GOE 434 AIRFOIL (goe434-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 434 AIRFOIL (goe434-il) Reynolds number: 100,000 Max Cl/Cd: 36.72 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe434-il-100000-n5.txt Download as CSV file: xf-goe434-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 434 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.1910 0.12703 0.12077 -0.0727 0.9629 0.0882
-13.500 -0.1923 0.12070 0.11440 -0.0769 0.9521 0.0898
-13.250 -0.5016 0.06561 0.05817 -0.1072 0.9528 0.0996
-13.000 -0.4834 0.06341 0.05597 -0.1097 0.9411 0.1009
-12.750 -0.4646 0.06199 0.05459 -0.1108 0.9251 0.1022
-12.500 -0.4597 0.05907 0.05159 -0.1128 0.9072 0.1036
-12.250 -0.4608 0.05559 0.04797 -0.1150 0.8888 0.1050
-12.000 -0.4628 0.05220 0.04440 -0.1169 0.8711 0.1065
-11.750 -0.4647 0.04898 0.04094 -0.1186 0.8548 0.1079
-11.500 -0.4499 0.04789 0.03986 -0.1183 0.8405 0.1093
-11.250 -0.4385 0.04650 0.03845 -0.1185 0.8270 0.1109
-11.000 -0.4301 0.04473 0.03657 -0.1190 0.8155 0.1126
-10.750 -0.4232 0.04281 0.03455 -0.1197 0.8040 0.1144
-10.500 -0.4164 0.04084 0.03241 -0.1205 0.7940 0.1164
-10.250 -0.4033 0.03960 0.03116 -0.1208 0.7855 0.1181
-10.000 -0.3923 0.03821 0.02976 -0.1213 0.7761 0.1202
-9.750 -0.3831 0.03667 0.02814 -0.1218 0.7681 0.1226
-9.500 -0.3752 0.03514 0.02646 -0.1224 0.7610 0.1252
-9.250 -0.3625 0.03385 0.02519 -0.1234 0.7532 0.1277
-9.000 -0.3476 0.03253 0.02381 -0.1248 0.7467 0.1308
-8.750 -0.3300 0.03124 0.02239 -0.1262 0.7415 0.1349
-8.500 -0.3111 0.03022 0.02133 -0.1273 0.7366 0.1388
-8.250 -0.2924 0.02930 0.02038 -0.1281 0.7308 0.1440
-8.000 -0.2721 0.02845 0.01950 -0.1287 0.7252 0.1498
-7.750 -0.2502 0.02762 0.01860 -0.1294 0.7202 0.1570
-7.500 -0.2269 0.02685 0.01781 -0.1301 0.7161 0.1645
-7.250 -0.2025 0.02617 0.01705 -0.1309 0.7123 0.1739
-7.000 -0.1795 0.02562 0.01657 -0.1314 0.7078 0.1835
-6.750 -0.1550 0.02517 0.01618 -0.1318 0.7032 0.1936
-6.500 -0.1290 0.02481 0.01583 -0.1322 0.6988 0.2045
-6.250 -0.1017 0.02451 0.01551 -0.1327 0.6948 0.2161
-6.000 -0.0733 0.02432 0.01528 -0.1331 0.6915 0.2278
-5.750 -0.0444 0.02425 0.01517 -0.1335 0.6885 0.2387
-5.500 -0.0189 0.02422 0.01516 -0.1335 0.6842 0.2490
-5.250 0.0077 0.02416 0.01503 -0.1337 0.6798 0.2598
-5.000 0.0351 0.02424 0.01513 -0.1336 0.6757 0.2685
-4.750 0.0637 0.02416 0.01493 -0.1340 0.6721 0.2796
-4.500 0.0927 0.02428 0.01505 -0.1340 0.6687 0.2877
-4.250 0.1231 0.02418 0.01475 -0.1346 0.6657 0.2980
-4.000 0.1498 0.02439 0.01503 -0.1343 0.6621 0.3045
-3.750 0.1751 0.02454 0.01518 -0.1340 0.6578 0.3126
-3.500 0.2017 0.02457 0.01514 -0.1340 0.6536 0.3204
-3.250 0.2288 0.02473 0.01536 -0.1337 0.6497 0.3265
-3.000 0.2576 0.02480 0.01537 -0.1338 0.6462 0.3344
-2.750 0.2878 0.02475 0.01516 -0.1343 0.6431 0.3425
-2.500 0.3177 0.02487 0.01531 -0.1342 0.6403 0.3486
-2.250 0.3421 0.02509 0.01558 -0.1337 0.6364 0.3549
-2.000 0.3664 0.02525 0.01571 -0.1334 0.6321 0.3615
-1.750 0.3925 0.02530 0.01571 -0.1333 0.6279 0.3667
-1.500 0.4193 0.02536 0.01582 -0.1330 0.6240 0.3708
-1.250 0.4480 0.02539 0.01584 -0.1330 0.6207 0.3757
-1.000 0.4784 0.02538 0.01577 -0.1333 0.6178 0.3813
-0.750 0.5103 0.02537 0.01563 -0.1339 0.6153 0.3876
-0.500 0.5315 0.02568 0.01599 -0.1331 0.6108 0.3928
-0.250 0.5524 0.02600 0.01646 -0.1321 0.6058 0.3979
0.000 0.5770 0.02622 0.01673 -0.1315 0.6015 0.4041
0.250 0.6050 0.02631 0.01678 -0.1316 0.5979 0.4108
0.500 0.6358 0.02633 0.01667 -0.1320 0.5949 0.4167
0.750 0.6668 0.02627 0.01663 -0.1323 0.5922 0.4210
1.000 0.6918 0.02649 0.01691 -0.1319 0.5884 0.4253
1.250 0.7070 0.02698 0.01753 -0.1302 0.5819 0.4296
1.500 0.7312 0.02711 0.01766 -0.1296 0.5766 0.4348
1.750 0.7618 0.02698 0.01746 -0.1299 0.5723 0.4402
2.000 0.7969 0.02666 0.01704 -0.1307 0.5686 0.4453
2.250 0.8134 0.02704 0.01755 -0.1290 0.5622 0.4493
2.500 0.8311 0.02735 0.01796 -0.1276 0.5555 0.4542
2.750 0.8594 0.02724 0.01784 -0.1274 0.5506 0.4608
3.000 0.8938 0.02695 0.01745 -0.1280 0.5468 0.4684
3.250 0.9074 0.02743 0.01806 -0.1261 0.5400 0.4737
3.500 0.9239 0.02772 0.01846 -0.1244 0.5331 0.4793
3.750 0.9543 0.02744 0.01815 -0.1244 0.5279 0.4869
4.000 0.9758 0.02755 0.01827 -0.1233 0.5217 0.4948
4.250 0.9846 0.02815 0.01899 -0.1208 0.5138 0.5014
4.500 1.0102 0.02807 0.01896 -0.1202 0.5087 0.5100
4.750 1.0333 0.02814 0.01903 -0.1193 0.5038 0.5204
5.000 1.0308 0.02923 0.02027 -0.1155 0.4954 0.5278
5.250 1.0545 0.02925 0.02034 -0.1148 0.4898 0.5380
5.500 1.0692 0.02982 0.02094 -0.1132 0.4831 0.5491
5.750 1.0756 0.03083 0.02206 -0.1110 0.4747 0.5581
6.000 1.1051 0.03053 0.02174 -0.1107 0.4693 0.5721
6.250 1.1006 0.03234 0.02369 -0.1078 0.4595 0.5818
6.500 1.1229 0.03247 0.02383 -0.1070 0.4528 0.5966
6.750 1.1271 0.03387 0.02534 -0.1050 0.4436 0.6089
7.000 1.1439 0.03440 0.02587 -0.1039 0.4352 0.6248
7.250 1.1501 0.03575 0.02732 -0.1022 0.4254 0.6385
7.500 1.1672 0.03627 0.02784 -0.1012 0.4161 0.6556
7.750 1.1697 0.03804 0.02970 -0.0995 0.4049 0.6712
8.000 1.1908 0.03815 0.02978 -0.0984 0.3956 0.6917
8.250 1.1878 0.04050 0.03224 -0.0967 0.3828 0.7093
8.500 1.1972 0.04171 0.03347 -0.0954 0.3716 0.7321
8.750 1.2064 0.04289 0.03466 -0.0940 0.3599 0.7578
9.000 1.2070 0.04496 0.03681 -0.0925 0.3469 0.7853
9.250 1.2128 0.04631 0.03821 -0.0909 0.3351 0.8247
9.500 1.2119 0.04733 0.03927 -0.0883 0.3240 1.0000
9.750 1.2172 0.04940 0.04128 -0.0876 0.3119 1.0000
10.000 1.2271 0.05097 0.04273 -0.0869 0.3019 1.0000
10.250 1.2366 0.05258 0.04423 -0.0862 0.2924 1.0000
10.500 1.2460 0.05426 0.04582 -0.0855 0.2843 1.0000
10.750 1.2564 0.05582 0.04729 -0.0849 0.2769 1.0000
11.000 1.2679 0.05726 0.04863 -0.0842 0.2708 1.0000
11.250 1.2767 0.05908 0.05042 -0.0837 0.2646 1.0000
11.500 1.2894 0.06038 0.05161 -0.0830 0.2593 1.0000
11.750 1.3017 0.06180 0.05296 -0.0825 0.2545 1.0000
12.000 1.3097 0.06376 0.05495 -0.0820 0.2494 1.0000
12.250 1.3208 0.06531 0.05643 -0.0815 0.2448 1.0000
12.500 1.3385 0.06603 0.05701 -0.0808 0.2410 1.0000
12.750 1.3463 0.06807 0.05911 -0.0804 0.2372 1.0000
13.000 1.3547 0.07002 0.06111 -0.0800 0.2335 1.0000
13.250 1.3652 0.07171 0.06279 -0.0796 0.2300 1.0000
13.500 1.3801 0.07282 0.06384 -0.0791 0.2267 1.0000
13.750 1.3976 0.07359 0.06450 -0.0785 0.2236 1.0000
14.000 1.3980 0.07655 0.06760 -0.0784 0.2201 1.0000
14.250 1.4025 0.07900 0.07012 -0.0782 0.2167 1.0000
14.500 1.4107 0.08097 0.07211 -0.0779 0.2134 1.0000
14.750 1.4242 0.08222 0.07332 -0.0776 0.2104 1.0000
15.000 1.4407 0.08309 0.07410 -0.0771 0.2075 1.0000
15.250 1.4338 0.08705 0.07826 -0.0773 0.2044 1.0000
15.500 1.4330 0.09024 0.08156 -0.0775 0.2013 1.0000
15.750 1.4373 0.09277 0.08416 -0.0775 0.1985 1.0000
16.000 1.4468 0.09454 0.08594 -0.0774 0.1958 1.0000
16.250 1.4648 0.09515 0.08646 -0.0770 0.1934 1.0000
16.500 1.4597 0.09896 0.09041 -0.0775 0.1907 1.0000
16.750 1.4422 0.10462 0.09631 -0.0787 0.1873 1.0000
17.000 1.4351 0.10885 0.10068 -0.0796 0.1840 1.0000
17.250 1.4416 0.11107 0.10291 -0.0799 0.1812 1.0000
17.500 1.4606 0.11140 0.10315 -0.0796 0.1788 1.0000
17.750 1.4297 0.11938 0.11142 -0.0822 0.1751 1.0000
18.000 1.3848 0.12993 0.12230 -0.0864 0.1699 1.0000
18.250 1.3929 0.13198 0.12435 -0.0870 0.1671 1.0000
18.500 1.4185 0.13110 0.12337 -0.0862 0.1651 1.0000
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Polar data table (+)
Polar graphs
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