E169 (14.4%) (e169-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 50,000 Max Cl/Cd: 16.65 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e169-il-50000.txt Download as CSV file: xf-e169-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E169 (14.4%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5568 0.13694 0.12909 0.0278 1.0000 0.3390
-11.750 -0.5611 0.13374 0.12589 0.0267 1.0000 0.3466
-11.500 -0.6180 0.12098 0.11324 0.0159 1.0000 0.2697
-11.250 -0.5997 0.11786 0.11003 0.0165 1.0000 0.2812
-11.000 -0.6046 0.11244 0.10459 0.0144 1.0000 0.2806
-10.750 -0.6135 0.10679 0.09894 0.0122 1.0000 0.2807
-10.500 -0.6271 0.10069 0.09286 0.0095 1.0000 0.2815
-10.250 -0.6157 0.09822 0.09033 0.0101 1.0000 0.2947
-10.000 -0.5562 0.10757 0.09951 0.0208 1.0000 0.3902
-9.750 -0.5357 0.10282 0.09466 0.0201 1.0000 0.3943
-9.500 -0.6150 0.08705 0.07907 0.0085 1.0000 0.3238
-9.250 -0.6481 0.07977 0.07190 0.0053 1.0000 0.3275
-9.000 -0.6327 0.07810 0.07014 0.0065 1.0000 0.3412
-8.750 -0.6205 0.07611 0.06809 0.0074 1.0000 0.3549
-8.500 -0.6148 0.07337 0.06531 0.0078 1.0000 0.3667
-8.250 -0.6596 0.06584 0.05793 0.0054 1.0000 0.3727
-8.000 -0.6413 0.06475 0.05675 0.0070 1.0000 0.3866
-7.750 -0.6294 0.06293 0.05485 0.0082 1.0000 0.3993
-7.500 -0.6796 0.05496 0.04700 0.0064 1.0000 0.4080
-7.250 -0.6951 0.05047 0.04243 0.0066 1.0000 0.4209
-7.000 -0.6604 0.05113 0.04300 0.0088 1.0000 0.4345
-6.750 -0.6352 0.05070 0.04250 0.0106 1.0000 0.4473
-6.500 -0.6232 0.04893 0.04068 0.0118 1.0000 0.4597
-6.250 -0.6197 0.04640 0.03809 0.0127 1.0000 0.4723
-6.000 -0.6200 0.04351 0.03512 0.0135 1.0000 0.4852
-5.750 -0.6076 0.04193 0.03345 0.0147 1.0000 0.4981
-5.500 -0.5816 0.04155 0.03306 0.0164 1.0000 0.5090
-5.250 -0.5683 0.04008 0.03156 0.0177 1.0000 0.5211
-5.000 -0.5605 0.03822 0.02965 0.0190 1.0000 0.5336
-4.750 -0.5540 0.03637 0.02772 0.0203 1.0000 0.5467
-4.500 -0.5318 0.03598 0.02738 0.0222 1.0000 0.5574
-4.250 -0.5195 0.03487 0.02628 0.0240 1.0000 0.5686
-4.000 -0.5136 0.03354 0.02495 0.0259 1.0000 0.5808
-3.750 -0.5109 0.03238 0.02377 0.0282 1.0000 0.5928
-3.500 -0.5034 0.03193 0.02337 0.0311 1.0000 0.6022
-3.250 -0.5036 0.03107 0.02249 0.0336 1.0000 0.6133
-3.000 -0.5028 0.03019 0.02156 0.0354 1.0000 0.6256
-2.750 -0.4953 0.02992 0.02132 0.0376 1.0000 0.6357
-2.500 -0.4881 0.02949 0.02087 0.0391 1.0000 0.6473
-2.250 -0.4420 0.02944 0.02076 0.0342 0.9843 0.6637
-2.000 -0.3852 0.02943 0.02070 0.0279 0.9625 0.6815
-1.750 -0.3287 0.02934 0.02056 0.0221 0.9421 0.6991
-1.500 -0.2718 0.02921 0.02039 0.0164 0.9233 0.7172
-1.250 -0.2221 0.02905 0.02019 0.0122 0.9042 0.7345
-1.000 -0.1726 0.02888 0.02001 0.0084 0.8859 0.7517
-0.750 -0.1259 0.02878 0.01991 0.0055 0.8683 0.7681
-0.500 -0.0819 0.02869 0.01982 0.0032 0.8510 0.7844
-0.250 -0.0402 0.02864 0.01977 0.0015 0.8340 0.8008
0.000 0.0000 0.02861 0.01973 0.0000 0.8172 0.8172
0.250 0.0402 0.02864 0.01976 -0.0015 0.8008 0.8340
0.500 0.0818 0.02869 0.01981 -0.0032 0.7844 0.8509
0.750 0.1261 0.02878 0.01991 -0.0055 0.7680 0.8683
1.000 0.1726 0.02887 0.02000 -0.0084 0.7517 0.8859
1.250 0.2221 0.02905 0.02019 -0.0122 0.7344 0.9042
1.500 0.2719 0.02920 0.02039 -0.0164 0.7172 0.9232
1.750 0.3290 0.02934 0.02056 -0.0221 0.6992 0.9422
2.000 0.3851 0.02943 0.02070 -0.0279 0.6816 0.9625
2.250 0.4419 0.02943 0.02077 -0.0342 0.6637 0.9843
2.500 0.4881 0.02948 0.02087 -0.0391 0.6474 1.0000
2.750 0.4953 0.02993 0.02133 -0.0376 0.6357 1.0000
3.000 0.5028 0.03019 0.02155 -0.0354 0.6256 1.0000
3.250 0.5037 0.03106 0.02249 -0.0336 0.6133 1.0000
3.500 0.5034 0.03193 0.02337 -0.0311 0.6022 1.0000
3.750 0.5110 0.03237 0.02376 -0.0282 0.5929 1.0000
4.000 0.5137 0.03354 0.02495 -0.0259 0.5808 1.0000
4.250 0.5195 0.03487 0.02628 -0.0240 0.5686 1.0000
4.500 0.5318 0.03598 0.02738 -0.0222 0.5575 1.0000
4.750 0.5541 0.03636 0.02771 -0.0203 0.5467 1.0000
5.000 0.5606 0.03820 0.02963 -0.0190 0.5336 1.0000
5.250 0.5684 0.04008 0.03155 -0.0177 0.5211 1.0000
5.500 0.5816 0.04155 0.03306 -0.0164 0.5090 1.0000
5.750 0.6078 0.04191 0.03344 -0.0147 0.4981 1.0000
6.000 0.6201 0.04349 0.03509 -0.0135 0.4852 1.0000
6.250 0.6199 0.04637 0.03806 -0.0127 0.4723 1.0000
6.500 0.6235 0.04889 0.04064 -0.0118 0.4596 1.0000
6.750 0.6352 0.05068 0.04248 -0.0106 0.4472 1.0000
7.000 0.6606 0.05110 0.04298 -0.0088 0.4345 1.0000
7.250 0.6958 0.05040 0.04236 -0.0065 0.4210 1.0000
7.500 0.6763 0.05531 0.04734 -0.0066 0.4082 1.0000
7.750 0.6295 0.06293 0.05484 -0.0082 0.3994 1.0000
8.000 0.6416 0.06472 0.05672 -0.0070 0.3867 1.0000
8.250 0.6590 0.06590 0.05798 -0.0054 0.3726 1.0000
8.500 0.6151 0.07335 0.06529 -0.0079 0.3668 1.0000
8.750 0.6208 0.07610 0.06808 -0.0074 0.3549 1.0000
9.000 0.7179 0.06786 0.06023 0.0006 0.3288 1.0000
9.250 0.6477 0.07982 0.07194 -0.0054 0.3274 1.0000
9.500 0.6156 0.08696 0.07899 -0.0085 0.3236 1.0000
9.750 0.6252 0.08941 0.08150 -0.0080 0.3103 1.0000
10.000 0.6393 0.09152 0.08369 -0.0071 0.2971 1.0000
10.250 0.6161 0.09819 0.09029 -0.0101 0.2946 1.0000
10.500 0.6275 0.10067 0.09284 -0.0096 0.2814 1.0000
10.750 0.6136 0.10678 0.09892 -0.0122 0.2806 1.0000
11.000 0.6047 0.11242 0.10457 -0.0145 0.2804 1.0000
11.250 0.6002 0.11785 0.11001 -0.0166 0.2812 1.0000
11.500 0.6182 0.12098 0.11324 -0.0160 0.2698 1.0000
11.750 0.5634 0.13385 0.12601 -0.0268 0.3463 1.0000
12.000 0.5575 0.13694 0.12908 -0.0278 0.3390 1.0000
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Polar data table (+)
Polar graphs
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