GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.15 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe437-il-1000000.txt Download as CSV file: xf-goe437-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 437 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3271 0.09374 0.09220 -0.0250 1.0000 0.0083
-8.000 -0.3278 0.09128 0.08976 -0.0245 1.0000 0.0088
-7.750 -0.3309 0.08915 0.08767 -0.0236 1.0000 0.0093
-7.500 -0.3277 0.08637 0.08491 -0.0252 0.9991 0.0096
-7.250 -0.3062 0.08212 0.08066 -0.0323 0.9955 0.0098
-7.000 -0.2830 0.07737 0.07591 -0.0394 0.9916 0.0098
-6.750 -0.2587 0.07254 0.07106 -0.0468 0.9876 0.0098
-6.250 -0.1480 0.04061 0.03917 -0.0691 0.9678 0.0102
-6.000 -0.1290 0.03531 0.03381 -0.0753 0.9571 0.0105
-5.750 -0.1100 0.03144 0.02988 -0.0792 0.9441 0.0107
-5.500 -0.0912 0.02786 0.02621 -0.0823 0.9279 0.0110
-5.250 -0.0726 0.02446 0.02269 -0.0848 0.9067 0.0116
-5.000 -0.0522 0.02053 0.01858 -0.0876 0.8830 0.0123
-4.750 -0.0270 0.01510 0.01166 -0.1014 0.9207 0.0094
-4.500 -0.0020 0.01360 0.00981 -0.1009 0.9017 0.0097
-4.250 0.0229 0.01260 0.00849 -0.1002 0.8766 0.0099
-4.000 0.0449 0.01007 0.00537 -0.0991 0.8503 0.0105
-3.750 0.0695 0.00931 0.00436 -0.0983 0.8273 0.0114
-3.500 0.0950 0.00884 0.00372 -0.0977 0.8085 0.0121
-3.250 0.1210 0.00853 0.00327 -0.0971 0.7924 0.0135
-3.000 0.1472 0.00826 0.00286 -0.0966 0.7781 0.0145
-2.750 0.1732 0.00786 0.00231 -0.0961 0.7656 0.0158
-2.500 0.1996 0.00753 0.00190 -0.0956 0.7544 0.0192
-2.250 0.2264 0.00748 0.00179 -0.0953 0.7436 0.0221
-2.000 0.2528 0.00724 0.00149 -0.0949 0.7327 0.0309
-1.750 0.2796 0.00711 0.00133 -0.0946 0.7217 0.0402
-1.500 0.3067 0.00708 0.00125 -0.0943 0.7111 0.0456
-1.250 0.3334 0.00696 0.00110 -0.0940 0.7002 0.0555
-1.000 0.3601 0.00686 0.00102 -0.0937 0.6877 0.0757
-0.750 0.3868 0.00683 0.00102 -0.0934 0.6730 0.1053
-0.500 0.4136 0.00684 0.00097 -0.0931 0.6557 0.1154
-0.250 0.4400 0.00687 0.00094 -0.0928 0.6346 0.1240
0.000 0.4660 0.00692 0.00090 -0.0924 0.6068 0.1325
0.250 0.4917 0.00702 0.00089 -0.0919 0.5778 0.1411
0.500 0.5176 0.00710 0.00091 -0.0915 0.5553 0.1564
0.750 0.5436 0.00712 0.00096 -0.0912 0.5387 0.1975
1.000 0.5675 0.00666 0.00107 -0.0907 0.5262 0.4609
1.250 0.6113 0.00557 0.00120 -0.0946 0.5143 1.0000
1.500 0.6374 0.00567 0.00124 -0.0942 0.5048 1.0000
1.750 0.6633 0.00579 0.00129 -0.0937 0.4955 1.0000
2.000 0.6894 0.00590 0.00135 -0.0934 0.4857 1.0000
2.250 0.7156 0.00600 0.00141 -0.0930 0.4764 1.0000
2.500 0.7416 0.00611 0.00148 -0.0926 0.4671 1.0000
2.750 0.7678 0.00622 0.00156 -0.0922 0.4570 1.0000
3.000 0.7940 0.00633 0.00163 -0.0919 0.4462 1.0000
3.250 0.8200 0.00646 0.00172 -0.0915 0.4345 1.0000
3.500 0.8458 0.00660 0.00181 -0.0911 0.4201 1.0000
3.750 0.8709 0.00681 0.00194 -0.0906 0.3983 1.0000
4.000 0.8959 0.00702 0.00206 -0.0901 0.3760 1.0000
4.250 0.9206 0.00728 0.00222 -0.0896 0.3534 1.0000
4.500 0.9451 0.00755 0.00239 -0.0890 0.3317 1.0000
4.750 0.9699 0.00779 0.00258 -0.0885 0.3122 1.0000
5.000 0.9941 0.00810 0.00278 -0.0879 0.2873 1.0000
5.250 1.0160 0.00864 0.00306 -0.0870 0.2351 1.0000
5.500 1.0209 0.01103 0.00435 -0.0836 0.0338 1.0000
5.750 1.0433 0.01158 0.00485 -0.0826 0.0170 1.0000
6.000 1.0664 0.01203 0.00541 -0.0817 0.0139 1.0000
6.250 1.0900 0.01240 0.00582 -0.0809 0.0128 1.0000
6.500 1.1132 0.01280 0.00625 -0.0802 0.0112 1.0000
6.750 1.1347 0.01338 0.00689 -0.0791 0.0099 1.0000
7.000 1.1491 0.01471 0.00841 -0.0767 0.0087 1.0000
7.250 1.1708 0.01519 0.00895 -0.0757 0.0085 1.0000
7.500 1.1917 0.01573 0.00955 -0.0746 0.0081 1.0000
7.750 1.2107 0.01641 0.01030 -0.0731 0.0075 1.0000
8.000 1.2279 0.01724 0.01120 -0.0714 0.0070 1.0000
8.250 1.2459 0.01793 0.01194 -0.0699 0.0065 1.0000
8.500 1.2635 0.01862 0.01267 -0.0684 0.0062 1.0000
8.750 1.2775 0.01957 0.01367 -0.0664 0.0058 1.0000
9.000 1.2861 0.02096 0.01515 -0.0635 0.0056 1.0000
9.250 1.2895 0.02292 0.01721 -0.0598 0.0054 1.0000
9.500 1.2960 0.02596 0.02039 -0.0569 0.0052 1.0000
9.750 1.3072 0.02656 0.02110 -0.0544 0.0051 1.0000
10.000 1.3184 0.02733 0.02196 -0.0520 0.0050 1.0000
10.250 1.3293 0.02908 0.02385 -0.0498 0.0049 1.0000
10.500 1.3390 0.03026 0.02514 -0.0474 0.0046 1.0000
10.750 1.3478 0.03213 0.02717 -0.0451 0.0043 1.0000
11.000 1.3557 0.03510 0.03036 -0.0429 0.0043 1.0000
11.250 1.3573 0.03880 0.03434 -0.0402 0.0043 1.0000
11.500 1.3503 0.04288 0.03871 -0.0370 0.0045 1.0000
11.750 1.3362 0.04712 0.04320 -0.0339 0.0048 1.0000
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Polar data table (+)
Polar graphs
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