E178 (8.69%) (e178-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E178 (8.69%) (e178-il) Reynolds number: 200,000 Max Cl/Cd: 73.5 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e178-il-200000-n5.txt Download as CSV file: xf-e178-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3823 0.09182 0.08875 -0.0104 1.0000 0.0148
-9.000 -0.3905 0.08461 0.08159 -0.0136 1.0000 0.0136
-8.500 -0.4584 0.08539 0.08215 -0.0152 1.0000 0.0126
-8.250 -0.4591 0.08106 0.07788 -0.0176 1.0000 0.0125
-8.000 -0.4615 0.07661 0.07350 -0.0204 1.0000 0.0124
-7.750 -0.4643 0.07205 0.06900 -0.0240 1.0000 0.0123
-7.500 -0.4625 0.06616 0.06313 -0.0299 1.0000 0.0123
-7.250 -0.4580 0.05944 0.05637 -0.0359 1.0000 0.0123
-7.000 -0.4490 0.05187 0.04865 -0.0418 0.9787 0.0123
-6.750 -0.4307 0.04211 0.03844 -0.0488 0.9358 0.0124
-6.500 -0.4188 0.03480 0.03047 -0.0513 0.9070 0.0134
-6.250 -0.4011 0.03265 0.02805 -0.0515 0.8853 0.0144
-6.000 -0.3814 0.03097 0.02612 -0.0512 0.8666 0.0158
-5.750 -0.3632 0.02710 0.02164 -0.0505 0.8508 0.0162
-5.500 -0.3422 0.02416 0.01812 -0.0497 0.8369 0.0170
-5.250 -0.3192 0.02191 0.01535 -0.0488 0.8241 0.0179
-5.000 -0.2944 0.02071 0.01376 -0.0482 0.8124 0.0196
-4.750 -0.2694 0.01938 0.01206 -0.0475 0.8015 0.0207
-4.500 -0.2450 0.01750 0.00986 -0.0468 0.7915 0.0214
-4.250 -0.2196 0.01627 0.00841 -0.0463 0.7815 0.0225
-4.000 -0.1939 0.01542 0.00742 -0.0458 0.7723 0.0237
-3.750 -0.1681 0.01475 0.00660 -0.0454 0.7637 0.0250
-3.500 -0.1417 0.01421 0.00595 -0.0450 0.7549 0.0269
-3.250 -0.1152 0.01381 0.00541 -0.0447 0.7471 0.0295
-3.000 -0.0886 0.01335 0.00482 -0.0444 0.7392 0.0304
-2.750 -0.0620 0.01284 0.00418 -0.0440 0.7318 0.0329
-2.500 -0.0350 0.01249 0.00372 -0.0437 0.7246 0.0384
-2.250 -0.0081 0.01210 0.00336 -0.0435 0.7176 0.0610
-2.000 0.0183 0.01168 0.00310 -0.0434 0.7108 0.1178
-1.750 0.0448 0.01131 0.00293 -0.0433 0.7042 0.1856
-1.500 0.0705 0.01082 0.00280 -0.0431 0.6977 0.2949
-1.250 0.0942 0.01013 0.00272 -0.0426 0.6916 0.4706
-1.000 0.1133 0.00926 0.00273 -0.0406 0.6853 0.7063
-0.750 0.1527 0.00880 0.00270 -0.0418 0.6799 0.9175
-0.500 0.2046 0.00876 0.00254 -0.0468 0.6731 0.9930
-0.250 0.2351 0.00882 0.00244 -0.0474 0.6676 1.0000
0.000 0.2613 0.00887 0.00242 -0.0471 0.6612 1.0000
0.250 0.2873 0.00895 0.00238 -0.0467 0.6556 1.0000
0.500 0.3137 0.00903 0.00238 -0.0464 0.6497 1.0000
0.750 0.3401 0.00911 0.00239 -0.0461 0.6437 1.0000
1.000 0.3665 0.00920 0.00240 -0.0457 0.6385 1.0000
1.250 0.3932 0.00929 0.00245 -0.0455 0.6321 1.0000
1.500 0.4197 0.00939 0.00249 -0.0452 0.6269 1.0000
1.750 0.4465 0.00948 0.00257 -0.0450 0.6205 1.0000
2.000 0.4732 0.00959 0.00264 -0.0448 0.6146 1.0000
2.250 0.5000 0.00969 0.00275 -0.0446 0.6082 1.0000
2.500 0.5267 0.00979 0.00283 -0.0443 0.6009 1.0000
2.750 0.5535 0.00989 0.00294 -0.0441 0.5924 1.0000
3.000 0.5801 0.00999 0.00301 -0.0438 0.5847 1.0000
3.250 0.6069 0.01009 0.00318 -0.0435 0.5749 1.0000
3.500 0.6335 0.01019 0.00330 -0.0433 0.5648 1.0000
3.750 0.6601 0.01029 0.00342 -0.0430 0.5542 1.0000
4.000 0.6865 0.01041 0.00355 -0.0427 0.5424 1.0000
4.250 0.7129 0.01052 0.00369 -0.0424 0.5295 1.0000
4.500 0.7393 0.01065 0.00390 -0.0421 0.5154 1.0000
4.750 0.7655 0.01079 0.00408 -0.0417 0.4988 1.0000
5.000 0.7913 0.01096 0.00427 -0.0414 0.4786 1.0000
5.250 0.8169 0.01117 0.00448 -0.0409 0.4537 1.0000
5.500 0.8416 0.01145 0.00471 -0.0404 0.4214 1.0000
5.750 0.8655 0.01185 0.00501 -0.0399 0.3772 1.0000
6.000 0.8873 0.01250 0.00549 -0.0391 0.3169 1.0000
6.250 0.9075 0.01339 0.00610 -0.0384 0.2535 1.0000
6.500 0.9264 0.01446 0.00684 -0.0375 0.1879 1.0000
6.750 0.9442 0.01566 0.00767 -0.0367 0.1250 1.0000
7.000 0.9630 0.01670 0.00847 -0.0358 0.0820 1.0000
7.250 0.9816 0.01773 0.00931 -0.0349 0.0501 1.0000
7.500 0.9992 0.01885 0.01029 -0.0339 0.0252 1.0000
7.750 1.0166 0.01998 0.01141 -0.0327 0.0148 1.0000
8.000 1.0328 0.02119 0.01270 -0.0313 0.0117 1.0000
8.250 1.0498 0.02224 0.01397 -0.0300 0.0107 1.0000
8.500 1.0651 0.02342 0.01531 -0.0285 0.0098 1.0000
8.750 1.0787 0.02467 0.01672 -0.0270 0.0092 1.0000
9.000 1.0904 0.02604 0.01824 -0.0252 0.0088 1.0000
9.250 1.1008 0.02749 0.01981 -0.0233 0.0084 1.0000
9.500 1.1093 0.02885 0.02128 -0.0213 0.0079 1.0000
9.750 1.1155 0.03039 0.02293 -0.0192 0.0074 1.0000
10.000 1.1185 0.03250 0.02517 -0.0171 0.0069 1.0000
10.250 1.1237 0.03467 0.02749 -0.0154 0.0065 1.0000
10.500 1.1322 0.03636 0.02936 -0.0141 0.0062 1.0000
10.750 1.1383 0.03854 0.03175 -0.0128 0.0061 1.0000
11.000 1.1431 0.04089 0.03436 -0.0116 0.0060 1.0000
11.250 1.1452 0.04363 0.03735 -0.0105 0.0058 1.0000
11.500 1.1455 0.04650 0.04045 -0.0097 0.0058 1.0000
11.750 1.1431 0.04974 0.04395 -0.0092 0.0057 1.0000
12.000 1.1380 0.05335 0.04780 -0.0091 0.0057 1.0000
12.250 1.1302 0.05736 0.05207 -0.0094 0.0056 1.0000
12.500 1.1204 0.06176 0.05672 -0.0102 0.0056 1.0000
12.750 1.1090 0.06657 0.06175 -0.0116 0.0056 1.0000
13.000 1.0940 0.07220 0.06762 -0.0137 0.0056 1.0000
13.250 1.0795 0.07806 0.07369 -0.0164 0.0056 1.0000
13.500 1.0637 0.08452 0.08034 -0.0197 0.0057 1.0000
13.750 1.0463 0.09190 0.08790 -0.0239 0.0057 1.0000
14.000 1.0276 0.10031 0.09649 -0.0289 0.0057 1.0000
14.250 1.0099 0.10932 0.10566 -0.0346 0.0057 1.0000
14.500 0.9917 0.11938 0.11586 -0.0408 0.0058 1.0000
14.750 0.9723 0.13075 0.12733 -0.0477 0.0059 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E178 (8.69%) (e178-il)