EPPLER 635 AIRFOIL (e635-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 635 AIRFOIL (e635-il) Reynolds number: 50,000 Max Cl/Cd: 23.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e635-il-50000-n5.txt Download as CSV file: xf-e635-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 635 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4869 0.12094 0.11467 0.0136 1.0000 0.1108
-10.000 -0.4856 0.11734 0.11113 0.0118 1.0000 0.1141
-9.500 -0.5161 0.11094 0.10499 0.0019 1.0000 0.1191
-9.250 -0.4918 0.10573 0.09978 0.0047 1.0000 0.1212
-9.000 -0.4856 0.10173 0.09583 0.0039 1.0000 0.1229
-8.750 -0.4166 0.08431 0.07878 -0.0102 1.0000 0.0602
-8.500 -0.5033 0.08687 0.08091 -0.0085 1.0000 0.0596
-8.250 -0.5031 0.08296 0.07705 -0.0086 1.0000 0.0575
-8.000 -0.5089 0.07906 0.07316 -0.0088 1.0000 0.0556
-7.750 -0.5141 0.07494 0.06900 -0.0092 1.0000 0.0541
-7.500 -0.5192 0.07068 0.06464 -0.0092 1.0000 0.0523
-7.250 -0.5215 0.06659 0.06039 -0.0086 1.0000 0.0514
-7.000 -0.5202 0.06281 0.05642 -0.0076 1.0000 0.0509
-6.750 -0.5143 0.05947 0.05295 -0.0065 1.0000 0.0513
-6.500 -0.5088 0.05593 0.04916 -0.0050 1.0000 0.0509
-6.250 -0.5020 0.05250 0.04538 -0.0030 1.0000 0.0501
-6.000 -0.4930 0.04973 0.04210 -0.0006 1.0000 0.0490
-5.750 -0.4769 0.04653 0.03868 0.0000 0.9724 0.0488
-5.500 -0.4441 0.04279 0.03438 -0.0019 0.9133 0.0488
-5.250 -0.4151 0.03964 0.03091 -0.0029 0.8743 0.0506
-5.000 -0.3902 0.03766 0.02863 -0.0026 0.8415 0.0532
-4.750 -0.3678 0.03572 0.02622 -0.0010 0.8142 0.0550
-4.500 -0.3443 0.03380 0.02379 0.0006 0.7911 0.0557
-4.250 -0.3188 0.03203 0.02155 0.0019 0.7691 0.0569
-4.000 -0.2913 0.03053 0.01959 0.0029 0.7496 0.0592
-3.750 -0.2620 0.02912 0.01786 0.0034 0.7316 0.0632
-3.500 -0.2292 0.02783 0.01641 0.0031 0.7134 0.0670
-3.250 -0.1925 0.02668 0.01498 0.0023 0.6964 0.0710
-3.000 -0.1600 0.02576 0.01378 0.0022 0.6808 0.0763
-2.750 -0.1330 0.02501 0.01291 0.0027 0.6664 0.0866
-2.500 0.0664 0.02173 0.01246 -0.0231 0.6408 1.0000
-2.250 0.0885 0.02168 0.01201 -0.0223 0.6278 1.0000
-2.000 0.1108 0.02165 0.01166 -0.0216 0.6154 1.0000
-1.750 0.1332 0.02164 0.01136 -0.0209 0.6037 1.0000
-1.500 0.1556 0.02166 0.01110 -0.0201 0.5933 1.0000
-1.250 0.1783 0.02170 0.01088 -0.0194 0.5829 1.0000
-1.000 0.2014 0.02177 0.01075 -0.0188 0.5725 1.0000
-0.750 0.2242 0.02185 0.01061 -0.0181 0.5636 1.0000
-0.500 0.2473 0.02196 0.01055 -0.0175 0.5541 1.0000
-0.250 0.2703 0.02211 0.01054 -0.0168 0.5454 1.0000
0.250 0.3162 0.02245 0.01060 -0.0155 0.5287 1.0000
0.500 0.3388 0.02262 0.01061 -0.0147 0.5217 1.0000
0.750 0.3625 0.02289 0.01082 -0.0143 0.5134 1.0000
1.000 0.3855 0.02309 0.01089 -0.0135 0.5067 1.0000
1.250 0.4089 0.02342 0.01118 -0.0131 0.4988 1.0000
1.500 0.4317 0.02368 0.01135 -0.0123 0.4925 1.0000
1.750 0.4546 0.02405 0.01169 -0.0118 0.4855 1.0000
2.000 0.4773 0.02438 0.01198 -0.0111 0.4788 1.0000
2.250 0.4999 0.02475 0.01229 -0.0104 0.4729 1.0000
2.500 0.5225 0.02522 0.01279 -0.0099 0.4659 1.0000
2.750 0.5449 0.02551 0.01300 -0.0090 0.4610 1.0000
3.000 0.5670 0.02614 0.01373 -0.0086 0.4537 1.0000
3.250 0.5891 0.02655 0.01412 -0.0078 0.4482 1.0000
3.500 0.6110 0.02707 0.01466 -0.0071 0.4428 1.0000
4.000 0.6542 0.02811 0.01577 -0.0056 0.4316 1.0000
4.250 0.6745 0.02897 0.01676 -0.0051 0.4252 1.0000
4.500 0.6953 0.02960 0.01745 -0.0043 0.4197 1.0000
4.750 0.7174 0.02995 0.01779 -0.0032 0.4157 1.0000
5.000 0.7349 0.03117 0.01924 -0.0028 0.4085 1.0000
5.250 0.7554 0.03179 0.01992 -0.0019 0.4037 1.0000
5.500 0.7756 0.03245 0.02062 -0.0009 0.3992 1.0000
5.750 0.7911 0.03379 0.02221 -0.0002 0.3924 1.0000
6.000 0.8115 0.03434 0.02281 0.0009 0.3880 1.0000
6.250 0.8271 0.03559 0.02422 0.0018 0.3824 1.0000
6.500 0.8414 0.03690 0.02569 0.0027 0.3763 1.0000
6.750 0.8626 0.03730 0.02613 0.0039 0.3723 1.0000
7.000 0.8692 0.03943 0.02855 0.0049 0.3652 1.0000
7.250 0.8845 0.04045 0.02969 0.0062 0.3599 1.0000
7.500 0.9091 0.04045 0.02971 0.0075 0.3564 1.0000
7.750 0.9004 0.04388 0.03343 0.0088 0.3475 1.0000
8.000 0.9219 0.04412 0.03374 0.0101 0.3432 1.0000
8.250 0.9072 0.04786 0.03768 0.0117 0.3348 1.0000
8.500 0.9232 0.04850 0.03846 0.0132 0.3297 1.0000
8.750 0.8976 0.05307 0.04312 0.0148 0.3215 1.0000
9.000 0.9049 0.05438 0.04453 0.0163 0.3156 1.0000
9.250 0.9439 0.05275 0.04302 0.0179 0.3123 1.0000
9.500 0.8570 0.06326 0.05341 0.0181 0.3001 1.0000
10.000 0.8392 0.07035 0.06057 0.0183 0.2850 1.0000
10.500 0.8326 0.07633 0.06664 0.0186 0.2703 1.0000
11.000 0.8291 0.08218 0.07261 0.0186 0.2558 1.0000
11.250 0.7998 0.08910 0.07949 0.0164 0.2450 1.0000
11.500 0.8230 0.08859 0.07912 0.0181 0.2406 1.0000
11.750 0.8007 0.09475 0.08529 0.0161 0.2305 1.0000
12.000 0.7968 0.09835 0.08893 0.0155 0.2231 1.0000
12.250 0.8017 0.10059 0.09126 0.0156 0.2162 1.0000
12.500 0.7933 0.10508 0.09579 0.0144 0.2085 1.0000
12.750 0.8036 0.10640 0.09726 0.0149 0.2019 1.0000
13.000 0.7914 0.11169 0.10257 0.0132 0.1940 1.0000
13.250 0.8028 0.11295 0.10395 0.0137 0.1881 1.0000
13.500 0.7902 0.11848 0.10949 0.0117 0.1803 1.0000
13.750 0.8041 0.11916 0.11031 0.0125 0.1743 1.0000
14.000 0.7896 0.12545 0.11660 0.0101 0.1671 1.0000
14.250 0.8005 0.12675 0.11802 0.0104 0.1613 1.0000
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Polar data table (+)
Polar graphs
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