FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.97 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61140-il-1000000.txt Download as CSV file: xf-fx61140-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4488 0.08278 0.08128 -0.0423 1.0000 0.0084
-9.750 -0.4732 0.07097 0.06945 -0.0506 1.0000 0.0081
-9.500 -0.5012 0.06374 0.06215 -0.0546 1.0000 0.0078
-9.250 -0.5271 0.05924 0.05758 -0.0553 1.0000 0.0079
-9.000 -0.5447 0.05379 0.05200 -0.0591 0.9979 0.0077
-8.750 -0.5401 0.04747 0.04545 -0.0673 0.9923 0.0079
-8.500 -0.5544 0.02978 0.02670 -0.0747 0.9854 0.0058
-8.250 -0.5430 0.02269 0.01888 -0.0758 0.9790 0.0056
-8.000 -0.5120 0.02065 0.01658 -0.0776 0.9761 0.0061
-7.750 -0.4777 0.01939 0.01514 -0.0798 0.9740 0.0064
-7.500 -0.4513 0.01832 0.01392 -0.0801 0.9679 0.0065
-7.000 -0.3963 0.01449 0.00973 -0.0813 0.9563 0.0068
-6.500 -0.3309 0.01240 0.00750 -0.0846 0.9399 0.0074
-6.250 -0.2845 0.01175 0.00682 -0.0890 0.9320 0.0080
-6.000 -0.2277 0.01090 0.00588 -0.0958 0.9198 0.0087
-5.750 -0.1688 0.01021 0.00504 -0.1030 0.8960 0.0096
-5.500 -0.1297 0.00954 0.00412 -0.1060 0.8578 0.0111
-5.250 -0.1023 0.00939 0.00380 -0.1061 0.8218 0.0127
-5.000 -0.0767 0.00931 0.00355 -0.1058 0.7900 0.0142
-4.750 -0.0501 0.00900 0.00311 -0.1059 0.7630 0.0194
-4.500 -0.0229 0.00880 0.00283 -0.1060 0.7393 0.0282
-4.000 0.0372 0.00766 0.00216 -0.1085 0.6969 0.1996
-3.750 0.0745 0.00654 0.00172 -0.1121 0.6784 0.4149
-3.500 0.1072 0.00620 0.00158 -0.1137 0.6614 0.5103
-3.250 0.1373 0.00614 0.00153 -0.1143 0.6457 0.5517
-3.000 0.1667 0.00615 0.00152 -0.1147 0.6311 0.5770
-2.750 0.1959 0.00620 0.00155 -0.1150 0.6176 0.6015
-2.500 0.2249 0.00629 0.00159 -0.1152 0.6047 0.6207
-2.250 0.2536 0.00639 0.00163 -0.1154 0.5928 0.6309
-2.000 0.2826 0.00649 0.00163 -0.1156 0.5819 0.6380
-1.750 0.3110 0.00657 0.00167 -0.1157 0.5716 0.6432
-1.500 0.3398 0.00666 0.00169 -0.1160 0.5616 0.6482
-1.250 0.3689 0.00674 0.00171 -0.1162 0.5525 0.6529
-0.750 0.4261 0.00690 0.00179 -0.1166 0.5361 0.6602
-0.500 0.4547 0.00700 0.00182 -0.1168 0.5283 0.6640
-0.250 0.4838 0.00707 0.00185 -0.1170 0.5207 0.6673
0.000 0.5121 0.00715 0.00190 -0.1172 0.5136 0.6701
0.250 0.5409 0.00722 0.00196 -0.1174 0.5066 0.6730
0.500 0.5692 0.00732 0.00202 -0.1175 0.4997 0.6760
0.750 0.5983 0.00739 0.00207 -0.1178 0.4931 0.6791
1.000 0.6267 0.00750 0.00212 -0.1180 0.4864 0.6818
1.250 0.6554 0.00755 0.00219 -0.1182 0.4805 0.6843
1.500 0.6836 0.00764 0.00226 -0.1183 0.4742 0.6867
1.750 0.7121 0.00773 0.00235 -0.1185 0.4684 0.6891
2.000 0.7407 0.00781 0.00242 -0.1187 0.4626 0.6916
2.250 0.7690 0.00793 0.00250 -0.1189 0.4568 0.6939
2.500 0.7979 0.00799 0.00258 -0.1192 0.4515 0.6960
2.750 0.8260 0.00807 0.00266 -0.1193 0.4454 0.6981
3.000 0.8541 0.00816 0.00277 -0.1194 0.4398 0.7001
3.250 0.8823 0.00825 0.00287 -0.1196 0.4336 0.7021
3.500 0.9101 0.00838 0.00299 -0.1196 0.4272 0.7044
3.750 0.9386 0.00847 0.00310 -0.1198 0.4212 0.7066
4.000 0.9665 0.00861 0.00322 -0.1200 0.4149 0.7086
4.250 0.9948 0.00869 0.00334 -0.1202 0.4087 0.7106
4.500 1.0223 0.00881 0.00346 -0.1202 0.4011 0.7125
4.750 1.0501 0.00892 0.00360 -0.1203 0.3927 0.7143
5.000 1.0774 0.00907 0.00374 -0.1203 0.3803 0.7163
5.250 1.1040 0.00928 0.00388 -0.1202 0.3607 0.7183
5.500 1.1306 0.00951 0.00407 -0.1201 0.3446 0.7202
5.750 1.1570 0.00977 0.00427 -0.1200 0.3259 0.7222
6.000 1.1826 0.01010 0.00450 -0.1198 0.3022 0.7238
6.250 1.2075 0.01046 0.00477 -0.1195 0.2759 0.7257
6.500 1.2313 0.01094 0.00513 -0.1190 0.2450 0.7274
6.750 1.2524 0.01168 0.00563 -0.1181 0.1985 0.7292
7.000 1.2692 0.01284 0.00641 -0.1166 0.1335 0.7311
7.250 1.2861 0.01396 0.00722 -0.1151 0.0814 0.7330
7.500 1.3044 0.01492 0.00797 -0.1138 0.0460 0.7348
7.750 1.3244 0.01569 0.00861 -0.1127 0.0263 0.7367
8.250 1.3648 0.01706 0.00991 -0.1106 0.0072 0.7402
8.500 1.3851 0.01769 0.01056 -0.1095 0.0048 0.7420
8.750 1.4053 0.01828 0.01121 -0.1085 0.0041 0.7438
9.000 1.4233 0.01903 0.01203 -0.1070 0.0035 0.7457
9.250 1.4415 0.01971 0.01279 -0.1056 0.0033 0.7476
9.500 1.4587 0.02041 0.01358 -0.1041 0.0031 0.7496
9.750 1.4739 0.02119 0.01443 -0.1023 0.0030 0.7514
10.000 1.4847 0.02198 0.01531 -0.0997 0.0029 0.7531
10.250 1.4930 0.02287 0.01631 -0.0968 0.0028 0.7550
10.500 1.5001 0.02387 0.01741 -0.0938 0.0027 0.7568
10.750 1.5055 0.02500 0.01864 -0.0908 0.0027 0.7587
11.000 1.5097 0.02628 0.02002 -0.0880 0.0026 0.7609
11.250 1.5119 0.02777 0.02162 -0.0852 0.0026 0.7630
11.500 1.5126 0.02950 0.02346 -0.0826 0.0026 0.7650
11.750 1.5126 0.03146 0.02552 -0.0805 0.0025 0.7667
12.000 1.5114 0.03371 0.02789 -0.0787 0.0025 0.7688
12.250 1.5087 0.03633 0.03064 -0.0774 0.0025 0.7707
12.500 1.5059 0.03921 0.03365 -0.0765 0.0025 0.7727
12.750 1.5018 0.04247 0.03704 -0.0760 0.0025 0.7747
13.000 1.4977 0.04596 0.04065 -0.0758 0.0025 0.7768
13.250 1.4931 0.04969 0.04450 -0.0760 0.0025 0.7787
13.500 1.4869 0.05378 0.04871 -0.0764 0.0025 0.7803
13.750 1.4823 0.05781 0.05287 -0.0771 0.0025 0.7820
14.000 1.4758 0.06221 0.05740 -0.0779 0.0025 0.7837
14.250 1.4704 0.06659 0.06192 -0.0789 0.0024 0.7853
14.500 1.4644 0.07120 0.06665 -0.0801 0.0024 0.7869
14.750 1.4574 0.07608 0.07165 -0.0814 0.0024 0.7885
15.000 1.4536 0.08063 0.07630 -0.0829 0.0024 0.7902
15.250 1.4472 0.08571 0.08151 -0.0846 0.0024 0.7919
15.500 1.4412 0.09082 0.08672 -0.0865 0.0023 0.7935
15.750 1.4350 0.09610 0.09212 -0.0884 0.0023 0.7949
16.000 1.4298 0.10135 0.09750 -0.0906 0.0023 0.7968
16.250 1.4219 0.10711 0.10339 -0.0930 0.0023 0.7982
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