FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 500,000 Max Cl/Cd: 104.46 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66196v-il-500000-n5.txt Download as CSV file: xf-fx66196v-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 V1 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.5970 0.10336 0.10057 -0.0640 0.9570 0.0082
-16.750 -0.6207 0.09100 0.08795 -0.0741 0.9462 0.0083
-16.500 -0.6282 0.08075 0.07744 -0.0849 0.9334 0.0082
-16.250 -0.6229 0.07137 0.06773 -0.0974 0.9134 0.0084
-16.000 -0.6132 0.06434 0.06032 -0.1074 0.8842 0.0085
-15.750 -0.6127 0.05962 0.05529 -0.1119 0.8563 0.0087
-15.500 -0.6159 0.05586 0.05130 -0.1141 0.8339 0.0086
-15.250 -0.6148 0.05298 0.04820 -0.1156 0.8146 0.0089
-15.000 -0.6173 0.04997 0.04499 -0.1166 0.7976 0.0088
-14.750 -0.6181 0.04732 0.04222 -0.1176 0.7833 0.0091
-14.500 -0.6187 0.04484 0.03958 -0.1180 0.7671 0.0092
-14.000 -0.6137 0.04076 0.03523 -0.1186 0.7418 0.0094
-13.750 -0.6096 0.03895 0.03330 -0.1187 0.7301 0.0095
-13.500 -0.6044 0.03729 0.03152 -0.1187 0.7197 0.0097
-13.250 -0.6003 0.03555 0.02965 -0.1184 0.7104 0.0097
-13.000 -0.5940 0.03403 0.02802 -0.1182 0.7018 0.0098
-12.750 -0.5860 0.03270 0.02659 -0.1179 0.6933 0.0101
-12.500 -0.5794 0.03125 0.02503 -0.1174 0.6856 0.0102
-12.250 -0.5710 0.02999 0.02367 -0.1169 0.6776 0.0105
-12.000 -0.5624 0.02877 0.02234 -0.1164 0.6698 0.0107
-11.750 -0.5535 0.02759 0.02105 -0.1157 0.6625 0.0109
-11.500 -0.5443 0.02646 0.01982 -0.1150 0.6558 0.0111
-11.250 -0.5345 0.02540 0.01866 -0.1142 0.6490 0.0113
-11.000 -0.5245 0.02440 0.01755 -0.1133 0.6425 0.0115
-10.750 -0.5176 0.02319 0.01629 -0.1123 0.6369 0.0118
-10.500 -0.5091 0.02216 0.01518 -0.1112 0.6313 0.0120
-10.250 -0.4994 0.02125 0.01421 -0.1100 0.6263 0.0124
-10.000 -0.4899 0.02038 0.01330 -0.1088 0.6211 0.0127
-9.750 -0.4813 0.01969 0.01254 -0.1071 0.6161 0.0132
-9.500 -0.4739 0.01909 0.01186 -0.1050 0.6116 0.0135
-9.250 -0.4593 0.01851 0.01121 -0.1038 0.6071 0.0140
-9.000 -0.4424 0.01802 0.01063 -0.1028 0.6024 0.0146
-8.750 -0.4262 0.01745 0.00999 -0.1018 0.5982 0.0152
-8.500 -0.4076 0.01693 0.00943 -0.1010 0.5944 0.0159
-8.250 -0.3872 0.01649 0.00894 -0.1004 0.5904 0.0166
-8.000 -0.3659 0.01608 0.00846 -0.0999 0.5865 0.0175
-7.750 -0.3438 0.01572 0.00801 -0.0994 0.5830 0.0184
-7.500 -0.3217 0.01529 0.00755 -0.0991 0.5799 0.0196
-7.250 -0.2982 0.01493 0.00716 -0.0988 0.5766 0.0212
-7.000 -0.2739 0.01463 0.00680 -0.0987 0.5733 0.0230
-6.750 -0.2500 0.01428 0.00641 -0.0985 0.5702 0.0254
-6.500 -0.2252 0.01400 0.00608 -0.0983 0.5674 0.0281
-6.250 -0.2002 0.01370 0.00576 -0.0983 0.5648 0.0318
-6.000 -0.1744 0.01342 0.00547 -0.0983 0.5622 0.0371
-5.750 -0.1486 0.01313 0.00518 -0.0984 0.5596 0.0446
-5.500 -0.1228 0.01284 0.00490 -0.0985 0.5569 0.0557
-5.250 -0.0972 0.01251 0.00462 -0.0985 0.5545 0.0740
-5.000 -0.0717 0.01215 0.00434 -0.0986 0.5521 0.1027
-4.750 -0.0464 0.01173 0.00405 -0.0988 0.5501 0.1448
-4.500 -0.0216 0.01110 0.00369 -0.0990 0.5481 0.2176
-4.250 0.0024 0.01031 0.00328 -0.0993 0.5460 0.3200
-4.000 0.0277 0.00983 0.00316 -0.0994 0.5440 0.4263
-3.750 0.0560 0.00981 0.00315 -0.0997 0.5419 0.4522
-3.500 0.0845 0.00984 0.00315 -0.0999 0.5397 0.4685
-3.250 0.1129 0.00989 0.00315 -0.1002 0.5377 0.4816
-3.000 0.1413 0.00997 0.00317 -0.1004 0.5359 0.4942
-2.750 0.1699 0.01004 0.00319 -0.1007 0.5342 0.5043
-2.500 0.1986 0.01006 0.00320 -0.1010 0.5326 0.5106
-2.250 0.2273 0.01009 0.00320 -0.1013 0.5310 0.5151
-2.000 0.2560 0.01012 0.00317 -0.1016 0.5294 0.5182
-1.750 0.2847 0.01014 0.00314 -0.1020 0.5278 0.5203
-1.500 0.3133 0.01017 0.00312 -0.1023 0.5263 0.5222
-1.250 0.3417 0.01018 0.00310 -0.1026 0.5249 0.5240
-1.000 0.3700 0.01020 0.00310 -0.1029 0.5235 0.5260
-0.750 0.3984 0.01024 0.00311 -0.1031 0.5222 0.5277
-0.500 0.4267 0.01029 0.00312 -0.1034 0.5209 0.5292
-0.250 0.4551 0.01034 0.00314 -0.1038 0.5197 0.5308
0.000 0.4837 0.01037 0.00316 -0.1041 0.5186 0.5325
0.250 0.5122 0.01040 0.00319 -0.1044 0.5175 0.5341
0.500 0.5406 0.01045 0.00323 -0.1048 0.5163 0.5358
0.750 0.5690 0.01050 0.00327 -0.1051 0.5152 0.5375
1.000 0.5973 0.01054 0.00332 -0.1054 0.5140 0.5391
1.250 0.6254 0.01059 0.00338 -0.1057 0.5129 0.5408
1.500 0.6535 0.01064 0.00344 -0.1060 0.5118 0.5426
1.750 0.6816 0.01070 0.00351 -0.1063 0.5107 0.5446
2.000 0.7096 0.01077 0.00359 -0.1066 0.5097 0.5467
2.250 0.7376 0.01085 0.00367 -0.1068 0.5087 0.5490
2.500 0.7656 0.01093 0.00376 -0.1071 0.5078 0.5514
2.750 0.7936 0.01103 0.00385 -0.1074 0.5068 0.5539
3.000 0.8214 0.01113 0.00396 -0.1077 0.5056 0.5562
3.250 0.8494 0.01123 0.00409 -0.1080 0.5045 0.5586
3.500 0.8770 0.01130 0.00422 -0.1082 0.5038 0.5613
3.750 0.9046 0.01139 0.00435 -0.1085 0.5030 0.5641
4.000 0.9322 0.01148 0.00449 -0.1087 0.5022 0.5671
4.500 0.9870 0.01167 0.00479 -0.1092 0.5004 0.5729
4.750 1.0141 0.01176 0.00494 -0.1093 0.4992 0.5762
5.000 1.0410 0.01185 0.00510 -0.1094 0.4978 0.5799
5.250 1.0680 0.01196 0.00526 -0.1096 0.4967 0.5837
5.500 1.0950 0.01207 0.00543 -0.1097 0.4957 0.5874
5.750 1.1218 0.01218 0.00562 -0.1099 0.4948 0.5916
6.000 1.1484 0.01230 0.00580 -0.1100 0.4937 0.5964
6.250 1.1752 0.01243 0.00598 -0.1101 0.4926 0.6012
6.500 1.2020 0.01256 0.00618 -0.1103 0.4916 0.6062
6.750 1.2289 0.01271 0.00638 -0.1104 0.4901 0.6121
7.250 1.2795 0.01297 0.00684 -0.1102 0.4873 0.6242
7.500 1.3033 0.01307 0.00707 -0.1098 0.4851 0.6312
7.750 1.3268 0.01316 0.00727 -0.1093 0.4825 0.6382
8.000 1.3501 0.01325 0.00746 -0.1088 0.4798 0.6461
8.250 1.3693 0.01325 0.00749 -0.1074 0.4732 0.6545
8.500 1.3810 0.01322 0.00756 -0.1046 0.4618 0.6642
8.750 1.3869 0.01330 0.00769 -0.1007 0.4477 0.6746
9.000 1.3926 0.01357 0.00800 -0.0970 0.4314 0.6861
9.500 1.3779 0.01532 0.00958 -0.0864 0.3666 0.7121
9.750 1.3581 0.01715 0.01130 -0.0804 0.3337 0.7279
10.250 1.3241 0.02169 0.01579 -0.0712 0.2819 0.7700
10.500 1.3039 0.02485 0.01894 -0.0677 0.2545 0.8011
10.750 1.2929 0.02797 0.02215 -0.0659 0.2298 0.8541
11.250 1.2722 0.03647 0.03058 -0.0665 0.1705 1.0000
11.500 1.2593 0.04011 0.03414 -0.0651 0.1490 1.0000
11.750 1.2484 0.04369 0.03764 -0.0639 0.1285 1.0000
12.000 1.2406 0.04702 0.04090 -0.0629 0.1093 1.0000
12.250 1.2332 0.05038 0.04417 -0.0620 0.0902 1.0000
12.500 1.2273 0.05363 0.04733 -0.0612 0.0718 1.0000
12.750 1.2249 0.05659 0.05023 -0.0606 0.0581 1.0000
13.000 1.2234 0.05949 0.05307 -0.0600 0.0458 1.0000
13.250 1.2237 0.06226 0.05580 -0.0596 0.0365 1.0000
13.500 1.2255 0.06486 0.05838 -0.0593 0.0287 1.0000
13.750 1.2284 0.06741 0.06093 -0.0590 0.0235 1.0000
14.000 1.2329 0.06979 0.06332 -0.0588 0.0196 1.0000
14.250 1.2377 0.07218 0.06573 -0.0586 0.0171 1.0000
14.500 1.2419 0.07465 0.06822 -0.0585 0.0149 1.0000
14.750 1.2478 0.07691 0.07053 -0.0584 0.0138 1.0000
15.000 1.2530 0.07930 0.07295 -0.0583 0.0125 1.0000
15.250 1.2571 0.08183 0.07551 -0.0583 0.0115 1.0000
15.500 1.2625 0.08423 0.07796 -0.0583 0.0109 1.0000
15.750 1.2681 0.08663 0.08043 -0.0583 0.0103 1.0000
16.000 1.2729 0.08914 0.08300 -0.0584 0.0098 1.0000
16.250 1.2774 0.09166 0.08557 -0.0585 0.0093 1.0000
16.500 1.2805 0.09440 0.08836 -0.0587 0.0088 1.0000
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Polar data table (+)
Polar graphs
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