GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.69 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe532-il-1000000-n5.txt Download as CSV file: xf-goe532-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7488 0.02559 0.02226 -0.1040 0.9739 0.0203
-11.750 -0.7188 0.02338 0.01985 -0.1075 0.9647 0.0205
-11.500 -0.6833 0.02215 0.01852 -0.1105 0.9549 0.0207
-11.250 -0.6475 0.02125 0.01752 -0.1130 0.9414 0.0209
-11.000 -0.6152 0.02067 0.01684 -0.1144 0.9220 0.0210
-10.750 -0.5892 0.02012 0.01617 -0.1145 0.8993 0.0212
-10.500 -0.5657 0.01965 0.01556 -0.1140 0.8788 0.0213
-10.250 -0.5431 0.01907 0.01484 -0.1134 0.8609 0.0215
-10.000 -0.5206 0.01841 0.01404 -0.1128 0.8463 0.0217
-9.750 -0.4976 0.01779 0.01327 -0.1122 0.8333 0.0219
-9.500 -0.4745 0.01713 0.01246 -0.1115 0.8201 0.0221
-9.250 -0.4506 0.01653 0.01172 -0.1110 0.8068 0.0223
-9.000 -0.4267 0.01592 0.01097 -0.1104 0.7935 0.0225
-8.750 -0.4024 0.01537 0.01028 -0.1098 0.7789 0.0227
-8.500 -0.3777 0.01488 0.00965 -0.1092 0.7634 0.0229
-8.250 -0.3525 0.01449 0.00912 -0.1087 0.7461 0.0232
-8.000 -0.3274 0.01412 0.00861 -0.1081 0.7254 0.0234
-7.750 -0.3023 0.01377 0.00811 -0.1074 0.6995 0.0235
-7.500 -0.2774 0.01348 0.00765 -0.1068 0.6718 0.0236
-7.250 -0.2526 0.01305 0.00706 -0.1062 0.6481 0.0238
-7.000 -0.2275 0.01260 0.00650 -0.1056 0.6288 0.0240
-6.750 -0.2015 0.01230 0.00610 -0.1052 0.6128 0.0242
-6.500 -0.1751 0.01203 0.00575 -0.1047 0.6000 0.0244
-6.250 -0.1482 0.01180 0.00545 -0.1044 0.5882 0.0247
-6.000 -0.1213 0.01156 0.00516 -0.1040 0.5780 0.0249
-5.750 -0.0943 0.01135 0.00488 -0.1037 0.5674 0.0251
-5.500 -0.0672 0.01115 0.00462 -0.1033 0.5557 0.0254
-5.250 -0.0404 0.01098 0.00436 -0.1029 0.5407 0.0256
-5.000 -0.0134 0.01083 0.00413 -0.1025 0.5263 0.0260
-4.750 0.0137 0.01069 0.00391 -0.1022 0.5134 0.0264
-4.500 0.0412 0.01052 0.00369 -0.1019 0.5047 0.0267
-4.250 0.0686 0.01038 0.00348 -0.1016 0.4958 0.0269
-4.000 0.0962 0.01023 0.00328 -0.1013 0.4888 0.0272
-3.750 0.1239 0.01010 0.00311 -0.1010 0.4813 0.0274
-3.500 0.1513 0.00993 0.00289 -0.1007 0.4747 0.0277
-3.250 0.1789 0.00976 0.00269 -0.1004 0.4685 0.0281
-3.000 0.2066 0.00965 0.00255 -0.1002 0.4620 0.0286
-2.750 0.2344 0.00956 0.00243 -0.0999 0.4560 0.0290
-2.500 0.2621 0.00948 0.00232 -0.0996 0.4481 0.0295
-2.250 0.2897 0.00944 0.00223 -0.0994 0.4399 0.0300
-2.000 0.3177 0.00937 0.00214 -0.0991 0.4340 0.0306
-1.750 0.3455 0.00933 0.00207 -0.0989 0.4282 0.0312
-1.500 0.3733 0.00930 0.00201 -0.0986 0.4230 0.0318
-1.250 0.4014 0.00922 0.00193 -0.0984 0.4193 0.0329
-1.000 0.4293 0.00918 0.00188 -0.0982 0.4146 0.0339
-0.750 0.4572 0.00916 0.00184 -0.0980 0.4098 0.0350
-0.500 0.4850 0.00916 0.00182 -0.0977 0.4051 0.0363
-0.250 0.5130 0.00912 0.00179 -0.0975 0.3999 0.0388
0.000 0.5407 0.00912 0.00179 -0.0973 0.3941 0.0427
0.250 0.5683 0.00911 0.00179 -0.0970 0.3885 0.0528
0.500 0.5959 0.00903 0.00179 -0.0968 0.3821 0.0848
0.750 0.6222 0.00876 0.00180 -0.0966 0.3735 0.2090
1.000 0.6492 0.00862 0.00185 -0.0963 0.3652 0.2866
1.250 0.6758 0.00861 0.00191 -0.0960 0.3533 0.3405
1.500 0.7021 0.00861 0.00200 -0.0956 0.3379 0.4000
1.750 0.7274 0.00864 0.00213 -0.0951 0.3139 0.4825
2.000 0.7465 0.00932 0.00253 -0.0937 0.2312 0.5405
2.500 0.7944 0.00972 0.00300 -0.0921 0.1851 0.6620
2.750 0.8199 0.00979 0.00315 -0.0916 0.1788 0.7114
3.000 0.8450 0.00986 0.00330 -0.0909 0.1736 0.7558
3.250 0.8683 0.00980 0.00343 -0.0898 0.1693 0.8311
3.500 0.9086 0.00973 0.00358 -0.0924 0.1666 1.0000
3.750 0.9350 0.00989 0.00371 -0.0920 0.1644 1.0000
4.000 0.9614 0.01005 0.00385 -0.0916 0.1624 1.0000
4.250 0.9875 0.01023 0.00399 -0.0912 0.1603 1.0000
4.500 1.0135 0.01042 0.00415 -0.0907 0.1578 1.0000
4.750 1.0393 0.01061 0.00432 -0.0903 0.1548 1.0000
5.000 1.0655 0.01077 0.00447 -0.0899 0.1535 1.0000
5.250 1.0916 0.01092 0.00462 -0.0895 0.1523 1.0000
5.500 1.1175 0.01109 0.00478 -0.0891 0.1509 1.0000
5.750 1.1431 0.01127 0.00496 -0.0886 0.1490 1.0000
6.000 1.1683 0.01147 0.00514 -0.0881 0.1462 1.0000
6.250 1.1930 0.01171 0.00535 -0.0876 0.1424 1.0000
6.500 1.2177 0.01193 0.00556 -0.0870 0.1394 1.0000
6.750 1.2428 0.01211 0.00575 -0.0865 0.1371 1.0000
7.000 1.2672 0.01234 0.00596 -0.0859 0.1321 1.0000
7.250 1.2900 0.01267 0.00622 -0.0851 0.1211 1.0000
7.500 1.3044 0.01355 0.00684 -0.0830 0.0852 1.0000
7.750 1.3252 0.01396 0.00723 -0.0819 0.0810 1.0000
8.000 1.3464 0.01432 0.00759 -0.0808 0.0779 1.0000
8.250 1.3682 0.01462 0.00791 -0.0798 0.0765 1.0000
8.500 1.3892 0.01495 0.00825 -0.0787 0.0751 1.0000
8.750 1.4093 0.01531 0.00862 -0.0775 0.0736 1.0000
9.000 1.4283 0.01570 0.00903 -0.0761 0.0722 1.0000
9.250 1.4449 0.01610 0.00944 -0.0743 0.0707 1.0000
9.500 1.4599 0.01652 0.00988 -0.0722 0.0692 1.0000
9.750 1.4769 0.01686 0.01025 -0.0704 0.0686 1.0000
10.000 1.4932 0.01724 0.01066 -0.0687 0.0680 1.0000
10.250 1.5088 0.01766 0.01111 -0.0668 0.0672 1.0000
10.500 1.5238 0.01812 0.01160 -0.0650 0.0664 1.0000
10.750 1.5382 0.01863 0.01215 -0.0632 0.0656 1.0000
11.000 1.5516 0.01920 0.01275 -0.0613 0.0647 1.0000
11.250 1.5643 0.01984 0.01342 -0.0594 0.0638 1.0000
11.500 1.5762 0.02054 0.01416 -0.0576 0.0630 1.0000
11.750 1.5869 0.02135 0.01501 -0.0558 0.0620 1.0000
12.000 1.5966 0.02227 0.01597 -0.0539 0.0611 1.0000
12.250 1.6080 0.02314 0.01689 -0.0524 0.0607 1.0000
12.500 1.6197 0.02403 0.01784 -0.0510 0.0603 1.0000
12.750 1.6307 0.02502 0.01888 -0.0497 0.0598 1.0000
13.000 1.6417 0.02604 0.01996 -0.0486 0.0588 1.0000
13.250 1.6507 0.02727 0.02124 -0.0473 0.0583 1.0000
13.500 1.6595 0.02856 0.02259 -0.0463 0.0574 1.0000
13.750 1.6674 0.03000 0.02405 -0.0453 0.0561 1.0000
14.000 1.6736 0.03163 0.02573 -0.0443 0.0550 1.0000
14.250 1.6777 0.03354 0.02768 -0.0435 0.0538 1.0000
14.500 1.6838 0.03533 0.02954 -0.0429 0.0533 1.0000
14.750 1.6901 0.03717 0.03145 -0.0424 0.0528 1.0000
15.000 1.6952 0.03919 0.03354 -0.0420 0.0523 1.0000
15.250 1.6997 0.04132 0.03575 -0.0417 0.0514 1.0000
15.500 1.7030 0.04365 0.03814 -0.0415 0.0507 1.0000
15.750 1.7050 0.04615 0.04071 -0.0414 0.0499 1.0000
16.000 1.7063 0.04879 0.04341 -0.0414 0.0490 1.0000
16.250 1.7059 0.05168 0.04635 -0.0415 0.0480 1.0000
16.500 1.7045 0.05473 0.04946 -0.0417 0.0472 1.0000
16.750 1.7045 0.05767 0.05248 -0.0419 0.0466 1.0000
17.000 1.7046 0.06064 0.05553 -0.0423 0.0460 1.0000
17.250 1.7034 0.06384 0.05881 -0.0428 0.0454 1.0000
17.500 1.7017 0.06714 0.06218 -0.0433 0.0445 1.0000
17.750 1.6993 0.07057 0.06568 -0.0440 0.0437 1.0000
18.000 1.6961 0.07417 0.06934 -0.0448 0.0427 1.0000
18.250 1.6915 0.07805 0.07329 -0.0457 0.0420 1.0000
18.500 1.6860 0.08209 0.07740 -0.0468 0.0411 1.0000
18.750 1.6839 0.08568 0.08108 -0.0478 0.0404 1.0000
19.000 1.6801 0.08962 0.08510 -0.0490 0.0395 1.0000
19.250 1.6751 0.09377 0.08933 -0.0504 0.0385 1.0000
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