GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 460 AIRFOIL (goe460-il) Reynolds number: 100,000 Max Cl/Cd: 39.84 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe460-il-100000.txt Download as CSV file: xf-goe460-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 460 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.4740 0.17853 0.17208 -0.0215 1.0000 0.1817
-17.250 -0.9007 0.08888 0.08219 -0.0653 1.0000 0.1382
-17.000 -0.9645 0.07792 0.07099 -0.0689 1.0000 0.1391
-16.500 -0.9631 0.07321 0.06626 -0.0688 1.0000 0.1467
-16.250 -1.0241 0.06468 0.05740 -0.0699 1.0000 0.1479
-16.000 -1.0688 0.05888 0.05127 -0.0692 1.0000 0.1496
-15.750 -1.0271 0.06023 0.05292 -0.0686 1.0000 0.1559
-15.500 -1.0478 0.05676 0.04930 -0.0675 1.0000 0.1595
-15.250 -1.0830 0.05262 0.04487 -0.0653 1.0000 0.1624
-15.000 -1.0650 0.05212 0.04452 -0.0644 1.0000 0.1682
-14.750 -1.0731 0.05027 0.04259 -0.0624 1.0000 0.1729
-14.500 -1.1029 0.04735 0.03942 -0.0589 1.0000 0.1764
-14.250 -1.0897 0.04664 0.03882 -0.0576 1.0000 0.1824
-14.000 -1.0945 0.04536 0.03750 -0.0549 1.0000 0.1875
-13.750 -1.1206 0.04335 0.03526 -0.0500 1.0000 0.1913
-13.500 -1.1108 0.04249 0.03447 -0.0482 1.0000 0.1971
-13.250 -1.1098 0.04166 0.03365 -0.0452 1.0000 0.2025
-13.000 -1.1308 0.04032 0.03211 -0.0396 1.0000 0.2065
-12.750 -1.1348 0.03926 0.03101 -0.0357 1.0000 0.2115
-12.500 -1.1209 0.03875 0.03061 -0.0339 1.0000 0.2178
-12.250 -1.1379 0.03785 0.02958 -0.0278 1.0000 0.2220
-12.000 -1.1667 0.03711 0.02864 -0.0194 1.0000 0.2251
-11.750 -1.1352 0.03642 0.02819 -0.0203 1.0000 0.2331
-11.500 -1.1483 0.03584 0.02754 -0.0141 1.0000 0.2377
-11.250 -1.1730 0.03525 0.02678 -0.0059 1.0000 0.2414
-11.000 -1.1542 0.03455 0.02624 -0.0048 1.0000 0.2487
-10.750 -1.1586 0.03400 0.02565 0.0002 1.0000 0.2548
-10.500 -1.1781 0.03333 0.02476 0.0076 1.0000 0.2597
-10.250 -1.1562 0.03279 0.02447 0.0083 1.0000 0.2681
-10.000 -1.1646 0.03224 0.02380 0.0139 1.0000 0.2749
-9.750 -1.1575 0.03172 0.02337 0.0170 1.0000 0.2830
-9.500 -1.1576 0.03130 0.02293 0.0214 1.0000 0.2911
-9.250 -1.1546 0.03077 0.02239 0.0252 1.0000 0.2991
-9.000 -1.1479 0.03043 0.02209 0.0285 1.0000 0.3076
-8.750 -1.1466 0.02989 0.02146 0.0325 1.0000 0.3156
-8.500 -1.1343 0.02957 0.02124 0.0349 1.0000 0.3238
-8.250 -1.1358 0.02904 0.02049 0.0394 1.0000 0.3313
-8.000 -1.1170 0.02868 0.02032 0.0406 1.0000 0.3386
-7.750 -1.1107 0.02826 0.01980 0.0439 1.0000 0.3464
-7.500 -1.0993 0.02785 0.01941 0.0462 1.0000 0.3537
-7.250 -1.0883 0.02755 0.01913 0.0487 1.0000 0.3616
-7.000 -1.0811 0.02714 0.01863 0.0517 1.0000 0.3697
-6.750 -1.0390 0.02723 0.01879 0.0482 0.9926 0.3814
-6.500 -1.0010 0.02711 0.01869 0.0455 0.9838 0.3926
-6.250 -0.9663 0.02704 0.01851 0.0434 0.9748 0.4058
-6.000 -0.9254 0.02699 0.01860 0.0404 0.9663 0.4185
-5.750 -0.8939 0.02685 0.01853 0.0392 0.9566 0.4324
-5.500 -0.8535 0.02689 0.01863 0.0364 0.9487 0.4499
-5.250 -0.8308 0.02671 0.01848 0.0370 0.9372 0.4661
-5.000 -0.7935 0.02672 0.01856 0.0350 0.9291 0.4850
-4.750 -0.7687 0.02661 0.01848 0.0354 0.9181 0.5027
-4.500 -0.7386 0.02661 0.01852 0.0349 0.9088 0.5214
-4.250 -0.7070 0.02658 0.01856 0.0343 0.8992 0.5397
-4.000 -0.6736 0.02661 0.01869 0.0333 0.8905 0.5564
-3.750 -0.6405 0.02657 0.01872 0.0325 0.8812 0.5723
-3.500 -0.5901 0.02647 0.01866 0.0286 0.8764 0.5896
-3.250 -0.5811 0.02637 0.01855 0.0319 0.8628 0.6028
-3.000 -0.5343 0.02617 0.01834 0.0287 0.8579 0.6196
-2.750 -0.5138 0.02636 0.01865 0.0302 0.8454 0.6306
-2.500 -0.4657 0.02618 0.01850 0.0269 0.8400 0.6457
-2.250 -0.4570 0.02619 0.01848 0.0304 0.8275 0.6595
-2.000 -0.4014 0.02624 0.01864 0.0260 0.8222 0.6722
-1.750 -0.3414 0.02606 0.01850 0.0209 0.8191 0.6857
-1.500 -0.3456 0.02613 0.01854 0.0265 0.8043 0.6988
-1.250 -0.2715 0.02612 0.01863 0.0192 0.8015 0.7090
-1.000 -0.2079 0.02587 0.01837 0.0134 0.7988 0.7218
-0.750 -0.2008 0.02624 0.01879 0.0174 0.7847 0.7331
-0.500 -0.1221 0.02631 0.01890 0.0095 0.7815 0.7445
-0.250 -0.0559 0.02608 0.01866 0.0039 0.7782 0.7589
0.000 0.0003 0.02678 0.01943 0.0000 0.7653 0.7653
0.250 0.1030 0.02640 0.01899 -0.0116 0.7592 0.7713
0.500 0.1223 0.02629 0.01888 -0.0095 0.7444 0.7815
0.750 0.2006 0.02624 0.01878 -0.0173 0.7330 0.7847
1.000 0.2080 0.02586 0.01837 -0.0134 0.7218 0.7988
1.250 0.2715 0.02611 0.01862 -0.0192 0.7090 0.8015
1.500 0.3458 0.02613 0.01854 -0.0266 0.6988 0.8043
1.750 0.3414 0.02605 0.01849 -0.0209 0.6856 0.8191
2.000 0.4016 0.02624 0.01864 -0.0260 0.6722 0.8222
2.500 0.4661 0.02619 0.01852 -0.0270 0.6458 0.8400
2.750 0.5139 0.02636 0.01865 -0.0302 0.6307 0.8454
3.000 0.5344 0.02617 0.01834 -0.0288 0.6196 0.8579
3.250 0.5810 0.02637 0.01855 -0.0319 0.6029 0.8628
3.500 0.5898 0.02646 0.01866 -0.0285 0.5896 0.8764
3.750 0.6403 0.02656 0.01871 -0.0324 0.5723 0.8812
4.000 0.6736 0.02661 0.01868 -0.0333 0.5566 0.8906
4.250 0.7071 0.02658 0.01855 -0.0343 0.5397 0.8993
4.500 0.7384 0.02660 0.01851 -0.0349 0.5214 0.9089
4.750 0.7685 0.02661 0.01848 -0.0354 0.5028 0.9181
5.000 0.7932 0.02673 0.01857 -0.0350 0.4851 0.9291
5.250 0.8307 0.02670 0.01847 -0.0370 0.4661 0.9373
5.500 0.8536 0.02688 0.01861 -0.0365 0.4499 0.9487
5.750 0.8940 0.02685 0.01853 -0.0392 0.4323 0.9567
6.000 0.9257 0.02698 0.01859 -0.0405 0.4185 0.9664
6.250 0.9662 0.02703 0.01851 -0.0434 0.4058 0.9749
6.500 1.0012 0.02710 0.01868 -0.0456 0.3926 0.9839
6.750 1.0389 0.02722 0.01879 -0.0482 0.3813 0.9926
7.000 1.0809 0.02713 0.01862 -0.0516 0.3697 1.0000
7.250 1.0881 0.02753 0.01911 -0.0486 0.3616 1.0000
7.500 1.0992 0.02784 0.01939 -0.0462 0.3537 1.0000
7.750 1.1105 0.02825 0.01979 -0.0439 0.3464 1.0000
8.000 1.1169 0.02867 0.02031 -0.0406 0.3387 1.0000
8.250 1.1357 0.02903 0.02048 -0.0394 0.3313 1.0000
8.500 1.1342 0.02957 0.02123 -0.0349 0.3238 1.0000
8.750 1.1466 0.02987 0.02144 -0.0326 0.3155 1.0000
9.000 1.1479 0.03042 0.02208 -0.0285 0.3076 1.0000
9.250 1.1546 0.03076 0.02238 -0.0252 0.2990 1.0000
9.500 1.1573 0.03129 0.02292 -0.0213 0.2910 1.0000
9.750 1.1574 0.03171 0.02335 -0.0170 0.2829 1.0000
10.000 1.1647 0.03223 0.02379 -0.0139 0.2750 1.0000
10.250 1.1561 0.03278 0.02445 -0.0082 0.2681 1.0000
10.500 1.1781 0.03333 0.02476 -0.0076 0.2597 1.0000
10.750 1.1586 0.03399 0.02564 -0.0002 0.2547 1.0000
11.000 1.1543 0.03454 0.02622 0.0048 0.2487 1.0000
11.250 1.1731 0.03524 0.02676 0.0059 0.2414 1.0000
11.500 1.1483 0.03583 0.02752 0.0141 0.2377 1.0000
11.750 1.1352 0.03640 0.02816 0.0203 0.2330 1.0000
12.000 1.1665 0.03710 0.02863 0.0195 0.2250 1.0000
12.250 1.1381 0.03785 0.02958 0.0278 0.2220 1.0000
12.500 1.1210 0.03873 0.03059 0.0339 0.2177 1.0000
12.750 1.1368 0.03920 0.03093 0.0355 0.2112 1.0000
13.000 1.1315 0.04032 0.03211 0.0395 0.2065 1.0000
13.250 1.1102 0.04164 0.03362 0.0452 0.2025 1.0000
13.500 1.1121 0.04245 0.03442 0.0480 0.1970 1.0000
13.750 1.1208 0.04335 0.03525 0.0500 0.1912 1.0000
14.000 1.0951 0.04533 0.03746 0.0548 0.1874 1.0000
14.250 1.0909 0.04660 0.03877 0.0575 0.1823 1.0000
14.500 1.1028 0.04736 0.03943 0.0588 0.1763 1.0000
14.750 1.0741 0.05024 0.04256 0.0623 0.1728 1.0000
15.000 1.0668 0.05206 0.04446 0.0643 0.1681 1.0000
15.250 1.0840 0.05259 0.04485 0.0652 0.1624 1.0000
15.500 1.0490 0.05673 0.04926 0.0673 0.1594 1.0000
15.750 1.0291 0.06015 0.05283 0.0684 0.1558 1.0000
16.000 1.0689 0.05892 0.05132 0.0691 0.1496 1.0000
16.250 1.0251 0.06468 0.05740 0.0697 0.1478 1.0000
16.500 0.9650 0.07312 0.06617 0.0686 0.1465 1.0000
17.000 1.0166 0.07257 0.06538 0.0705 0.1372 1.0000
17.250 0.9304 0.08518 0.07839 0.0668 0.1373 1.0000
17.500 0.4757 0.17877 0.17232 0.0212 0.1817 1.0000
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