GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 100,000 Max Cl/Cd: 69.29 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe495-il-100000-n5.txt Download as CSV file: xf-goe495-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 495 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3261 0.09977 0.09500 -0.0324 1.0000 0.0449
-7.750 -0.3330 0.09808 0.09340 -0.0311 1.0000 0.0457
-7.500 -0.3406 0.09643 0.09184 -0.0290 1.0000 0.0455
-7.250 -0.2592 0.07709 0.07285 -0.0370 0.9883 0.0343
-7.000 -0.2509 0.07283 0.06860 -0.0395 0.9830 0.0334
-6.750 -0.3500 0.08800 0.08359 -0.0302 0.9944 0.0338
-6.500 -0.3300 0.08327 0.07885 -0.0357 0.9884 0.0318
-6.250 -0.3086 0.07828 0.07383 -0.0426 0.9817 0.0306
-6.000 -0.2827 0.07320 0.06872 -0.0509 0.9756 0.0320
-5.750 -0.2552 0.06770 0.06318 -0.0597 0.9687 0.0328
-5.500 -0.2252 0.06190 0.05728 -0.0685 0.9624 0.0323
-5.250 -0.1879 0.05492 0.05017 -0.0797 0.9565 0.0319
-5.000 -0.1354 0.04516 0.04009 -0.0954 0.9531 0.0323
-4.750 -0.0841 0.03433 0.02839 -0.1094 0.9480 0.0349
-4.500 -0.0390 0.02819 0.02117 -0.1167 0.9448 0.0368
-4.250 -0.0028 0.02606 0.01876 -0.1198 0.9416 0.0410
-4.000 0.0369 0.02381 0.01593 -0.1228 0.9391 0.0457
-3.750 0.0667 0.02216 0.01374 -0.1235 0.9328 0.0496
-3.500 0.1011 0.02104 0.01249 -0.1253 0.9288 0.0547
-3.250 0.1387 0.01987 0.01104 -0.1272 0.9260 0.0585
-3.000 0.1678 0.01916 0.01015 -0.1275 0.9198 0.0637
-2.750 0.2014 0.01848 0.00939 -0.1287 0.9152 0.0689
-2.500 0.2382 0.01781 0.00857 -0.1304 0.9120 0.0743
-2.250 0.2677 0.01731 0.00807 -0.1307 0.9058 0.0830
-2.000 0.3005 0.01681 0.00758 -0.1317 0.9008 0.1057
-1.750 0.3363 0.01637 0.00723 -0.1332 0.8972 0.1515
-1.500 0.3637 0.01617 0.00713 -0.1333 0.8900 0.1981
-1.250 0.3964 0.01587 0.00701 -0.1343 0.8851 0.2656
-1.000 0.4285 0.01562 0.00692 -0.1351 0.8799 0.3288
-0.750 0.4580 0.01544 0.00683 -0.1353 0.8732 0.3855
-0.500 0.4923 0.01513 0.00666 -0.1364 0.8689 0.4546
-0.250 0.5184 0.01494 0.00668 -0.1359 0.8609 0.5321
0.000 0.5482 0.01440 0.00654 -0.1358 0.8558 0.6731
0.250 0.5752 0.01396 0.00640 -0.1352 0.8478 1.0000
0.500 0.6079 0.01396 0.00627 -0.1359 0.8419 1.0000
0.750 0.6353 0.01408 0.00630 -0.1356 0.8334 1.0000
1.000 0.6676 0.01408 0.00622 -0.1362 0.8272 1.0000
1.250 0.6941 0.01421 0.00631 -0.1358 0.8178 1.0000
1.500 0.7255 0.01423 0.00628 -0.1362 0.8108 1.0000
1.750 0.7522 0.01435 0.00638 -0.1357 0.8008 1.0000
2.000 0.7796 0.01444 0.00646 -0.1354 0.7906 1.0000
2.250 0.8091 0.01446 0.00648 -0.1353 0.7810 1.0000
2.500 0.8361 0.01455 0.00658 -0.1349 0.7697 1.0000
2.750 0.8621 0.01466 0.00672 -0.1342 0.7574 1.0000
3.000 0.8885 0.01475 0.00687 -0.1336 0.7445 1.0000
3.250 0.9149 0.01482 0.00697 -0.1329 0.7302 1.0000
3.500 0.9410 0.01489 0.00709 -0.1322 0.7150 1.0000
3.750 0.9671 0.01498 0.00723 -0.1315 0.6993 1.0000
4.000 0.9932 0.01508 0.00740 -0.1307 0.6830 1.0000
4.250 1.0187 0.01520 0.00757 -0.1299 0.6647 1.0000
4.500 1.0434 0.01536 0.00778 -0.1289 0.6436 1.0000
4.750 1.0684 0.01553 0.00801 -0.1279 0.6217 1.0000
5.000 1.0913 0.01575 0.00822 -0.1265 0.5900 1.0000
5.250 1.1121 0.01608 0.00842 -0.1246 0.5446 1.0000
5.500 1.1312 0.01658 0.00872 -0.1226 0.4921 1.0000
5.750 1.1489 0.01722 0.00917 -0.1205 0.4300 1.0000
6.000 1.1627 0.01821 0.00978 -0.1180 0.3503 1.0000
6.250 1.1739 0.01954 0.01064 -0.1154 0.2641 1.0000
6.500 1.1854 0.02099 0.01166 -0.1130 0.1919 1.0000
6.750 1.1983 0.02238 0.01281 -0.1109 0.1468 1.0000
7.000 1.2116 0.02375 0.01398 -0.1087 0.1008 1.0000
7.250 1.2235 0.02522 0.01524 -0.1065 0.0739 1.0000
7.500 1.2362 0.02656 0.01662 -0.1043 0.0596 1.0000
7.750 1.2479 0.02797 0.01805 -0.1019 0.0505 1.0000
8.000 1.2578 0.02949 0.01960 -0.0994 0.0434 1.0000
8.250 1.2674 0.03098 0.02125 -0.0967 0.0383 1.0000
8.500 1.2760 0.03254 0.02287 -0.0941 0.0338 1.0000
8.750 1.2841 0.03448 0.02490 -0.0914 0.0311 1.0000
9.000 1.2968 0.03621 0.02684 -0.0893 0.0281 1.0000
9.250 1.3083 0.03790 0.02864 -0.0874 0.0254 1.0000
9.500 1.3188 0.04012 0.03091 -0.0855 0.0234 1.0000
9.750 1.3363 0.04273 0.03373 -0.0842 0.0222 1.0000
10.000 1.3530 0.04527 0.03668 -0.0828 0.0209 1.0000
10.250 1.3646 0.04781 0.03956 -0.0810 0.0195 1.0000
10.500 1.3714 0.05034 0.04240 -0.0788 0.0182 1.0000
10.750 1.3750 0.05312 0.04549 -0.0766 0.0174 1.0000
11.000 1.3753 0.05628 0.04897 -0.0743 0.0169 1.0000
11.250 1.3717 0.05963 0.05263 -0.0720 0.0166 1.0000
11.500 1.3647 0.06323 0.05654 -0.0699 0.0163 1.0000
11.750 1.3549 0.06713 0.06074 -0.0682 0.0162 1.0000
12.000 1.3425 0.07141 0.06532 -0.0670 0.0160 1.0000
12.250 1.3277 0.07613 0.07032 -0.0665 0.0160 1.0000
12.500 1.3107 0.08138 0.07585 -0.0667 0.0159 1.0000
12.750 1.2918 0.08723 0.08198 -0.0678 0.0160 1.0000
13.000 1.2709 0.09386 0.08887 -0.0700 0.0160 1.0000
13.250 1.2481 0.10143 0.09670 -0.0735 0.0162 1.0000
13.500 1.2233 0.11029 0.10580 -0.0785 0.0164 1.0000
13.750 1.1963 0.12098 0.11670 -0.0854 0.0167 1.0000
14.000 1.1632 0.13581 0.13171 -0.0958 0.0174 1.0000
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