EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 100,000 Max Cl/Cd: 45.97 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e360-il-100000-n5.txt Download as CSV file: xf-e360-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 360 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5221 0.09416 0.08893 -0.0270 1.0000 0.0214
-10.500 -0.5238 0.08952 0.08433 -0.0293 1.0000 0.0212
-10.250 -0.5330 0.08216 0.07700 -0.0342 1.0000 0.0209
-10.000 -0.5450 0.07566 0.07049 -0.0387 1.0000 0.0206
-9.750 -0.5610 0.07024 0.06501 -0.0416 1.0000 0.0203
-9.500 -0.5830 0.06520 0.05987 -0.0427 1.0000 0.0201
-9.250 -0.6033 0.06132 0.05588 -0.0415 1.0000 0.0200
-9.000 -0.6203 0.05819 0.05263 -0.0388 1.0000 0.0198
-8.750 -0.6334 0.05467 0.04892 -0.0361 1.0000 0.0197
-8.500 -0.6427 0.05119 0.04520 -0.0332 1.0000 0.0195
-8.250 -0.6485 0.04782 0.04155 -0.0301 1.0000 0.0193
-8.000 -0.6509 0.04461 0.03803 -0.0269 1.0000 0.0192
-7.750 -0.6500 0.04165 0.03474 -0.0237 1.0000 0.0192
-7.500 -0.6461 0.03887 0.03162 -0.0206 1.0000 0.0193
-7.250 -0.6394 0.03636 0.02877 -0.0176 1.0000 0.0195
-7.000 -0.6302 0.03415 0.02623 -0.0148 1.0000 0.0199
-6.750 -0.6199 0.03209 0.02375 -0.0119 1.0000 0.0210
-6.500 -0.6082 0.03037 0.02176 -0.0093 1.0000 0.0218
-6.250 -0.5882 0.02902 0.02032 -0.0086 0.9969 0.0227
-6.000 -0.5523 0.02721 0.01831 -0.0106 0.9875 0.0240
-5.750 -0.5166 0.02533 0.01616 -0.0122 0.9776 0.0253
-5.500 -0.4818 0.02373 0.01438 -0.0136 0.9665 0.0267
-5.250 -0.4481 0.02255 0.01322 -0.0152 0.9545 0.0296
-5.000 -0.4137 0.02140 0.01200 -0.0167 0.9428 0.0338
-4.750 -0.3806 0.02033 0.01088 -0.0179 0.9304 0.0386
-4.500 -0.3490 0.01939 0.00991 -0.0188 0.9167 0.0479
-4.250 -0.3190 0.01841 0.00898 -0.0194 0.9028 0.0629
-4.000 -0.2903 0.01748 0.00818 -0.0197 0.8889 0.0950
-3.750 -0.2657 0.01637 0.00752 -0.0195 0.8749 0.1765
-3.500 -0.2505 0.01481 0.00699 -0.0178 0.8605 0.3826
-3.250 -0.2335 0.01387 0.00719 -0.0147 0.8482 0.6320
-3.000 -0.2059 0.01406 0.00748 -0.0131 0.8361 0.7257
-2.750 -0.1803 0.01431 0.00764 -0.0115 0.8236 0.7710
-2.500 -0.1520 0.01469 0.00790 -0.0101 0.8126 0.8062
-2.250 -0.1205 0.01521 0.00827 -0.0091 0.8027 0.8369
-2.000 -0.0850 0.01564 0.00855 -0.0092 0.7920 0.8569
-1.750 -0.0513 0.01582 0.00855 -0.0096 0.7824 0.8691
-1.500 -0.0247 0.01587 0.00845 -0.0091 0.7723 0.8803
-1.250 0.0138 0.01596 0.00839 -0.0108 0.7626 0.8855
-1.000 0.0448 0.01597 0.00825 -0.0113 0.7540 0.8927
-0.750 0.0745 0.01598 0.00816 -0.0116 0.7441 0.8991
-0.500 0.1092 0.01600 0.00804 -0.0129 0.7358 0.9036
-0.250 0.1340 0.01599 0.00795 -0.0124 0.7265 0.9110
0.000 0.1676 0.01599 0.00786 -0.0136 0.7184 0.9150
0.250 0.2018 0.01600 0.00780 -0.0149 0.7097 0.9189
0.500 0.2303 0.01601 0.00774 -0.0152 0.7017 0.9245
0.750 0.2594 0.01602 0.00770 -0.0155 0.6933 0.9296
1.000 0.2940 0.01604 0.00768 -0.0170 0.6852 0.9331
1.250 0.3250 0.01606 0.00766 -0.0178 0.6767 0.9377
1.500 0.3503 0.01610 0.00768 -0.0174 0.6680 0.9438
1.750 0.3851 0.01609 0.00761 -0.0188 0.6584 0.9469
2.000 0.4165 0.01608 0.00761 -0.0197 0.6458 0.9512
2.250 0.4433 0.01607 0.00757 -0.0195 0.6322 0.9568
2.500 0.4740 0.01603 0.00750 -0.0202 0.6169 0.9609
2.750 0.5056 0.01598 0.00743 -0.0210 0.6008 0.9651
3.000 0.5339 0.01598 0.00741 -0.0212 0.5855 0.9703
3.250 0.5643 0.01596 0.00742 -0.0218 0.5697 0.9746
3.500 0.5957 0.01595 0.00741 -0.0227 0.5529 0.9790
3.750 0.6244 0.01598 0.00745 -0.0231 0.5356 0.9841
4.000 0.6564 0.01597 0.00746 -0.0241 0.5161 0.9881
4.250 0.6868 0.01601 0.00754 -0.0249 0.4930 0.9929
4.500 0.7174 0.01607 0.00758 -0.0258 0.4645 0.9975
4.750 0.7412 0.01621 0.00768 -0.0253 0.4320 1.0000
5.000 0.7562 0.01645 0.00780 -0.0231 0.3955 1.0000
5.250 0.7694 0.01681 0.00798 -0.0207 0.3536 1.0000
5.500 0.7808 0.01731 0.00827 -0.0181 0.3130 1.0000
5.750 0.7912 0.01790 0.00867 -0.0153 0.2780 1.0000
6.000 0.8013 0.01850 0.00913 -0.0125 0.2503 1.0000
6.250 0.8113 0.01910 0.00961 -0.0097 0.2286 1.0000
6.500 0.8216 0.01968 0.01012 -0.0069 0.2120 1.0000
6.750 0.8325 0.02026 0.01065 -0.0043 0.1979 1.0000
7.000 0.8441 0.02083 0.01120 -0.0017 0.1858 1.0000
7.250 0.8560 0.02143 0.01177 0.0007 0.1758 1.0000
7.500 0.8676 0.02208 0.01236 0.0032 0.1674 1.0000
7.750 0.8815 0.02267 0.01300 0.0053 0.1593 1.0000
8.000 0.8939 0.02339 0.01366 0.0075 0.1525 1.0000
8.250 0.9091 0.02402 0.01435 0.0093 0.1455 1.0000
8.500 0.9230 0.02474 0.01506 0.0112 0.1396 1.0000
8.750 0.9380 0.02549 0.01586 0.0129 0.1342 1.0000
9.000 0.9532 0.02621 0.01665 0.0145 0.1285 1.0000
9.250 0.9670 0.02706 0.01745 0.0162 0.1239 1.0000
9.500 0.9831 0.02786 0.01838 0.0176 0.1190 1.0000
9.750 0.9975 0.02868 0.01927 0.0192 0.1144 1.0000
10.000 1.0103 0.02958 0.02016 0.0209 0.1106 1.0000
10.250 1.0245 0.03051 0.02124 0.0225 0.1065 1.0000
10.500 1.0376 0.03146 0.02231 0.0240 0.1026 1.0000
10.750 1.0498 0.03244 0.02333 0.0256 0.0991 1.0000
11.000 1.0622 0.03354 0.02447 0.0270 0.0959 1.0000
11.250 1.0737 0.03472 0.02588 0.0285 0.0924 1.0000
11.500 1.0844 0.03591 0.02721 0.0299 0.0891 1.0000
11.750 1.0943 0.03709 0.02844 0.0312 0.0864 1.0000
12.000 1.1054 0.03844 0.02980 0.0322 0.0838 1.0000
12.250 1.1109 0.04004 0.03170 0.0336 0.0809 1.0000
12.750 1.1229 0.04327 0.03525 0.0357 0.0758 1.0000
13.000 1.1294 0.04482 0.03684 0.0365 0.0738 1.0000
13.250 1.1338 0.04680 0.03894 0.0372 0.0718 1.0000
13.500 1.1311 0.04938 0.04183 0.0378 0.0697 1.0000
13.750 1.1284 0.05204 0.04472 0.0381 0.0678 1.0000
14.000 1.1261 0.05470 0.04756 0.0382 0.0661 1.0000
14.250 1.1248 0.05727 0.05024 0.0381 0.0644 1.0000
14.500 1.1271 0.05949 0.05249 0.0379 0.0629 1.0000
14.750 1.1228 0.06271 0.05583 0.0374 0.0615 1.0000
15.000 1.1050 0.06771 0.06115 0.0358 0.0605 1.0000
15.250 1.0847 0.07336 0.06707 0.0336 0.0597 1.0000
15.500 1.0600 0.08004 0.07400 0.0304 0.0591 1.0000
15.750 1.0264 0.08883 0.08304 0.0257 0.0589 1.0000
16.000 0.9680 0.10351 0.09798 0.0168 0.0595 1.0000
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