EPPLER 636 AIRFOIL (e636-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 636 AIRFOIL (e636-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.7 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e636-il-1000000.txt Download as CSV file: xf-e636-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 636 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4558 0.09179 0.09031 -0.0078 1.0000 0.0113
-9.500 -0.4553 0.08845 0.08698 -0.0091 1.0000 0.0115
-9.250 -0.4578 0.08368 0.08222 -0.0121 0.9592 0.0115
-9.000 -0.4352 0.07906 0.07710 -0.0205 0.8063 0.0117
-8.750 -0.4477 0.07501 0.07288 -0.0233 0.7577 0.0118
-8.500 -0.4645 0.07084 0.06860 -0.0244 0.7315 0.0118
-8.250 -0.4785 0.06763 0.06528 -0.0231 0.7114 0.0118
-8.000 -0.4826 0.06455 0.06211 -0.0225 0.6933 0.0120
-7.750 -0.4824 0.06162 0.05907 -0.0220 0.6767 0.0122
-7.500 -0.4827 0.05793 0.05524 -0.0212 0.6625 0.0123
-7.250 -0.4795 0.05453 0.05170 -0.0203 0.6491 0.0126
-7.000 -0.4742 0.05105 0.04805 -0.0191 0.6365 0.0130
-6.750 -0.4675 0.04704 0.04385 -0.0174 0.6248 0.0137
-6.500 -0.4546 0.04158 0.03805 -0.0148 0.6151 0.0146
-6.250 -0.4473 0.03746 0.03361 -0.0120 0.6050 0.0147
-6.000 -0.4548 0.03052 0.02619 -0.0076 0.5973 0.0151
-5.750 -0.4369 0.02920 0.02477 -0.0065 0.5855 0.0154
-5.500 -0.4186 0.02780 0.02322 -0.0052 0.5742 0.0156
-5.250 -0.3997 0.02641 0.02165 -0.0039 0.5633 0.0160
-5.000 -0.3799 0.02491 0.01998 -0.0025 0.5531 0.0166
-4.750 -0.3587 0.02321 0.01798 -0.0007 0.5435 0.0182
-4.500 -0.3429 0.02021 0.01445 0.0021 0.5344 0.0198
-4.250 -0.3192 0.01921 0.01340 0.0027 0.5245 0.0204
-4.000 -0.2950 0.01838 0.01245 0.0034 0.5149 0.0210
-3.750 -0.2702 0.01762 0.01155 0.0042 0.5058 0.0223
-3.500 -0.2435 0.01397 0.00737 0.0060 0.4985 0.0164
-3.250 -0.2170 0.01329 0.00658 0.0064 0.4893 0.0167
-3.000 -0.1907 0.01240 0.00556 0.0071 0.4809 0.0163
-2.750 -0.1652 0.01176 0.00482 0.0078 0.4727 0.0164
-2.500 -0.1397 0.01129 0.00431 0.0085 0.4655 0.0167
-2.250 -0.1145 0.01091 0.00387 0.0092 0.4578 0.0171
-2.000 -0.0889 0.01060 0.00352 0.0098 0.4509 0.0177
-1.750 -0.0636 0.01033 0.00318 0.0105 0.4434 0.0181
-1.500 -0.0379 0.01008 0.00289 0.0111 0.4370 0.0184
-1.250 -0.0120 0.00989 0.00265 0.0117 0.4306 0.0187
-1.000 0.0137 0.00970 0.00240 0.0122 0.4243 0.0193
-0.750 0.0393 0.00944 0.00211 0.0129 0.4186 0.0207
-0.500 0.0655 0.00932 0.00194 0.0134 0.4124 0.0219
-0.250 0.0921 0.00922 0.00181 0.0137 0.4072 0.0237
0.000 0.1188 0.00913 0.00170 0.0141 0.4020 0.0285
0.250 0.1417 0.00872 0.00163 0.0151 0.3969 0.1404
0.500 0.1333 0.00652 0.00141 0.0221 0.3941 0.7454
0.750 0.1806 0.00625 0.00174 0.0185 0.3881 0.9360
1.000 0.2223 0.00659 0.00201 0.0159 0.3825 0.9509
1.250 0.2589 0.00691 0.00227 0.0144 0.3781 0.9596
1.500 0.3284 0.00747 0.00275 0.0060 0.3717 0.9653
1.750 0.3579 0.00774 0.00295 0.0058 0.3669 0.9717
2.000 0.3923 0.00777 0.00294 0.0044 0.3632 0.9723
2.250 0.4263 0.00780 0.00295 0.0031 0.3591 0.9731
2.500 0.4596 0.00787 0.00296 0.0019 0.3549 0.9740
2.750 0.4923 0.00796 0.00300 0.0008 0.3504 0.9750
3.000 0.5248 0.00799 0.00302 -0.0003 0.3471 0.9761
3.250 0.5564 0.00804 0.00306 -0.0011 0.3432 0.9775
3.500 0.5869 0.00812 0.00311 -0.0018 0.3393 0.9792
3.750 0.6152 0.00823 0.00319 -0.0020 0.3355 0.9813
4.000 0.6404 0.00832 0.00329 -0.0014 0.3323 0.9839
4.250 0.6739 0.00834 0.00330 -0.0028 0.3287 0.9846
4.500 0.7066 0.00840 0.00333 -0.0040 0.3247 0.9853
4.750 0.7387 0.00847 0.00339 -0.0050 0.3207 0.9861
5.000 0.7711 0.00849 0.00343 -0.0061 0.3175 0.9871
5.250 0.8029 0.00855 0.00348 -0.0071 0.3137 0.9882
5.500 0.8337 0.00864 0.00356 -0.0079 0.3096 0.9895
5.750 0.8638 0.00873 0.00365 -0.0086 0.3056 0.9908
6.000 0.8939 0.00878 0.00373 -0.0092 0.3015 0.9923
6.250 0.9227 0.00889 0.00383 -0.0096 0.2964 0.9938
6.500 0.9537 0.00899 0.00393 -0.0105 0.2917 0.9947
6.750 0.9856 0.00901 0.00399 -0.0116 0.2877 0.9955
7.000 1.0169 0.00908 0.00406 -0.0126 0.2828 0.9964
7.250 1.0479 0.00921 0.00419 -0.0135 0.2776 0.9976
7.500 1.0792 0.00925 0.00427 -0.0145 0.2727 0.9986
7.750 1.1098 0.00938 0.00440 -0.0154 0.2669 0.9995
8.000 1.1376 0.00949 0.00454 -0.0157 0.2611 1.0000
8.250 1.1610 0.00964 0.00469 -0.0150 0.2539 1.0000
8.500 1.1841 0.00981 0.00486 -0.0144 0.2444 1.0000
8.750 1.2065 0.01005 0.00508 -0.0136 0.2359 1.0000
9.000 1.2294 0.01024 0.00528 -0.0129 0.2264 1.0000
9.250 1.2512 0.01051 0.00553 -0.0121 0.2142 1.0000
9.500 1.2725 0.01082 0.00581 -0.0112 0.2020 1.0000
9.750 1.2923 0.01126 0.00618 -0.0101 0.1850 1.0000
10.000 1.3105 0.01180 0.00664 -0.0089 0.1656 1.0000
10.250 1.3256 0.01257 0.00726 -0.0072 0.1400 1.0000
10.500 1.3406 0.01329 0.00789 -0.0055 0.1200 1.0000
10.750 1.3546 0.01404 0.00855 -0.0036 0.1034 1.0000
11.000 1.3678 0.01479 0.00923 -0.0016 0.0879 1.0000
11.250 1.3784 0.01565 0.01002 0.0007 0.0721 1.0000
11.500 1.3881 0.01648 0.01080 0.0031 0.0599 1.0000
11.750 1.3944 0.01743 0.01168 0.0060 0.0480 1.0000
12.000 1.3980 0.01842 0.01263 0.0093 0.0377 1.0000
12.250 1.3981 0.01947 0.01365 0.0130 0.0296 1.0000
12.500 1.3806 0.02059 0.01477 0.0196 0.0222 1.0000
12.750 1.3647 0.02224 0.01644 0.0242 0.0161 1.0000
13.000 1.3511 0.02472 0.01895 0.0264 0.0112 1.0000
13.250 1.3450 0.02730 0.02159 0.0272 0.0093 1.0000
13.500 1.3418 0.02992 0.02429 0.0274 0.0086 1.0000
13.750 1.3332 0.03328 0.02775 0.0273 0.0074 1.0000
14.000 1.3295 0.03622 0.03078 0.0271 0.0071 1.0000
14.250 1.3221 0.03961 0.03426 0.0268 0.0069 1.0000
14.500 1.3137 0.04318 0.03792 0.0264 0.0066 1.0000
14.750 1.3028 0.04706 0.04189 0.0258 0.0064 1.0000
15.000 1.2917 0.05104 0.04596 0.0252 0.0062 1.0000
15.250 1.2740 0.05585 0.05087 0.0243 0.0057 1.0000
15.500 1.2657 0.05968 0.05479 0.0234 0.0057 1.0000
15.750 1.2563 0.06379 0.05898 0.0224 0.0056 1.0000
16.000 1.2448 0.06830 0.06359 0.0213 0.0056 1.0000
16.250 1.2399 0.07197 0.06733 0.0203 0.0055 1.0000
16.500 1.2314 0.07621 0.07166 0.0190 0.0055 1.0000
16.750 1.2218 0.08069 0.07623 0.0177 0.0054 1.0000
17.000 1.2144 0.08489 0.08051 0.0164 0.0053 1.0000
17.250 1.2062 0.08930 0.08500 0.0150 0.0051 1.0000
17.500 1.1970 0.09392 0.08971 0.0135 0.0052 1.0000
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Polar data table (+)
Polar graphs
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