EPPLER 862 STRUT AIRFOIL (e862-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 862 STRUT AIRFOIL (e862-il) Reynolds number: 200,000 Max Cl/Cd: 32.66 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e862-il-200000-n5.txt Download as CSV file: xf-e862-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 862 STRUT AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8593 0.10487 0.09891 -0.0040 0.8259 0.2306
-16.250 -0.8332 0.10565 0.09950 -0.0032 0.7721 0.2312
-15.750 -0.8700 0.09492 0.08848 -0.0053 0.7392 0.2439
-15.500 -0.8394 0.09575 0.08922 -0.0052 0.7145 0.2445
-15.000 -0.8796 0.08474 0.07798 -0.0073 0.6943 0.2576
-14.000 -0.8381 0.07780 0.07076 -0.0090 0.6446 0.2705
-13.500 -0.9158 0.06346 0.05614 -0.0107 0.6362 0.2864
-13.250 -0.8805 0.06449 0.05715 -0.0108 0.6246 0.2873
-13.000 -0.8464 0.06538 0.05804 -0.0110 0.6132 0.2883
-12.500 -0.9149 0.05296 0.04534 -0.0119 0.6052 0.3023
-12.250 -0.8831 0.05352 0.04590 -0.0121 0.5961 0.3037
-12.000 -0.8608 0.05315 0.04552 -0.0123 0.5878 0.3059
-11.750 -0.9613 0.04156 0.03358 -0.0119 0.5892 0.3168
-11.500 -0.9318 0.04180 0.03384 -0.0121 0.5811 0.3185
-11.250 -0.9106 0.04135 0.03335 -0.0122 0.5748 0.3207
-11.000 -0.9076 0.03934 0.03130 -0.0121 0.5697 0.3241
-10.750 -0.9316 0.03532 0.02710 -0.0114 0.5660 0.3293
-10.500 -0.9404 0.03272 0.02434 -0.0107 0.5615 0.3329
-10.250 -0.9162 0.03248 0.02410 -0.0108 0.5557 0.3349
-10.000 -0.8998 0.03177 0.02332 -0.0106 0.5508 0.3373
-9.750 -0.8905 0.03059 0.02211 -0.0101 0.5462 0.3402
-9.500 -0.8871 0.02916 0.02057 -0.0091 0.5416 0.3434
-9.250 -0.8885 0.02764 0.01888 -0.0075 0.5374 0.3467
-9.000 -0.8761 0.02687 0.01804 -0.0065 0.5331 0.3492
-8.750 -0.8526 0.02665 0.01781 -0.0064 0.5289 0.3512
-8.500 -0.8338 0.02627 0.01739 -0.0058 0.5253 0.3533
-8.250 -0.8180 0.02579 0.01689 -0.0048 0.5216 0.3557
-8.000 -0.8070 0.02531 0.01636 -0.0030 0.5179 0.3583
-7.750 -0.7994 0.02486 0.01582 -0.0006 0.5144 0.3610
-7.500 -0.7881 0.02438 0.01519 0.0013 0.5108 0.3637
-7.250 -0.7677 0.02409 0.01482 0.0020 0.5072 0.3658
-6.750 -0.7180 0.02383 0.01457 0.0023 0.5005 0.3697
-6.500 -0.6948 0.02365 0.01439 0.0027 0.4973 0.3719
-6.250 -0.6720 0.02344 0.01414 0.0031 0.4941 0.3743
-6.000 -0.6495 0.02320 0.01384 0.0035 0.4910 0.3767
-5.750 -0.6278 0.02295 0.01348 0.0041 0.4880 0.3794
-5.500 -0.6066 0.02268 0.01307 0.0047 0.4850 0.3819
-5.250 -0.5788 0.02258 0.01295 0.0045 0.4820 0.3837
-5.000 -0.5513 0.02248 0.01288 0.0043 0.4792 0.3855
-4.750 -0.5244 0.02238 0.01280 0.0042 0.4765 0.3875
-4.500 -0.4978 0.02228 0.01271 0.0041 0.4737 0.3897
-4.250 -0.4715 0.02216 0.01257 0.0040 0.4709 0.3921
-4.000 -0.4455 0.02202 0.01238 0.0040 0.4681 0.3945
-3.750 -0.4195 0.02187 0.01214 0.0040 0.4654 0.3969
-3.500 -0.3938 0.02172 0.01188 0.0041 0.4628 0.3992
-3.250 -0.3663 0.02163 0.01173 0.0039 0.4603 0.4012
-3.000 -0.3377 0.02158 0.01173 0.0035 0.4580 0.4032
-2.750 -0.3094 0.02153 0.01173 0.0032 0.4557 0.4052
-2.500 -0.2814 0.02148 0.01170 0.0029 0.4531 0.4072
-2.250 -0.2535 0.02142 0.01164 0.0027 0.4505 0.4093
-2.000 -0.2256 0.02134 0.01154 0.0024 0.4478 0.4116
-1.750 -0.1979 0.02127 0.01143 0.0022 0.4453 0.4140
-1.500 -0.1702 0.02121 0.01129 0.0020 0.4430 0.4166
-1.250 -0.1426 0.02117 0.01114 0.0017 0.4409 0.4189
-1.000 -0.1136 0.02116 0.01112 0.0013 0.4389 0.4208
-0.750 -0.0850 0.02113 0.01118 0.0010 0.4368 0.4227
-0.500 -0.0566 0.02112 0.01123 0.0006 0.4344 0.4247
-0.250 -0.0283 0.02112 0.01126 0.0003 0.4318 0.4268
0.000 0.0000 0.02112 0.01127 0.0000 0.4292 0.4292
0.250 0.0283 0.02112 0.01126 -0.0003 0.4268 0.4318
0.500 0.0566 0.02112 0.01123 -0.0006 0.4247 0.4344
0.750 0.0850 0.02113 0.01118 -0.0010 0.4227 0.4368
1.000 0.1136 0.02116 0.01112 -0.0013 0.4208 0.4389
1.250 0.1426 0.02117 0.01114 -0.0017 0.4189 0.4409
1.500 0.1703 0.02121 0.01129 -0.0020 0.4166 0.4430
1.750 0.1979 0.02127 0.01143 -0.0022 0.4140 0.4453
2.000 0.2256 0.02134 0.01154 -0.0024 0.4116 0.4478
2.250 0.2535 0.02142 0.01164 -0.0027 0.4093 0.4505
2.500 0.2814 0.02148 0.01170 -0.0029 0.4072 0.4531
2.750 0.3095 0.02153 0.01173 -0.0032 0.4052 0.4556
3.000 0.3377 0.02158 0.01173 -0.0035 0.4032 0.4580
3.250 0.3664 0.02163 0.01173 -0.0039 0.4012 0.4603
3.500 0.3939 0.02172 0.01188 -0.0041 0.3992 0.4628
3.750 0.4196 0.02186 0.01214 -0.0040 0.3969 0.4654
4.000 0.4455 0.02202 0.01238 -0.0040 0.3946 0.4681
4.250 0.4716 0.02216 0.01257 -0.0041 0.3921 0.4709
4.500 0.4979 0.02228 0.01271 -0.0041 0.3897 0.4737
4.750 0.5245 0.02237 0.01280 -0.0042 0.3875 0.4765
5.000 0.5514 0.02248 0.01288 -0.0043 0.3855 0.4792
5.250 0.5790 0.02258 0.01295 -0.0045 0.3837 0.4820
5.500 0.6067 0.02268 0.01307 -0.0047 0.3819 0.4850
5.750 0.6280 0.02295 0.01348 -0.0041 0.3794 0.4880
6.000 0.6498 0.02320 0.01384 -0.0036 0.3767 0.4910
6.250 0.6722 0.02344 0.01414 -0.0031 0.3743 0.4941
6.500 0.6951 0.02365 0.01438 -0.0027 0.3719 0.4973
6.750 0.7184 0.02383 0.01457 -0.0024 0.3697 0.5005
7.250 0.7681 0.02409 0.01482 -0.0021 0.3658 0.5072
7.500 0.7886 0.02438 0.01518 -0.0014 0.3637 0.5108
7.750 0.8000 0.02486 0.01582 0.0004 0.3610 0.5144
8.000 0.8079 0.02531 0.01636 0.0029 0.3582 0.5179
8.250 0.8189 0.02578 0.01688 0.0047 0.3557 0.5216
8.500 0.8347 0.02626 0.01738 0.0056 0.3533 0.5253
8.750 0.8536 0.02664 0.01779 0.0062 0.3511 0.5290
9.000 0.8772 0.02686 0.01802 0.0063 0.3492 0.5331
9.250 0.8896 0.02762 0.01887 0.0073 0.3467 0.5374
9.500 0.8884 0.02913 0.02055 0.0090 0.3434 0.5417
9.750 0.8921 0.03056 0.02207 0.0099 0.3402 0.5463
10.000 0.9015 0.03173 0.02328 0.0104 0.3373 0.5509
10.250 0.9179 0.03244 0.02406 0.0106 0.3349 0.5558
10.500 0.9422 0.03268 0.02430 0.0104 0.3329 0.5616
10.750 0.9338 0.03525 0.02703 0.0112 0.3293 0.5661
11.000 0.9103 0.03924 0.03120 0.0119 0.3242 0.5699
11.250 0.9133 0.04125 0.03325 0.0119 0.3207 0.5749
11.500 0.9342 0.04173 0.03376 0.0118 0.3185 0.5812
11.750 0.9638 0.04148 0.03351 0.0116 0.3168 0.5894
12.250 0.8862 0.05341 0.04579 0.0118 0.3038 0.5964
12.500 0.9178 0.05286 0.04524 0.0116 0.3024 0.6055
13.000 0.8494 0.06529 0.05796 0.0106 0.2883 0.6136
13.250 0.8835 0.06441 0.05707 0.0105 0.2873 0.6249
13.500 0.9188 0.06338 0.05607 0.0104 0.2864 0.6365
14.000 0.7637 0.08691 0.07995 0.0075 0.2609 0.6348
14.250 0.7906 0.08674 0.07983 0.0072 0.2599 0.6474
14.500 0.8190 0.08636 0.07950 0.0070 0.2590 0.6605
14.750 0.8500 0.08565 0.07883 0.0069 0.2583 0.6765
15.000 0.8830 0.08466 0.07790 0.0069 0.2576 0.6950
15.500 0.8426 0.09569 0.08917 0.0048 0.2446 0.7152
15.750 0.8732 0.09487 0.08843 0.0048 0.2439 0.7401
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