -0.6324 0.03243 0.02645 -0.1155 0.8033 0.0184
-12.000 -0.5889 0.02916 0.02301 -0.1144 0.7803 0.0209
-11.750 -0.5635 0.02803 0.02187 -0.1135 0.7697 0.0218
-11.500 -0.5496 0.02716 0.02096 -0.1126 0.7574 0.0225
-11.250 -0.5373 0.02624 0.01990 -0.1116 0.7462 0.0232
-11.000 -0.5238 0.02540 0.01891 -0.1106 0.7354 0.0235
-10.750 -0.5086 0.02454 0.01800 -0.1095 0.7258 0.0240
-10.500 -0.4952 0.02381 0.01723 -0.1085 0.7153 0.0244
-10.250 -0.4814 0.02313 0.01649 -0.1077 0.7061 0.0250
-10.000 -0.4674 0.02241 0.01570 -0.1066 0.6965 0.0252
-9.750 -0.4538 0.02173 0.01494 -0.1055 0.6876 0.0256
-9.500 -0.4410 0.02097 0.01411 -0.1043 0.6794 0.0258
-9.000 -0.4184 0.01960 0.01260 -0.1014 0.6628 0.0266
-8.750 -0.4084 0.01914 0.01209 -0.0997 0.6557 0.0270
-8.500 -0.3913 0.01884 0.01171 -0.0989 0.6485 0.0276
-8.250 -0.3746 0.01827 0.01112 -0.0979 0.6428 0.0278
-8.000 -0.3549 0.01790 0.01067 -0.0972 0.6359 0.0284
-7.750 -0.3362 0.01744 0.01012 -0.0964 0.6304 0.0288
-7.500 -0.3168 0.01691 0.00955 -0.0958 0.6257 0.0290
-7.250 -0.2951 0.01650 0.00910 -0.0953 0.6210 0.0295
-7.000 -0.2725 0.01615 0.00871 -0.0950 0.6162 0.0299
-6.750 -0.2486 0.01591 0.00840 -0.0948 0.6108 0.0307
-6.500 -0.2249 0.01557 0.00802 -0.0946 0.6059 0.0314
-6.250 -0.2011 0.01514 0.00756 -0.0944 0.6010 0.0318
-6.000 -0.1769 0.01476 0.00713 -0.0943 0.5961 0.0323
-5.750 -0.1519 0.01444 0.00673 -0.0943 0.5917 0.0327
-5.500 -0.1268 0.01413 0.00637 -0.0943 0.5874 0.0333
-5.250 -0.1002 0.01379 0.00603 -0.0945 0.5842 0.0341
-5.000 -0.0733 0.01350 0.00571 -0.0947 0.5789 0.0354
-4.750 -0.0465 0.01327 0.00540 -0.0948 0.5726 0.0366
-4.500 -0.0200 0.01301 0.00507 -0.0950 0.5663 0.0381
-4.250 0.0080 0.01278 0.00481 -0.0953 0.5616 0.0397
-4.000 0.0358 0.01256 0.00454 -0.0956 0.5570 0.0410
-3.750 0.0637 0.01238 0.00431 -0.0959 0.5529 0.0425
-3.500 0.0916 0.01228 0.00413 -0.0961 0.5483 0.0435
-3.250 0.1201 0.01218 0.00400 -0.0965 0.5444 0.0442
-3.000 0.1488 0.01205 0.00388 -0.0969 0.5401 0.0455
-2.750 0.1772 0.01193 0.00376 -0.0972 0.5352 0.0476
-2.500 0.2055 0.01184 0.00367 -0.0975 0.5307 0.0609
-2.250 0.2337 0.01184 0.00361 -0.0978 0.5264 0.0627
-2.000 0.2627 0.01176 0.00353 -0.0982 0.5228 0.0642
-1.750 0.2916 0.01170 0.00347 -0.0986 0.5184 0.0656
-1.500 0.3200 0.01167 0.00340 -0.0989 0.5123 0.0677
-1.250 0.3478 0.01167 0.00334 -0.0991 0.5053 0.0685
-1.000 0.3765 0.01162 0.00328 -0.0994 0.4986 0.0696
-0.750 0.4048 0.01160 0.00324 -0.0997 0.4927 0.0715
-0.500 0.4326 0.01161 0.00321 -0.1000 0.4870 0.0741
-0.250 0.4613 0.01154 0.00318 -0.1004 0.4811 0.0949
0.000 0.4893 0.01156 0.00318 -0.1006 0.4734 0.1028
0.250 0.5165 0.01160 0.00318 -0.1008 0.4645 0.1094
0.500 0.5449 0.01151 0.00315 -0.1012 0.4517 0.1473
0.750 0.5705 0.01154 0.00314 -0.1013 0.4228 0.1939
1.000 0.5849 0.01225 0.00353 -0.0997 0.3352 0.2502
1.250 0.6042 0.01237 0.00390 -0.0996 0.2731 0.4264
1.500 0.6222 0.01298 0.00438 -0.0984 0.2241 0.4537
1.750 0.6469 0.01319 0.00462 -0.0982 0.2045 0.4714
2.000 0.6661 0.01370 0.00501 -0.0971 0.1749 0.4892
2.250 0.6892 0.01398 0.00526 -0.0966 0.1667 0.5001
2.500 0.7142 0.01413 0.00546 -0.0963 0.1602 0.5127
2.750 0.7322 0.01460 0.00584 -0.0950 0.1323 0.5190
3.000 0.7543 0.01485 0.00608 -0.0943 0.1279 0.5237
3.250 0.7758 0.01510 0.00636 -0.0936 0.1246 0.5315
3.500 0.7955 0.01538 0.00664 -0.0924 0.1218 0.5385
3.750 0.8152 0.01557 0.00688 -0.0913 0.1205 0.5456
4.000 0.8343 0.01580 0.00713 -0.0900 0.1185 0.5523
4.250 0.8532 0.01608 0.00743 -0.0888 0.1151 0.5585
4.500 0.8640 0.01665 0.00798 -0.0865 0.0945 0.5646
4.750 0.8799 0.01708 0.00843 -0.0850 0.0932 0.5707
5.000 0.8947 0.01759 0.00894 -0.0835 0.0913 0.5786
5.250 0.9085 0.01814 0.00955 -0.0819 0.0890 0.5858
5.500 0.9235 0.01869 0.01014 -0.0806 0.0876 0.5921
5.750 0.9387 0.01928 0.01076 -0.0793 0.0865 0.5981
6.000 0.9540 0.01988 0.01142 -0.0782 0.0852 0.6040
6.250 0.9688 0.02053 0.01214 -0.0771 0.0843 0.6113
6.500 0.9833 0.02127 0.01290 -0.0760 0.0834 0.6180
6.750 0.9968 0.02206 0.01375 -0.0749 0.0821 0.6235
7.000 1.0102 0.02290 0.01465 -0.0738 0.0811 0.6294
7.250 1.0230 0.02382 0.01563 -0.0728 0.0802 0.6352
7.500 1.0354 0.02481 0.01666 -0.0718 0.0793 0.6420
7.750 1.0498 0.02568 0.01762 -0.0711 0.0784 0.6489
8.000 1.0633 0.02664 0.01865 -0.0703 0.0776 0.6571
8.250 1.0767 0.02764 0.01973 -0.0695 0.0764 0.6652
8.500 1.0918 0.02854 0.02072 -0.0689 0.0660 0.6743
8.750 1.0977 0.03014 0.02234 -0.0678 0.0641 0.6832
9.000 1.1047 0.03171 0.02395 -0.0668 0.0615 0.6936
9.250 1.1141 0.03311 0.02542 -0.0660 0.0602 0.7047
9.500 1.1232 0.03456 0.02695 -0.0653 0.0595 0.7175
9.750 1.1327 0.03598 0.02847 -0.0645 0.0590 0.7338
10.000 1.1417 0.03748 0.03009 -0.0638 0.0585 0.7537
10.250 1.1498 0.03904 0.03178 -0.0631 0.0578 0.7777
10.500 1.1573 0.04060 0.03351 -0.0622 0.0573 0.8125
10.750 1.1585 0.04197 0.03518 -0.0600 0.0565 0.9030
11.000 1.1670 0.04377 0.03707 -0.0599 0.0556 1.0000
11.250 1.1766 0.04550 0.03883 -0.0596 0.0550 1.0000
11.500 1.1858 0.04731 0.04070 -0.0594 0.0542 1.0000
11.750 1.1945 0.04919 0.04263 -0.0592 0.0532 1.0000
12.000 1.2013 0.05128 0.04476 -0.0590 0.0518 1.0000
12.250 1.2059 0.05365 0.04717 -0.0588 0.0507 1.0000
12.500 1.2135 0.05572 0.04928 -0.0586 0.0497 1.0000
12.750 1.2261 0.05729 0.05091 -0.0587 0.0486 1.0000
13.000 1.2361 0.05918 0.05286 -0.0587 0.0471 1.0000
13.250 1.2456 0.06113 0.05485 -0.0587 0.0457 1.0000
13.500 1.2551 0.06309 0.05685 -0.0588 0.0447 1.0000
13.750 1.2664 0.06486 0.05868 -0.0589 0.0432 1.0000
14.000 1.2762 0.06685 0.06073 -0.0590 0.0414 1.0000
14.250 1.2861 0.06882 0.06273 -0.0592 0.0399 1.0000
14.500 1.2968 0.07071 0.06461 -0.0594 0.0386 1.0000
14.750 1.3062 0.07276 0.06666 -0.0597 0.0374 1.0000
15.000 1.3129 0.07518 0.06908 -0.0599 0.0363 1.0000
15.250 1.3189 0.07770 0.07164 -0.0602 0.0357 1.0000
15.500 1.3247 0.08028 0.07427 -0.0606 0.0353 1.0000
15.750 1.3282 0.08321 0.07726 -0.0610 0.0348 1.0000
16.000 1.3314 0.08619 0.08029 -0.0615 0.0343 1.0000
16.250 1.3349 0.08914 0.08330 -0.0620 0.0339 1.0000
16.500 1.3355 0.09254 0.08673 -0.0627 0.0332 1.0000
16.750 1.3355 0.09608 0.09031 -0.0634 0.0327 1.0000
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Polar data table (+)
Polar graphs
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