EPPLER 636 AIRFOIL (e636-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 636 AIRFOIL (e636-il) Reynolds number: 50,000 Max Cl/Cd: 24.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e636-il-50000-n5.txt Download as CSV file: xf-e636-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4275 0.11111 0.10485 -0.0009 1.0000 0.1201
-9.250 -0.4467 0.10884 0.10272 -0.0061 1.0000 0.1249
-9.000 -0.4548 0.10503 0.09904 -0.0096 1.0000 0.1261
-8.750 -0.4305 0.10025 0.09425 -0.0069 1.0000 0.1288
-8.500 -0.4245 0.09663 0.09069 -0.0076 1.0000 0.1313
-8.250 -0.4248 0.09302 0.08716 -0.0094 1.0000 0.1342
-7.500 -0.4503 0.07633 0.07038 -0.0199 1.0000 0.0649
-7.250 -0.4464 0.07256 0.06663 -0.0197 1.0000 0.0620
-6.750 -0.4534 0.06432 0.05788 -0.0191 1.0000 0.0533
-6.500 -0.4464 0.06104 0.05459 -0.0182 1.0000 0.0529
-6.250 -0.4415 0.05805 0.05149 -0.0168 1.0000 0.0527
-6.000 -0.4275 0.05467 0.04788 -0.0172 0.9662 0.0528
-5.750 -0.3987 0.05066 0.04342 -0.0197 0.9169 0.0529
-5.500 -0.3706 0.04706 0.03938 -0.0212 0.8823 0.0526
-5.000 -0.3275 0.04155 0.03297 -0.0198 0.8255 0.0515
-4.750 -0.3081 0.03933 0.03029 -0.0182 0.8025 0.0512
-4.500 -0.2879 0.03726 0.02773 -0.0164 0.7815 0.0511
-4.250 -0.2662 0.03539 0.02540 -0.0148 0.7630 0.0511
-4.000 -0.2427 0.03363 0.02319 -0.0133 0.7457 0.0514
-3.750 -0.2174 0.03214 0.02123 -0.0121 0.7289 0.0527
-3.500 -0.1910 0.03067 0.01944 -0.0113 0.7132 0.0550
-3.250 -0.1633 0.02939 0.01798 -0.0110 0.6981 0.0577
-3.000 -0.1317 0.02818 0.01653 -0.0109 0.6839 0.0599
-2.750 -0.0967 0.02708 0.01516 -0.0114 0.6705 0.0626
-2.500 -0.0633 0.02619 0.01397 -0.0117 0.6569 0.0660
-2.250 -0.0353 0.02537 0.01307 -0.0114 0.6443 0.0722
-1.750 0.1723 0.02131 0.01152 -0.0354 0.6124 1.0000
-1.500 0.1950 0.02135 0.01124 -0.0347 0.6017 1.0000
-1.250 0.2174 0.02141 0.01096 -0.0338 0.5925 1.0000
-1.000 0.2401 0.02150 0.01080 -0.0331 0.5825 1.0000
-0.750 0.2629 0.02162 0.01070 -0.0324 0.5733 1.0000
-0.500 0.2853 0.02173 0.01056 -0.0315 0.5653 1.0000
-0.250 0.3081 0.02191 0.01058 -0.0309 0.5562 1.0000
0.000 0.3304 0.02205 0.01050 -0.0299 0.5491 1.0000
0.250 0.3534 0.02230 0.01064 -0.0294 0.5403 1.0000
0.500 0.3762 0.02249 0.01062 -0.0285 0.5340 1.0000
0.750 0.3993 0.02280 0.01087 -0.0280 0.5256 1.0000
1.000 0.4219 0.02302 0.01093 -0.0271 0.5195 1.0000
1.250 0.4444 0.02339 0.01125 -0.0266 0.5118 1.0000
1.500 0.4669 0.02368 0.01142 -0.0257 0.5057 1.0000
1.750 0.4891 0.02407 0.01176 -0.0250 0.4991 1.0000
2.000 0.5113 0.02445 0.01209 -0.0243 0.4926 1.0000
2.250 0.5337 0.02476 0.01229 -0.0233 0.4876 1.0000
2.500 0.5552 0.02533 0.01291 -0.0228 0.4805 1.0000
3.000 0.5985 0.02624 0.01377 -0.0211 0.4693 1.0000
3.250 0.6197 0.02679 0.01433 -0.0203 0.4633 1.0000
3.500 0.6419 0.02715 0.01462 -0.0193 0.4590 1.0000
3.750 0.6614 0.02796 0.01556 -0.0187 0.4524 1.0000
4.000 0.6823 0.02851 0.01612 -0.0177 0.4471 1.0000
4.250 0.7046 0.02886 0.01641 -0.0167 0.4433 1.0000
4.500 0.7216 0.02997 0.01770 -0.0160 0.4365 1.0000
4.750 0.7420 0.03056 0.01834 -0.0150 0.4316 1.0000
5.000 0.7636 0.03101 0.01876 -0.0139 0.4278 1.0000
5.250 0.7779 0.03234 0.02030 -0.0130 0.4209 1.0000
5.500 0.7977 0.03298 0.02099 -0.0119 0.4164 1.0000
5.750 0.8181 0.03357 0.02164 -0.0109 0.4124 1.0000
6.000 0.8288 0.03518 0.02346 -0.0097 0.4056 1.0000
6.250 0.8481 0.03584 0.02417 -0.0086 0.4012 1.0000
6.500 0.8653 0.03674 0.02515 -0.0074 0.3968 1.0000
6.750 0.8718 0.03862 0.02724 -0.0060 0.3900 1.0000
7.000 0.8913 0.03923 0.02794 -0.0048 0.3859 1.0000
7.250 0.8989 0.04096 0.02982 -0.0033 0.3803 1.0000
7.500 0.9032 0.04290 0.03191 -0.0017 0.3740 1.0000
7.750 0.9255 0.04319 0.03227 -0.0005 0.3703 1.0000
8.000 0.9077 0.04697 0.03623 0.0017 0.3622 1.0000
8.250 0.9205 0.04803 0.03738 0.0031 0.3573 1.0000
8.500 0.9516 0.04753 0.03698 0.0042 0.3543 1.0000
8.750 0.8941 0.05452 0.04406 0.0068 0.3433 1.0000
9.000 0.9260 0.05382 0.04347 0.0081 0.3404 1.0000
9.500 0.8171 0.06962 0.05911 0.0078 0.3177 1.0000
9.750 0.8310 0.07062 0.06024 0.0089 0.3128 1.0000
10.000 0.8644 0.06916 0.05893 0.0110 0.3103 1.0000
10.500 0.8076 0.08170 0.07143 0.0082 0.2897 1.0000
10.750 0.8214 0.08273 0.07257 0.0091 0.2841 1.0000
11.250 0.8205 0.08861 0.07858 0.0089 0.2699 1.0000
11.750 0.8217 0.09435 0.08447 0.0085 0.2558 1.0000
12.000 0.8108 0.09893 0.08909 0.0074 0.2473 1.0000
12.250 0.8255 0.09981 0.09013 0.0082 0.2415 1.0000
12.500 0.8126 0.10490 0.09525 0.0067 0.2331 1.0000
12.750 0.8280 0.10565 0.09613 0.0075 0.2274 1.0000
13.000 0.8150 0.11087 0.10138 0.0058 0.2186 1.0000
13.250 0.8320 0.11131 0.10197 0.0067 0.2133 1.0000
13.500 0.8168 0.11713 0.10781 0.0046 0.2047 1.0000
13.750 0.8365 0.11699 0.10782 0.0058 0.1994 1.0000
14.000 0.8189 0.12352 0.11436 0.0032 0.1908 1.0000
14.250 0.8381 0.12345 0.11448 0.0043 0.1858 1.0000
14.500 0.8213 0.12999 0.12099 0.0015 0.1771 1.0000
14.750 0.8414 0.12966 0.12085 0.0027 0.1722 1.0000
15.000 0.8224 0.13713 0.12831 -0.0006 0.1644 1.0000
15.250 0.8420 0.13668 0.12802 0.0006 0.1591 1.0000
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Polar data table (+)
Polar graphs
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