GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 395 AIRFOIL (goe395-il) Reynolds number: 500,000 Max Cl/Cd: 117.34 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe395-il-500000-n5.txt Download as CSV file: xf-goe395-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 395 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2213 0.09041 0.08717 -0.0414 0.7495 0.0106
-7.750 -0.2132 0.08670 0.08347 -0.0439 0.7478 0.0110
-7.500 -0.2067 0.08187 0.07864 -0.0479 0.7461 0.0116
-7.250 -0.1915 0.07889 0.07566 -0.0513 0.7445 0.0122
-7.000 -0.1736 0.07697 0.07372 -0.0538 0.7431 0.0127
-6.750 -0.1553 0.07425 0.07098 -0.0573 0.7416 0.0133
-6.500 -0.1355 0.07039 0.06708 -0.0624 0.7401 0.0141
-6.250 -0.1095 0.06248 0.05913 -0.0739 0.7387 0.0159
-6.000 -0.0855 0.06096 0.05760 -0.0766 0.7375 0.0165
-5.750 -0.0606 0.05912 0.05575 -0.0797 0.7363 0.0172
-5.500 -0.0312 0.05560 0.05217 -0.0857 0.7351 0.0183
-5.250 0.0159 0.04682 0.04326 -0.1009 0.7338 0.0214
-5.000 0.0450 0.04524 0.04164 -0.1040 0.7327 0.0220
-4.500 0.1856 0.01608 0.01084 -0.1470 0.7308 0.0286
-4.250 0.2168 0.01414 0.00849 -0.1486 0.7298 0.0294
-4.000 0.2464 0.01321 0.00733 -0.1493 0.7288 0.0299
-3.750 0.2756 0.01253 0.00647 -0.1498 0.7277 0.0304
-3.500 0.3046 0.01200 0.00576 -0.1500 0.7260 0.0308
-3.250 0.3335 0.01155 0.00517 -0.1503 0.7238 0.0313
-3.000 0.3623 0.01118 0.00472 -0.1504 0.7213 0.0321
-2.750 0.3912 0.01085 0.00430 -0.1506 0.7190 0.0329
-2.500 0.4200 0.01051 0.00388 -0.1507 0.7167 0.0336
-2.250 0.4487 0.01024 0.00353 -0.1508 0.7144 0.0343
-2.000 0.4774 0.01001 0.00322 -0.1508 0.7121 0.0352
-1.750 0.5059 0.00984 0.00298 -0.1508 0.7101 0.0359
-1.500 0.5345 0.00969 0.00279 -0.1509 0.7078 0.0367
-1.250 0.5631 0.00952 0.00260 -0.1509 0.7049 0.0376
-1.000 0.5917 0.00936 0.00243 -0.1509 0.7020 0.0399
-0.750 0.6202 0.00924 0.00232 -0.1510 0.6992 0.0430
-0.500 0.6486 0.00915 0.00223 -0.1509 0.6965 0.0481
-0.250 0.6768 0.00911 0.00223 -0.1509 0.6938 0.0607
0.000 0.7051 0.00909 0.00225 -0.1509 0.6910 0.0701
0.250 0.7334 0.00905 0.00226 -0.1509 0.6874 0.0758
0.500 0.7617 0.00903 0.00225 -0.1508 0.6841 0.0803
0.750 0.7898 0.00903 0.00224 -0.1508 0.6810 0.0839
1.000 0.8179 0.00900 0.00222 -0.1507 0.6777 0.0874
1.250 0.8461 0.00893 0.00222 -0.1507 0.6724 0.0904
1.500 0.8741 0.00889 0.00221 -0.1506 0.6663 0.0941
1.750 0.9021 0.00888 0.00222 -0.1506 0.6603 0.0986
2.000 0.9301 0.00883 0.00222 -0.1506 0.6537 0.1030
2.250 0.9581 0.00880 0.00224 -0.1505 0.6468 0.1069
2.500 0.9858 0.00877 0.00223 -0.1504 0.6341 0.1115
2.750 1.0130 0.00875 0.00220 -0.1502 0.6067 0.1180
3.000 1.0378 0.00898 0.00221 -0.1495 0.5524 0.1268
3.250 1.0625 0.00934 0.00241 -0.1490 0.5185 0.1407
3.500 1.0880 0.00961 0.00265 -0.1487 0.4952 0.1696
3.750 1.1135 0.00986 0.00293 -0.1484 0.4733 0.2304
4.000 1.1392 0.00984 0.00340 -0.1483 0.4507 0.5506
4.250 1.1640 0.01016 0.00367 -0.1479 0.4244 0.5882
4.500 1.1883 0.01022 0.00392 -0.1475 0.3987 0.7152
5.000 1.2344 0.01052 0.00439 -0.1456 0.3598 1.0000
5.250 1.2589 0.01089 0.00468 -0.1451 0.3396 1.0000
5.500 1.2831 0.01129 0.00499 -0.1446 0.3193 1.0000
5.750 1.3058 0.01183 0.00539 -0.1439 0.2874 1.0000
6.000 1.3254 0.01269 0.00593 -0.1427 0.2316 1.0000
6.250 1.3407 0.01397 0.00675 -0.1411 0.1554 1.0000
6.500 1.3605 0.01474 0.00735 -0.1400 0.1265 1.0000
6.750 1.3819 0.01531 0.00786 -0.1391 0.1113 1.0000
7.000 1.4035 0.01584 0.00835 -0.1382 0.0985 1.0000
7.250 1.4243 0.01641 0.00886 -0.1372 0.0827 1.0000
7.500 1.4427 0.01718 0.00948 -0.1359 0.0617 1.0000
7.750 1.4616 0.01786 0.01011 -0.1347 0.0491 1.0000
8.000 1.4779 0.01873 0.01089 -0.1331 0.0311 1.0000
8.250 1.4917 0.01976 0.01181 -0.1311 0.0169 1.0000
8.500 1.5075 0.02055 0.01263 -0.1294 0.0138 1.0000
8.750 1.5228 0.02123 0.01338 -0.1275 0.0124 1.0000
9.000 1.5366 0.02197 0.01419 -0.1254 0.0114 1.0000
9.250 1.5488 0.02284 0.01512 -0.1233 0.0104 1.0000
9.500 1.5593 0.02389 0.01626 -0.1210 0.0096 1.0000
9.750 1.5696 0.02499 0.01745 -0.1189 0.0091 1.0000
10.000 1.5812 0.02601 0.01856 -0.1170 0.0087 1.0000
10.250 1.5920 0.02714 0.01977 -0.1151 0.0083 1.0000
10.500 1.6020 0.02836 0.02107 -0.1133 0.0078 1.0000
10.750 1.6117 0.02965 0.02244 -0.1116 0.0074 1.0000
11.000 1.6201 0.03108 0.02393 -0.1099 0.0070 1.0000
11.250 1.6257 0.03282 0.02575 -0.1080 0.0067 1.0000
11.500 1.6285 0.03486 0.02789 -0.1060 0.0064 1.0000
11.750 1.6352 0.03656 0.02972 -0.1045 0.0063 1.0000
12.000 1.6405 0.03843 0.03170 -0.1029 0.0061 1.0000
12.250 1.6445 0.04045 0.03383 -0.1013 0.0059 1.0000
12.500 1.6475 0.04261 0.03610 -0.0998 0.0057 1.0000
12.750 1.6494 0.04490 0.03850 -0.0983 0.0056 1.0000
13.000 1.6506 0.04729 0.04100 -0.0968 0.0054 1.0000
13.250 1.6509 0.04984 0.04366 -0.0955 0.0053 1.0000
13.500 1.6502 0.05251 0.04643 -0.0942 0.0052 1.0000
13.750 1.6492 0.05528 0.04931 -0.0930 0.0050 1.0000
14.000 1.6478 0.05821 0.05235 -0.0921 0.0049 1.0000
14.250 1.6456 0.06133 0.05558 -0.0913 0.0048 1.0000
14.500 1.6425 0.06466 0.05905 -0.0906 0.0047 1.0000
14.750 1.6377 0.06833 0.06283 -0.0902 0.0046 1.0000
15.000 1.6305 0.07249 0.06710 -0.0900 0.0045 1.0000
15.250 1.6206 0.07716 0.07191 -0.0900 0.0044 1.0000
15.500 1.6141 0.08151 0.07639 -0.0903 0.0044 1.0000
15.750 1.6086 0.08587 0.08090 -0.0908 0.0043 1.0000
16.000 1.6028 0.09041 0.08558 -0.0915 0.0042 1.0000
16.250 1.5963 0.09518 0.09050 -0.0925 0.0042 1.0000
16.500 1.5882 0.10024 0.09570 -0.0937 0.0041 1.0000
16.750 1.5797 0.10548 0.10109 -0.0951 0.0040 1.0000
17.000 1.5704 0.11095 0.10671 -0.0968 0.0040 1.0000
17.250 1.5606 0.11660 0.11250 -0.0987 0.0039 1.0000
17.500 1.5506 0.12239 0.11844 -0.1008 0.0039 1.0000
17.750 1.5404 0.12829 0.12448 -0.1032 0.0039 1.0000
18.000 1.5303 0.13431 0.13064 -0.1058 0.0038 1.0000
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