GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 500,000 Max Cl/Cd: 73.89 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe681-il-500000-n5.txt Download as CSV file: xf-goe681-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 681 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6666 0.08932 0.08566 -0.0720 1.0000 0.0270
-16.000 -0.7026 0.08022 0.07639 -0.0775 1.0000 0.0271
-15.750 -0.7288 0.07323 0.06926 -0.0816 1.0000 0.0272
-15.500 -0.7510 0.06710 0.06301 -0.0850 1.0000 0.0271
-15.250 -0.7707 0.06137 0.05717 -0.0882 1.0000 0.0272
-15.000 -0.7868 0.05628 0.05197 -0.0910 1.0000 0.0272
-14.750 -0.8027 0.05131 0.04689 -0.0937 1.0000 0.0273
-14.500 -0.8167 0.04680 0.04227 -0.0961 1.0000 0.0273
-14.250 -0.8282 0.04294 0.03830 -0.0978 1.0000 0.0273
-13.750 -0.8160 0.03570 0.03079 -0.1064 0.9931 0.0276
-13.500 -0.8052 0.03311 0.02808 -0.1093 0.9862 0.0277
-13.250 -0.7924 0.03102 0.02588 -0.1114 0.9784 0.0278
-13.000 -0.7772 0.02932 0.02406 -0.1129 0.9698 0.0279
-12.750 -0.7604 0.02786 0.02249 -0.1138 0.9598 0.0281
-12.500 -0.7358 0.02654 0.02106 -0.1157 0.9517 0.0283
-12.250 -0.7066 0.02528 0.01969 -0.1180 0.9427 0.0285
-12.000 -0.6754 0.02413 0.01842 -0.1204 0.9324 0.0287
-11.750 -0.6429 0.02306 0.01723 -0.1228 0.9202 0.0288
-11.250 -0.5931 0.02149 0.01540 -0.1238 0.8869 0.0291
-11.000 -0.5775 0.02068 0.01449 -0.1224 0.8700 0.0292
-10.750 -0.5622 0.02003 0.01375 -0.1207 0.8553 0.0294
-10.500 -0.5467 0.01945 0.01307 -0.1189 0.8429 0.0296
-10.250 -0.5306 0.01892 0.01247 -0.1171 0.8316 0.0298
-10.000 -0.5132 0.01844 0.01191 -0.1155 0.8218 0.0300
-9.750 -0.4953 0.01798 0.01138 -0.1138 0.8122 0.0301
-9.500 -0.4766 0.01754 0.01086 -0.1123 0.8040 0.0303
-9.250 -0.4571 0.01712 0.01039 -0.1109 0.7960 0.0305
-9.000 -0.4372 0.01673 0.00992 -0.1095 0.7880 0.0307
-8.750 -0.4167 0.01632 0.00946 -0.1082 0.7809 0.0310
-8.500 -0.3957 0.01595 0.00904 -0.1070 0.7734 0.0313
-8.250 -0.3741 0.01561 0.00862 -0.1058 0.7665 0.0315
-8.000 -0.3521 0.01526 0.00823 -0.1047 0.7599 0.0318
-7.750 -0.3298 0.01494 0.00785 -0.1036 0.7525 0.0321
-7.500 -0.3070 0.01465 0.00749 -0.1026 0.7461 0.0324
-7.250 -0.2835 0.01437 0.00716 -0.1017 0.7398 0.0327
-7.000 -0.2605 0.01406 0.00681 -0.1007 0.7329 0.0331
-6.750 -0.2379 0.01374 0.00643 -0.0996 0.7262 0.0336
-6.500 -0.2141 0.01344 0.00611 -0.0988 0.7200 0.0341
-6.250 -0.1900 0.01318 0.00582 -0.0979 0.7134 0.0346
-6.000 -0.1658 0.01296 0.00555 -0.0971 0.7070 0.0351
-5.750 -0.1411 0.01275 0.00529 -0.0963 0.6997 0.0356
-5.500 -0.1167 0.01256 0.00505 -0.0955 0.6910 0.0363
-5.250 -0.0921 0.01239 0.00482 -0.0946 0.6825 0.0369
-5.000 -0.0677 0.01219 0.00458 -0.0938 0.6733 0.0377
-4.750 -0.0434 0.01201 0.00436 -0.0929 0.6644 0.0389
-4.500 -0.0186 0.01185 0.00416 -0.0921 0.6548 0.0403
-4.250 0.0058 0.01172 0.00397 -0.0912 0.6455 0.0421
-4.000 0.0303 0.01154 0.00379 -0.0904 0.6350 0.0460
-3.750 0.0539 0.01131 0.00362 -0.0894 0.6270 0.0602
-3.500 0.0788 0.01112 0.00347 -0.0887 0.6191 0.0774
-3.250 0.1029 0.01097 0.00334 -0.0878 0.6106 0.0897
-3.000 0.1277 0.01081 0.00321 -0.0870 0.6024 0.1034
-2.750 0.1516 0.01063 0.00311 -0.0862 0.5941 0.1264
-2.500 0.1760 0.01051 0.00306 -0.0853 0.5855 0.1504
-2.250 0.2010 0.01045 0.00303 -0.0846 0.5762 0.1678
-2.000 0.2261 0.01044 0.00300 -0.0838 0.5672 0.1786
-1.750 0.2513 0.01042 0.00297 -0.0831 0.5575 0.1870
-1.500 0.2764 0.01044 0.00296 -0.0824 0.5488 0.1960
-1.250 0.3011 0.01044 0.00294 -0.0815 0.5376 0.2030
-1.000 0.3257 0.01045 0.00292 -0.0807 0.5274 0.2092
-0.750 0.3497 0.01050 0.00291 -0.0797 0.5154 0.2147
-0.500 0.3744 0.01051 0.00291 -0.0789 0.5041 0.2213
-0.250 0.3979 0.01054 0.00292 -0.0779 0.4923 0.2296
0.000 0.4213 0.01061 0.00294 -0.0769 0.4790 0.2361
0.250 0.4443 0.01065 0.00296 -0.0758 0.4647 0.2456
0.500 0.4666 0.01073 0.00299 -0.0745 0.4488 0.2539
0.750 0.4880 0.01085 0.00304 -0.0731 0.4304 0.2613
1.000 0.5085 0.01096 0.00311 -0.0716 0.4115 0.2725
1.250 0.5289 0.01109 0.00318 -0.0701 0.3933 0.2838
1.500 0.5492 0.01122 0.00327 -0.0685 0.3774 0.2987
1.750 0.5691 0.01132 0.00337 -0.0669 0.3636 0.3201
2.000 0.5879 0.01139 0.00349 -0.0651 0.3511 0.3552
2.250 0.6072 0.01140 0.00360 -0.0634 0.3410 0.4056
2.500 0.6241 0.01140 0.00373 -0.0612 0.3323 0.4635
2.750 0.6410 0.01137 0.00384 -0.0590 0.3246 0.5213
3.250 0.6643 0.01108 0.00415 -0.0524 0.3118 0.7289
3.500 0.6792 0.01096 0.00438 -0.0495 0.3057 0.8426
3.750 0.7813 0.01143 0.00493 -0.0653 0.2950 0.9525
4.000 0.8363 0.01175 0.00520 -0.0711 0.2886 0.9748
4.250 0.8724 0.01206 0.00545 -0.0730 0.2830 0.9893
4.500 0.9100 0.01238 0.00572 -0.0752 0.2784 0.9999
4.750 0.9227 0.01251 0.00584 -0.0722 0.2753 1.0000
5.000 0.9354 0.01266 0.00598 -0.0692 0.2720 1.0000
5.250 0.9485 0.01286 0.00615 -0.0663 0.2683 1.0000
5.500 0.9617 0.01310 0.00635 -0.0635 0.2646 1.0000
5.750 0.9768 0.01333 0.00656 -0.0612 0.2615 1.0000
6.000 0.9940 0.01353 0.00677 -0.0592 0.2587 1.0000
6.250 1.0110 0.01377 0.00699 -0.0573 0.2557 1.0000
6.500 1.0276 0.01404 0.00725 -0.0553 0.2528 1.0000
6.750 1.0438 0.01434 0.00754 -0.0533 0.2501 1.0000
7.000 1.0597 0.01468 0.00785 -0.0514 0.2473 1.0000
7.250 1.0764 0.01501 0.00818 -0.0496 0.2449 1.0000
7.500 1.0950 0.01529 0.00849 -0.0482 0.2430 1.0000
7.750 1.1129 0.01562 0.00882 -0.0467 0.2409 1.0000
8.000 1.1304 0.01598 0.00919 -0.0452 0.2383 1.0000
8.250 1.1474 0.01637 0.00959 -0.0437 0.2359 1.0000
8.500 1.1630 0.01685 0.01004 -0.0420 0.2324 1.0000
8.750 1.1784 0.01736 0.01053 -0.0404 0.2292 1.0000
9.000 1.1970 0.01774 0.01095 -0.0393 0.2271 1.0000
9.250 1.2149 0.01818 0.01141 -0.0381 0.2247 1.0000
9.500 1.2321 0.01867 0.01192 -0.0369 0.2227 1.0000
9.750 1.2487 0.01920 0.01247 -0.0357 0.2206 1.0000
10.000 1.2646 0.01979 0.01306 -0.0344 0.2183 1.0000
10.250 1.2794 0.02045 0.01372 -0.0332 0.2159 1.0000
10.500 1.2947 0.02112 0.01440 -0.0320 0.2136 1.0000
10.750 1.3125 0.02165 0.01498 -0.0311 0.2117 1.0000
11.000 1.3291 0.02227 0.01564 -0.0301 0.2089 1.0000
11.250 1.3449 0.02295 0.01634 -0.0291 0.2065 1.0000
11.500 1.3597 0.02371 0.01713 -0.0281 0.2042 1.0000
11.750 1.3733 0.02455 0.01798 -0.0270 0.2018 1.0000
12.000 1.3862 0.02547 0.01891 -0.0260 0.1990 1.0000
12.250 1.4025 0.02617 0.01966 -0.0252 0.1972 1.0000
12.500 1.4177 0.02697 0.02051 -0.0244 0.1948 1.0000
12.750 1.4316 0.02787 0.02144 -0.0235 0.1919 1.0000
13.000 1.4434 0.02893 0.02252 -0.0226 0.1887 1.0000
13.250 1.4543 0.03007 0.02368 -0.0217 0.1862 1.0000
13.500 1.4678 0.03105 0.02471 -0.0209 0.1841 1.0000
13.750 1.4814 0.03203 0.02575 -0.0203 0.1812 1.0000
14.000 1.4930 0.03319 0.02694 -0.0195 0.1775 1.0000
14.250 1.5016 0.03462 0.02840 -0.0187 0.1738 1.0000
14.500 1.5119 0.03593 0.02974 -0.0181 0.1701 1.0000
14.750 1.5220 0.03728 0.03113 -0.0174 0.1653 1.0000
15.000 1.5276 0.03906 0.03292 -0.0167 0.1606 1.0000
15.250 1.5360 0.04061 0.03451 -0.0162 0.1553 1.0000
15.500 1.5391 0.04270 0.03661 -0.0156 0.1487 1.0000
15.750 1.5432 0.04472 0.03865 -0.0150 0.1416 1.0000
16.000 1.5429 0.04720 0.04114 -0.0145 0.1337 1.0000
16.250 1.5377 0.05025 0.04418 -0.0140 0.1236 1.0000
16.500 1.5289 0.05375 0.04767 -0.0137 0.1130 1.0000
16.750 1.5164 0.05774 0.05165 -0.0134 0.1024 1.0000
17.000 1.4997 0.06235 0.05626 -0.0135 0.0922 1.0000
17.250 1.4829 0.06712 0.06107 -0.0137 0.0842 1.0000
17.500 1.4673 0.07189 0.06588 -0.0142 0.0783 1.0000
17.750 1.4502 0.07700 0.07105 -0.0149 0.0730 1.0000
18.000 1.4336 0.08217 0.07629 -0.0157 0.0673 1.0000
18.250 1.4162 0.08756 0.08175 -0.0168 0.0619 1.0000
18.500 1.3887 0.09450 0.08876 -0.0185 0.0536 1.0000
18.750 1.3605 0.10168 0.09601 -0.0204 0.0458 1.0000
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