GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 572 AIRFOIL (goe572-il) Reynolds number: 500,000 Max Cl/Cd: 77.53 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe572-il-500000-n5.txt Download as CSV file: xf-goe572-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 572 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2181 0.02792 0.02290 -0.1420 0.5546 0.0136
-10.250 -0.2327 0.02493 0.01951 -0.1366 0.5507 0.0139
-10.000 -0.2262 0.02379 0.01819 -0.1334 0.5453 0.0142
-9.750 -0.2097 0.02348 0.01782 -0.1315 0.5399 0.0146
-9.500 -0.1959 0.02285 0.01708 -0.1292 0.5344 0.0149
-9.250 -0.1790 0.02244 0.01659 -0.1273 0.5294 0.0153
-9.000 -0.1668 0.02165 0.01562 -0.1246 0.5241 0.0157
-8.750 -0.1523 0.02095 0.01475 -0.1223 0.5198 0.0163
-8.500 -0.1397 0.01997 0.01355 -0.1196 0.5155 0.0169
-8.250 -0.1254 0.01916 0.01253 -0.1171 0.5109 0.0174
-8.000 -0.1069 0.01891 0.01220 -0.1153 0.5063 0.0178
-7.750 -0.0858 0.01878 0.01204 -0.1140 0.5021 0.0183
-7.500 -0.0665 0.01844 0.01161 -0.1123 0.4978 0.0188
-7.250 -0.0466 0.01820 0.01127 -0.1106 0.4932 0.0197
-7.000 -0.0289 0.01770 0.01059 -0.1086 0.4891 0.0204
-6.750 -0.0092 0.01727 0.01001 -0.1070 0.4856 0.0213
-6.500 0.0116 0.01710 0.00981 -0.1055 0.4814 0.0218
-6.250 0.0322 0.01693 0.00959 -0.1040 0.4772 0.0224
-6.000 0.0520 0.01677 0.00934 -0.1023 0.4728 0.0232
-5.750 0.0730 0.01650 0.00896 -0.1008 0.4696 0.0241
-5.500 0.0940 0.01620 0.00854 -0.0994 0.4660 0.0250
-5.250 0.1142 0.01589 0.00813 -0.0978 0.4620 0.0258
-5.000 0.1341 0.01569 0.00788 -0.0961 0.4581 0.0265
-4.750 0.1544 0.01551 0.00765 -0.0945 0.4543 0.0272
-4.500 0.1758 0.01531 0.00740 -0.0931 0.4508 0.0280
-4.250 0.1965 0.01515 0.00717 -0.0916 0.4469 0.0290
-4.000 0.2161 0.01501 0.00694 -0.0898 0.4432 0.0300
-3.750 0.2349 0.01488 0.00670 -0.0879 0.4398 0.0306
-3.500 0.2540 0.01452 0.00632 -0.0861 0.4367 0.0316
-3.250 0.2738 0.01436 0.00614 -0.0844 0.4325 0.0325
-3.000 0.2932 0.01420 0.00594 -0.0826 0.4289 0.0333
-2.750 0.3117 0.01409 0.00576 -0.0806 0.4249 0.0341
-2.500 0.3317 0.01398 0.00561 -0.0790 0.4217 0.0351
-2.250 0.3524 0.01385 0.00544 -0.0775 0.4186 0.0359
-2.000 0.3725 0.01375 0.00529 -0.0759 0.4149 0.0367
-1.750 0.3910 0.01363 0.00513 -0.0739 0.4110 0.0374
-1.500 0.4091 0.01355 0.00500 -0.0720 0.4077 0.0385
-1.250 0.4300 0.01348 0.00492 -0.0705 0.4044 0.0396
-1.000 0.4505 0.01346 0.00488 -0.0691 0.4002 0.0411
-0.750 0.4705 0.01346 0.00484 -0.0675 0.3967 0.0427
-0.500 0.4890 0.01349 0.00482 -0.0657 0.3929 0.0437
-0.250 0.5095 0.01351 0.00481 -0.0642 0.3898 0.0447
0.000 0.5301 0.01347 0.00478 -0.0628 0.3861 0.0481
0.250 0.5502 0.01351 0.00479 -0.0614 0.3822 0.0509
0.500 0.5694 0.01359 0.00483 -0.0598 0.3787 0.0538
0.750 0.5885 0.01364 0.00489 -0.0581 0.3755 0.0613
1.000 0.6097 0.01367 0.00493 -0.0570 0.3721 0.0702
1.250 0.6297 0.01373 0.00501 -0.0556 0.3680 0.0845
1.500 0.6491 0.01379 0.00510 -0.0541 0.3644 0.1066
1.750 0.6673 0.01384 0.00525 -0.0526 0.3606 0.1537
2.000 0.6892 0.01378 0.00539 -0.0518 0.3570 0.2322
2.250 0.7141 0.01342 0.00562 -0.0519 0.3539 0.4549
2.500 1.0459 0.01354 0.00672 -0.1187 0.3418 1.0000
2.750 1.0620 0.01371 0.00685 -0.1166 0.3390 1.0000
3.000 1.0777 0.01390 0.00700 -0.1144 0.3361 1.0000
3.250 1.0929 0.01412 0.00718 -0.1122 0.3334 1.0000
3.500 1.1072 0.01437 0.00739 -0.1099 0.3306 1.0000
3.750 1.1247 0.01456 0.00757 -0.1082 0.3283 1.0000
4.000 1.1417 0.01477 0.00777 -0.1065 0.3258 1.0000
4.250 1.1577 0.01502 0.00800 -0.1046 0.3226 1.0000
4.500 1.1731 0.01530 0.00826 -0.1026 0.3199 1.0000
4.750 1.1873 0.01563 0.00856 -0.1005 0.3172 1.0000
5.000 1.2028 0.01594 0.00886 -0.0986 0.3148 1.0000
5.250 1.2198 0.01622 0.00914 -0.0971 0.3126 1.0000
5.500 1.2361 0.01654 0.00946 -0.0955 0.3103 1.0000
5.750 1.2514 0.01690 0.00982 -0.0938 0.3077 1.0000
6.000 1.2658 0.01731 0.01023 -0.0920 0.3053 1.0000
6.250 1.2792 0.01778 0.01069 -0.0901 0.3031 1.0000
6.500 1.2921 0.01830 0.01120 -0.0882 0.3009 1.0000
6.750 1.3083 0.01871 0.01164 -0.0869 0.2991 1.0000
7.000 1.3237 0.01917 0.01212 -0.0855 0.2971 1.0000
7.250 1.3382 0.01969 0.01266 -0.0840 0.2949 1.0000
7.500 1.3518 0.02028 0.01327 -0.0825 0.2928 1.0000
8.000 1.3756 0.02170 0.01472 -0.0794 0.2886 1.0000
8.250 1.3855 0.02257 0.01560 -0.0777 0.2861 1.0000
8.500 1.3996 0.02325 0.01632 -0.0765 0.2844 1.0000
8.750 1.4127 0.02401 0.01713 -0.0754 0.2819 1.0000
9.000 1.4240 0.02491 0.01806 -0.0742 0.2789 1.0000
9.250 1.4301 0.02618 0.01933 -0.0725 0.2742 1.0000
9.500 1.4357 0.02755 0.02070 -0.0710 0.2711 1.0000
9.750 1.4474 0.02855 0.02175 -0.0700 0.2681 1.0000
10.000 1.4541 0.02996 0.02319 -0.0688 0.2627 1.0000
10.250 1.4599 0.03147 0.02472 -0.0676 0.2600 1.0000
10.500 1.4624 0.03330 0.02658 -0.0663 0.2568 1.0000
10.750 1.4689 0.03486 0.02818 -0.0654 0.2526 1.0000
11.000 1.4747 0.03650 0.02987 -0.0645 0.2494 1.0000
11.250 1.4738 0.03878 0.03219 -0.0633 0.2447 1.0000
11.500 1.4704 0.04138 0.03480 -0.0622 0.2402 1.0000
11.750 1.4736 0.04340 0.03688 -0.0614 0.2362 1.0000
12.000 1.4660 0.04649 0.03999 -0.0603 0.2296 1.0000
12.250 1.4591 0.04961 0.04313 -0.0593 0.2247 1.0000
12.500 1.4493 0.05309 0.04664 -0.0584 0.2165 1.0000
12.750 1.4375 0.05685 0.05042 -0.0575 0.2106 1.0000
13.000 1.4305 0.06017 0.05379 -0.0568 0.2049 1.0000
13.250 1.4149 0.06452 0.05815 -0.0560 0.1979 1.0000
13.500 1.3896 0.07004 0.06368 -0.0552 0.1858 1.0000
13.750 1.3647 0.07569 0.06933 -0.0546 0.1723 1.0000
14.000 1.3475 0.08056 0.07421 -0.0542 0.1618 1.0000
14.250 1.3138 0.08754 0.08118 -0.0538 0.1395 1.0000
14.500 1.2890 0.09359 0.08726 -0.0537 0.1248 1.0000
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