FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.96 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66196v-il-1000000.txt Download as CSV file: xf-fx66196v-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6236 0.10159 0.09948 -0.0616 1.0000 0.0087
-16.750 -0.6450 0.09298 0.09074 -0.0666 1.0000 0.0087
-16.500 -0.6748 0.08351 0.08111 -0.0721 1.0000 0.0086
-16.250 -0.6950 0.07613 0.07357 -0.0765 1.0000 0.0086
-16.000 -0.7070 0.06938 0.06667 -0.0810 0.9626 0.0086
-15.750 -0.6933 0.06170 0.05870 -0.0929 0.9397 0.0087
-15.500 -0.6706 0.05461 0.05130 -0.1058 0.9196 0.0087
-15.250 -0.6601 0.04787 0.04415 -0.1164 0.8908 0.0090
-15.000 -0.6538 0.04435 0.04033 -0.1202 0.8589 0.0090
-14.750 -0.6527 0.04170 0.03749 -0.1215 0.8327 0.0093
-14.500 -0.6524 0.03932 0.03493 -0.1220 0.8150 0.0093
-14.250 -0.6504 0.03727 0.03271 -0.1222 0.7974 0.0093
-14.000 -0.6440 0.03566 0.03101 -0.1224 0.7821 0.0096
-13.750 -0.6384 0.03406 0.02928 -0.1223 0.7672 0.0096
-13.250 -0.6257 0.03105 0.02605 -0.1219 0.7419 0.0099
-13.000 -0.6191 0.02962 0.02450 -0.1214 0.7307 0.0100
-12.750 -0.6084 0.02856 0.02335 -0.1212 0.7200 0.0103
-12.500 -0.6013 0.02723 0.02192 -0.1205 0.7099 0.0104
-12.250 -0.5917 0.02610 0.02069 -0.1199 0.7008 0.0106
-12.000 -0.5817 0.02506 0.01956 -0.1192 0.6915 0.0109
-11.750 -0.5703 0.02409 0.01850 -0.1186 0.6835 0.0111
-11.250 -0.5451 0.02244 0.01669 -0.1172 0.6673 0.0115
-10.750 -0.5384 0.01975 0.01381 -0.1139 0.6533 0.0120
-10.500 -0.5323 0.01874 0.01273 -0.1122 0.6464 0.0121
-10.250 -0.5266 0.01788 0.01182 -0.1103 0.6405 0.0125
-10.000 -0.5223 0.01727 0.01115 -0.1076 0.6345 0.0127
-9.750 -0.5081 0.01679 0.01060 -0.1062 0.6286 0.0131
-9.500 -0.4918 0.01627 0.01003 -0.1051 0.6236 0.0135
-9.250 -0.4742 0.01577 0.00947 -0.1041 0.6181 0.0139
-9.000 -0.4549 0.01537 0.00898 -0.1032 0.6127 0.0143
-8.750 -0.4331 0.01501 0.00857 -0.1027 0.6082 0.0147
-8.500 -0.4166 0.01426 0.00776 -0.1017 0.6034 0.0156
-8.250 -0.3949 0.01387 0.00732 -0.1011 0.5986 0.0164
-8.000 -0.3714 0.01355 0.00695 -0.1008 0.5945 0.0173
-7.750 -0.3468 0.01327 0.00663 -0.1007 0.5905 0.0182
-7.500 -0.3236 0.01288 0.00618 -0.1003 0.5864 0.0194
-7.250 -0.2999 0.01254 0.00580 -0.1001 0.5823 0.0210
-7.000 -0.2742 0.01227 0.00550 -0.1001 0.5792 0.0225
-6.750 -0.2488 0.01195 0.00514 -0.1000 0.5760 0.0246
-6.500 -0.2231 0.01166 0.00484 -0.1000 0.5727 0.0275
-6.250 -0.1974 0.01141 0.00455 -0.0999 0.5695 0.0316
-6.000 -0.1715 0.01120 0.00431 -0.0999 0.5659 0.0370
-5.750 -0.1450 0.01087 0.00404 -0.1001 0.5639 0.0482
-5.500 -0.1185 0.01054 0.00379 -0.1002 0.5615 0.0658
-5.250 -0.0927 0.01014 0.00351 -0.1004 0.5589 0.0994
-5.000 -0.0672 0.00967 0.00323 -0.1005 0.5562 0.1514
-4.750 -0.0426 0.00908 0.00291 -0.1006 0.5537 0.2283
-4.500 -0.0192 0.00832 0.00254 -0.1007 0.5508 0.3392
-4.250 0.0068 0.00789 0.00243 -0.1008 0.5491 0.4379
-4.000 0.0358 0.00787 0.00240 -0.1012 0.5473 0.4569
-3.750 0.0649 0.00787 0.00240 -0.1016 0.5454 0.4706
-3.500 0.0940 0.00789 0.00239 -0.1019 0.5434 0.4791
-3.250 0.1231 0.00795 0.00240 -0.1023 0.5415 0.4876
-3.000 0.1518 0.00798 0.00240 -0.1026 0.5395 0.4946
-2.750 0.1805 0.00807 0.00244 -0.1028 0.5374 0.5020
-2.500 0.2091 0.00817 0.00248 -0.1031 0.5351 0.5085
-2.250 0.2381 0.00818 0.00250 -0.1035 0.5340 0.5143
-2.000 0.2673 0.00822 0.00253 -0.1039 0.5327 0.5190
-1.750 0.2964 0.00828 0.00254 -0.1043 0.5313 0.5221
-1.500 0.3252 0.00825 0.00251 -0.1046 0.5298 0.5250
-1.250 0.3540 0.00825 0.00251 -0.1050 0.5284 0.5272
-1.000 0.3828 0.00828 0.00251 -0.1053 0.5269 0.5292
-0.750 0.4115 0.00831 0.00252 -0.1057 0.5255 0.5310
-0.500 0.4402 0.00835 0.00254 -0.1060 0.5241 0.5328
-0.250 0.4687 0.00842 0.00257 -0.1063 0.5225 0.5348
0.000 0.4973 0.00851 0.00262 -0.1067 0.5208 0.5364
0.250 0.5261 0.00857 0.00266 -0.1071 0.5196 0.5376
0.500 0.5548 0.00858 0.00267 -0.1075 0.5188 0.5391
0.750 0.5834 0.00858 0.00270 -0.1078 0.5179 0.5411
1.000 0.6120 0.00860 0.00274 -0.1082 0.5170 0.5429
1.250 0.6406 0.00864 0.00279 -0.1085 0.5160 0.5448
1.500 0.6691 0.00868 0.00284 -0.1089 0.5150 0.5466
1.750 0.6977 0.00873 0.00289 -0.1093 0.5139 0.5486
2.000 0.7262 0.00879 0.00295 -0.1096 0.5128 0.5506
2.250 0.7546 0.00884 0.00301 -0.1100 0.5118 0.5525
2.500 0.7830 0.00891 0.00308 -0.1103 0.5108 0.5543
2.750 0.8111 0.00895 0.00315 -0.1106 0.5098 0.5571
3.000 0.8393 0.00902 0.00324 -0.1109 0.5089 0.5596
3.250 0.8675 0.00910 0.00334 -0.1113 0.5079 0.5622
3.500 0.8958 0.00922 0.00346 -0.1117 0.5068 0.5650
3.750 0.9244 0.00938 0.00362 -0.1121 0.5053 0.5678
4.000 0.9527 0.00948 0.00374 -0.1125 0.5043 0.5705
4.250 0.9804 0.00950 0.00384 -0.1127 0.5037 0.5741
4.500 1.0082 0.00956 0.00395 -0.1130 0.5030 0.5775
4.750 1.0360 0.00963 0.00406 -0.1133 0.5023 0.5812
5.000 1.0638 0.00971 0.00419 -0.1136 0.5015 0.5846
5.250 1.0913 0.00977 0.00431 -0.1138 0.5005 0.5887
5.500 1.1187 0.00983 0.00443 -0.1140 0.4994 0.5932
5.750 1.1462 0.00991 0.00456 -0.1142 0.4983 0.5981
6.000 1.1735 0.00998 0.00467 -0.1144 0.4970 0.6030
6.250 1.2006 0.01005 0.00480 -0.1146 0.4958 0.6087
6.500 1.2277 0.01013 0.00493 -0.1148 0.4945 0.6148
6.750 1.2545 0.01021 0.00506 -0.1149 0.4929 0.6211
7.000 1.2818 0.01036 0.00525 -0.1152 0.4908 0.6283
7.250 1.3081 0.01048 0.00544 -0.1152 0.4886 0.6357
7.500 1.3298 0.01032 0.00540 -0.1142 0.4842 0.6441
7.750 1.3501 0.01022 0.00530 -0.1130 0.4761 0.6530
8.000 1.3713 0.01015 0.00533 -0.1119 0.4687 0.6633
8.250 1.3901 0.01022 0.00541 -0.1105 0.4595 0.6744
8.500 1.4130 0.01023 0.00553 -0.1098 0.4525 0.6867
8.750 1.4317 0.01036 0.00570 -0.1084 0.4464 0.7003
9.000 1.4507 0.01044 0.00588 -0.1070 0.4387 0.7155
9.250 1.4649 0.01063 0.00612 -0.1047 0.4269 0.7328
9.500 1.4683 0.01109 0.00653 -0.1006 0.3949 0.7536
9.750 1.4521 0.01224 0.00753 -0.0934 0.3563 0.7799
10.000 1.4310 0.01377 0.00898 -0.0862 0.3189 0.8183
10.250 1.4171 0.01551 0.01082 -0.0813 0.2848 0.9151
10.500 1.4184 0.01967 0.01474 -0.0837 0.2234 1.0000
10.750 1.4072 0.02296 0.01788 -0.0819 0.1920 1.0000
11.000 1.3915 0.02681 0.02160 -0.0801 0.1609 1.0000
11.250 1.3795 0.03039 0.02509 -0.0786 0.1382 1.0000
11.500 1.3618 0.03446 0.02906 -0.0769 0.1131 1.0000
11.750 1.3484 0.03824 0.03275 -0.0754 0.0919 1.0000
12.000 1.3384 0.04178 0.03622 -0.0742 0.0743 1.0000
12.250 1.3299 0.04522 0.03960 -0.0731 0.0581 1.0000
12.500 1.3231 0.04853 0.04285 -0.0722 0.0448 1.0000
12.750 1.3200 0.05152 0.04580 -0.0714 0.0341 1.0000
13.000 1.3176 0.05447 0.04872 -0.0707 0.0256 1.0000
13.250 1.3168 0.05728 0.05151 -0.0700 0.0199 1.0000
13.500 1.3193 0.05978 0.05402 -0.0695 0.0165 1.0000
13.750 1.3217 0.06234 0.05660 -0.0691 0.0147 1.0000
14.000 1.3269 0.06460 0.05889 -0.0688 0.0135 1.0000
14.250 1.3319 0.06687 0.06119 -0.0684 0.0124 1.0000
14.500 1.3324 0.06965 0.06401 -0.0680 0.0113 1.0000
14.750 1.3392 0.07178 0.06618 -0.0678 0.0108 1.0000
15.000 1.3448 0.07405 0.06851 -0.0676 0.0102 1.0000
15.250 1.3488 0.07650 0.07099 -0.0674 0.0096 1.0000
15.500 1.3527 0.07893 0.07346 -0.0671 0.0092 1.0000
15.750 1.3522 0.08188 0.07646 -0.0668 0.0087 1.0000
16.000 1.3555 0.08444 0.07908 -0.0667 0.0084 1.0000
16.250 1.3612 0.08671 0.08140 -0.0666 0.0081 1.0000
16.500 1.3649 0.08925 0.08399 -0.0665 0.0077 1.0000
16.750 1.3676 0.09186 0.08665 -0.0664 0.0075 1.0000
17.000 1.3708 0.09440 0.08923 -0.0663 0.0072 1.0000
17.250 1.3724 0.09719 0.09208 -0.0663 0.0070 1.0000
17.500 1.3706 0.10038 0.09532 -0.0663 0.0067 1.0000
17.750 1.3673 0.10378 0.09879 -0.0663 0.0065 1.0000
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