GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 200,000 Max Cl/Cd: 75.19 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe476-il-200000.txt Download as CSV file: xf-goe476-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1513 0.09904 0.09532 -0.0695 0.9713 0.0877
-9.250 -0.1280 0.09545 0.09172 -0.0739 0.9675 0.0899
-9.000 -0.1455 0.08895 0.08522 -0.0888 0.9545 0.0948
-8.750 -0.1093 0.08575 0.08199 -0.0884 0.9524 0.0956
-8.500 -0.0814 0.08327 0.07951 -0.0888 0.9442 0.0971
-8.250 -0.0535 0.07991 0.07612 -0.0934 0.9387 0.0996
-8.000 -0.0644 0.07176 0.06791 -0.1125 0.9207 0.1055
-7.750 -0.0280 0.06957 0.06570 -0.1113 0.9137 0.1065
-7.500 0.0056 0.06701 0.06309 -0.1136 0.9048 0.1081
-7.250 0.0251 0.06426 0.06028 -0.1168 0.8898 0.1112
-7.000 -0.0171 0.05753 0.05324 -0.1262 0.8639 0.1173
-6.750 0.0051 0.05602 0.05175 -0.1245 0.8521 0.1182
-6.500 -0.0627 0.03978 0.03456 -0.1266 0.8346 0.0951
-6.250 -0.0411 0.03856 0.03331 -0.1262 0.8254 0.0958
-6.000 -0.0345 0.03518 0.02967 -0.1244 0.8146 0.0924
-5.750 -0.0307 0.03124 0.02527 -0.1224 0.8057 0.0915
-5.500 -0.0241 0.02795 0.02153 -0.1198 0.7962 0.0911
-5.250 -0.0091 0.02542 0.01851 -0.1182 0.7892 0.0916
-5.000 0.0054 0.02376 0.01649 -0.1160 0.7803 0.0928
-4.750 0.0264 0.02252 0.01480 -0.1146 0.7737 0.0944
-4.500 0.0483 0.02143 0.01361 -0.1137 0.7668 0.0960
-4.250 0.0716 0.02084 0.01297 -0.1128 0.7597 0.0975
-4.000 0.0979 0.02025 0.01224 -0.1124 0.7539 0.0994
-3.750 0.1213 0.01971 0.01158 -0.1114 0.7474 0.1016
-3.500 0.1453 0.01922 0.01087 -0.1104 0.7407 0.1043
-3.250 0.1722 0.01854 0.01011 -0.1101 0.7354 0.1069
-3.000 0.1973 0.01826 0.00983 -0.1095 0.7298 0.1095
-2.750 0.2216 0.01796 0.00947 -0.1086 0.7235 0.1127
-2.500 0.2488 0.01768 0.00902 -0.1081 0.7180 0.1166
-2.250 0.2758 0.01731 0.00869 -0.1079 0.7129 0.1208
-2.000 0.2990 0.01714 0.00853 -0.1068 0.7063 0.1255
-1.750 0.3257 0.01682 0.00813 -0.1063 0.7008 0.1310
-1.500 0.3543 0.01667 0.00798 -0.1062 0.6962 0.1379
-1.250 0.3770 0.01650 0.00782 -0.1051 0.6902 0.1458
-1.000 0.4020 0.01636 0.00773 -0.1044 0.6844 0.1551
-0.750 0.4296 0.01612 0.00749 -0.1041 0.6795 0.1666
-0.500 0.4549 0.01601 0.00738 -0.1035 0.6742 0.1797
-0.250 0.4779 0.01595 0.00737 -0.1024 0.6678 0.1923
0.000 0.5044 0.01577 0.00722 -0.1020 0.6624 0.2054
0.250 0.5328 0.01569 0.00712 -0.1020 0.6578 0.2188
0.500 0.5537 0.01571 0.00721 -0.1005 0.6515 0.2311
0.750 0.5784 0.01560 0.00718 -0.0998 0.6459 0.2452
1.000 0.6061 0.01551 0.00712 -0.0996 0.6413 0.2620
1.250 0.6286 0.01549 0.00722 -0.0985 0.6360 0.2826
1.500 0.6493 0.01537 0.00730 -0.0970 0.6300 0.3167
1.750 0.8227 0.01384 0.00730 -0.1268 0.6222 1.0000
2.000 0.8422 0.01403 0.00745 -0.1251 0.6153 1.0000
2.250 0.8641 0.01416 0.00752 -0.1238 0.6089 1.0000
2.500 0.8901 0.01428 0.00751 -0.1232 0.6037 1.0000
2.750 0.9103 0.01450 0.00773 -0.1217 0.5979 1.0000
3.000 0.9309 0.01468 0.00790 -0.1201 0.5919 1.0000
3.250 0.9555 0.01482 0.00796 -0.1194 0.5869 1.0000
3.500 0.9796 0.01501 0.00808 -0.1185 0.5817 1.0000
3.750 0.9970 0.01520 0.00831 -0.1164 0.5751 1.0000
4.000 1.0203 0.01534 0.00841 -0.1154 0.5698 1.0000
4.250 1.0471 0.01550 0.00848 -0.1150 0.5656 1.0000
4.500 1.0634 0.01574 0.00879 -0.1128 0.5595 1.0000
4.750 1.0840 0.01588 0.00893 -0.1112 0.5535 1.0000
5.000 1.1095 0.01597 0.00894 -0.1106 0.5485 1.0000
5.250 1.1276 0.01618 0.00919 -0.1086 0.5425 1.0000
5.500 1.1464 0.01631 0.00934 -0.1068 0.5360 1.0000
5.750 1.1709 0.01639 0.00937 -0.1060 0.5309 1.0000
6.000 1.1891 0.01660 0.00962 -0.1040 0.5250 1.0000
6.250 1.2067 0.01675 0.00981 -0.1020 0.5184 1.0000
6.500 1.2304 0.01681 0.00980 -0.1010 0.5126 1.0000
6.750 1.2454 0.01701 0.01008 -0.0985 0.5057 1.0000
7.000 1.2629 0.01710 0.01017 -0.0964 0.4983 1.0000
7.250 1.2823 0.01721 0.01026 -0.0946 0.4912 1.0000
7.500 1.2946 0.01736 0.01046 -0.0916 0.4825 1.0000
7.750 1.3128 0.01746 0.01051 -0.0896 0.4744 1.0000
8.000 1.3224 0.01765 0.01077 -0.0861 0.4651 1.0000
8.250 1.3383 0.01783 0.01090 -0.0838 0.4566 1.0000
8.500 1.3463 0.01807 0.01120 -0.0800 0.4468 1.0000
8.750 1.3554 0.01831 0.01143 -0.0765 0.4373 1.0000
9.000 1.3605 0.01857 0.01167 -0.0722 0.4267 1.0000
9.250 1.3635 0.01891 0.01206 -0.0677 0.4150 1.0000
9.500 1.3676 0.01932 0.01244 -0.0637 0.4020 1.0000
9.750 1.3710 0.01982 0.01292 -0.0597 0.3879 1.0000
10.000 1.3725 0.02047 0.01354 -0.0556 0.3723 1.0000
10.250 1.3725 0.02127 0.01434 -0.0516 0.3544 1.0000
10.500 1.3717 0.02226 0.01530 -0.0479 0.3345 1.0000
10.750 1.3696 0.02347 0.01643 -0.0443 0.3144 1.0000
11.000 1.3664 0.02491 0.01777 -0.0409 0.2961 1.0000
11.250 1.3643 0.02646 0.01923 -0.0379 0.2814 1.0000
11.500 1.3638 0.02806 0.02074 -0.0353 0.2693 1.0000
11.750 1.3644 0.02967 0.02227 -0.0330 0.2593 1.0000
12.000 1.3686 0.03115 0.02374 -0.0311 0.2500 1.0000
12.250 1.3717 0.03272 0.02522 -0.0292 0.2423 1.0000
12.500 1.3779 0.03416 0.02673 -0.0277 0.2346 1.0000
12.750 1.3829 0.03568 0.02819 -0.0261 0.2276 1.0000
13.000 1.3895 0.03715 0.02970 -0.0247 0.2210 1.0000
13.250 1.3949 0.03872 0.03130 -0.0234 0.2144 1.0000
13.500 1.4020 0.04018 0.03269 -0.0221 0.2082 1.0000
13.750 1.4061 0.04196 0.03461 -0.0210 0.2019 1.0000
14.000 1.4107 0.04368 0.03630 -0.0199 0.1956 1.0000
14.250 1.4146 0.04555 0.03825 -0.0189 0.1893 1.0000
14.500 1.4162 0.04769 0.04046 -0.0181 0.1825 1.0000
14.750 1.4182 0.04979 0.04257 -0.0172 0.1760 1.0000
15.000 1.4180 0.05226 0.04516 -0.0166 0.1686 1.0000
15.250 1.4170 0.05479 0.04768 -0.0160 0.1616 1.0000
15.500 1.4145 0.05766 0.05064 -0.0156 0.1533 1.0000
15.750 1.4113 0.06061 0.05361 -0.0152 0.1452 1.0000
16.000 1.4066 0.06376 0.05674 -0.0149 0.1373 1.0000
16.250 1.4042 0.06675 0.05978 -0.0146 0.1296 1.0000
16.500 1.4003 0.06981 0.06273 -0.0143 0.1232 1.0000
16.750 1.3997 0.07270 0.06573 -0.0141 0.1171 1.0000
17.000 1.3996 0.07534 0.06828 -0.0138 0.1126 1.0000
17.250 1.4021 0.07779 0.07081 -0.0136 0.1087 1.0000
17.500 1.4043 0.08031 0.07337 -0.0135 0.1051 1.0000
17.750 1.4086 0.08243 0.07544 -0.0132 0.1021 1.0000
18.000 1.4145 0.08438 0.07742 -0.0128 0.0995 1.0000
18.250 1.4171 0.08693 0.08009 -0.0128 0.0968 1.0000
18.500 1.4210 0.08926 0.08247 -0.0128 0.0945 1.0000
18.750 1.4257 0.09140 0.08458 -0.0128 0.0921 1.0000
19.000 1.4314 0.09335 0.08655 -0.0126 0.0898 1.0000
19.250 1.4298 0.09662 0.08997 -0.0132 0.0876 1.0000
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