GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 100,000 Max Cl/Cd: 43.23 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe449-il-100000-n5.txt Download as CSV file: xf-goe449-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1240 0.09710 0.09145 -0.1065 0.9337 0.0574
-10.750 -0.1244 0.09168 0.08602 -0.1105 0.9294 0.0577
-10.500 -0.1242 0.08557 0.07990 -0.1157 0.9262 0.0578
-10.250 -0.1322 0.07925 0.07357 -0.1202 0.9209 0.0577
-9.750 -0.2576 0.05451 0.04849 -0.1358 0.8963 0.0567
-9.500 -0.2948 0.04960 0.04322 -0.1336 0.8876 0.0568
-9.250 -0.3225 0.04681 0.04014 -0.1286 0.8770 0.0570
-9.000 -0.3295 0.04264 0.03540 -0.1273 0.8725 0.0579
-8.750 -0.3512 0.04104 0.03347 -0.1206 0.8615 0.0585
-8.500 -0.3318 0.03935 0.03159 -0.1205 0.8576 0.0596
-8.250 -0.3033 0.03793 0.03004 -0.1217 0.8549 0.0609
-8.000 -0.3074 0.03718 0.02914 -0.1166 0.8444 0.0616
-7.750 -0.2866 0.03545 0.02713 -0.1163 0.8402 0.0631
-7.500 -0.2615 0.03348 0.02477 -0.1166 0.8375 0.0647
-7.250 -0.2637 0.03272 0.02376 -0.1116 0.8286 0.0657
-7.000 -0.2420 0.03171 0.02263 -0.1109 0.8242 0.0673
-6.750 -0.2128 0.03091 0.02177 -0.1114 0.8214 0.0695
-6.500 -0.1812 0.02979 0.02042 -0.1124 0.8193 0.0725
-6.250 -0.1832 0.02952 0.01999 -0.1071 0.8098 0.0740
-6.000 -0.1574 0.02868 0.01910 -0.1069 0.8059 0.0762
-5.750 -0.1257 0.02787 0.01824 -0.1077 0.8033 0.0793
-5.500 -0.0909 0.02697 0.01708 -0.1090 0.8012 0.0841
-5.250 -0.0939 0.02701 0.01718 -0.1035 0.7911 0.0859
-5.000 -0.0655 0.02642 0.01658 -0.1037 0.7875 0.0905
-4.750 -0.0318 0.02567 0.01569 -0.1047 0.7850 0.0962
-4.500 -0.0168 0.02545 0.01551 -0.1025 0.7788 0.1006
-4.250 -0.0009 0.02521 0.01519 -0.1002 0.7720 0.1060
-4.000 0.0308 0.02461 0.01460 -0.1009 0.7687 0.1131
-3.750 0.0668 0.02402 0.01392 -0.1023 0.7663 0.1221
-3.500 0.0673 0.02412 0.01408 -0.0974 0.7568 0.1263
-3.250 0.0953 0.02374 0.01365 -0.0974 0.7525 0.1357
-3.000 0.1296 0.02316 0.01311 -0.0985 0.7496 0.1460
-2.750 0.1432 0.02306 0.01300 -0.0958 0.7424 0.1543
-2.500 0.1611 0.02284 0.01282 -0.0940 0.7358 0.1646
-2.250 0.1949 0.02233 0.01235 -0.0949 0.7325 0.1803
-2.000 0.2319 0.02179 0.01185 -0.0965 0.7300 0.2018
-1.750 0.2268 0.02207 0.01221 -0.0905 0.7191 0.2135
-1.500 0.2592 0.02161 0.01183 -0.0912 0.7153 0.2466
-1.250 0.2973 0.02099 0.01137 -0.0930 0.7125 0.2992
-1.000 0.2925 0.02120 0.01176 -0.0872 0.7018 0.3321
-0.750 0.3219 0.02056 0.01153 -0.0874 0.6978 0.4439
-0.500 0.3564 0.01969 0.01132 -0.0881 0.6951 0.6080
-0.250 0.3582 0.01989 0.01196 -0.0828 0.6853 0.7463
0.000 0.4382 0.01987 0.01211 -0.0916 0.6824 0.8990
0.250 0.5122 0.01986 0.01195 -0.1000 0.6795 0.9498
0.500 0.5995 0.01976 0.01166 -0.1113 0.6770 0.9761
0.750 0.6573 0.02014 0.01196 -0.1179 0.6688 0.9987
1.000 0.6814 0.02009 0.01180 -0.1174 0.6631 1.0000
1.250 0.6979 0.02011 0.01172 -0.1154 0.6574 1.0000
1.500 0.6951 0.02040 0.01198 -0.1099 0.6492 1.0000
1.750 0.7217 0.02030 0.01175 -0.1097 0.6444 1.0000
2.000 0.7196 0.02062 0.01203 -0.1043 0.6368 1.0000
2.250 0.7312 0.02074 0.01208 -0.1014 0.6306 1.0000
2.500 0.7650 0.02062 0.01184 -0.1024 0.6265 1.0000
2.750 0.7525 0.02111 0.01232 -0.0952 0.6183 1.0000
3.000 0.7734 0.02117 0.01230 -0.0939 0.6128 1.0000
3.250 0.8105 0.02103 0.01206 -0.0955 0.6091 1.0000
3.500 0.7978 0.02167 0.01270 -0.0885 0.6007 1.0000
3.750 0.8228 0.02171 0.01267 -0.0879 0.5956 1.0000
4.000 0.8557 0.02165 0.01251 -0.0888 0.5914 1.0000
4.250 0.8506 0.02230 0.01318 -0.0832 0.5834 1.0000
4.500 0.8777 0.02233 0.01316 -0.0831 0.5783 1.0000
4.750 0.9046 0.02239 0.01315 -0.0829 0.5732 1.0000
5.000 0.9071 0.02299 0.01377 -0.0788 0.5657 1.0000
5.250 0.9376 0.02295 0.01366 -0.0792 0.5602 1.0000
5.500 0.9524 0.02330 0.01400 -0.0771 0.5537 1.0000
5.750 0.9649 0.02372 0.01440 -0.0748 0.5465 1.0000
6.000 1.0001 0.02359 0.01420 -0.0759 0.5413 1.0000
6.250 1.0020 0.02433 0.01498 -0.0720 0.5338 1.0000
6.500 1.0213 0.02464 0.01528 -0.0707 0.5275 1.0000
6.750 1.0586 0.02449 0.01506 -0.0722 0.5227 1.0000
7.000 1.0526 0.02552 0.01619 -0.0673 0.5150 1.0000
7.250 1.0737 0.02580 0.01646 -0.0664 0.5088 1.0000
7.500 1.1025 0.02588 0.01651 -0.0666 0.5035 1.0000
7.750 1.0978 0.02698 0.01771 -0.0622 0.4954 1.0000
8.000 1.1223 0.02715 0.01787 -0.0618 0.4895 1.0000
8.250 1.1318 0.02785 0.01861 -0.0594 0.4825 1.0000
8.500 1.1381 0.02867 0.01950 -0.0568 0.4747 1.0000
8.750 1.1699 0.02854 0.01932 -0.0573 0.4692 1.0000
9.000 1.1576 0.03017 0.02108 -0.0525 0.4601 1.0000
9.250 1.1798 0.03031 0.02120 -0.0518 0.4529 1.0000
9.500 1.1734 0.03180 0.02279 -0.0481 0.4432 1.0000
9.750 1.1945 0.03189 0.02284 -0.0472 0.4346 1.0000
10.000 1.1834 0.03375 0.02482 -0.0433 0.4234 1.0000
10.250 1.1926 0.03454 0.02560 -0.0415 0.4135 1.0000
10.500 1.1966 0.03570 0.02679 -0.0392 0.4032 1.0000
10.750 1.1970 0.03722 0.02838 -0.0369 0.3927 1.0000
11.000 1.2138 0.03766 0.02880 -0.0359 0.3846 1.0000
11.250 1.2109 0.03959 0.03082 -0.0336 0.3745 1.0000
11.500 1.2264 0.04017 0.03138 -0.0326 0.3665 1.0000
11.750 1.2265 0.04200 0.03329 -0.0307 0.3567 1.0000
12.000 1.2365 0.04307 0.03437 -0.0295 0.3480 1.0000
12.250 1.2419 0.04454 0.03588 -0.0281 0.3387 1.0000
12.500 1.2471 0.04610 0.03747 -0.0268 0.3295 1.0000
12.750 1.2569 0.04723 0.03859 -0.0256 0.3205 1.0000
13.000 1.2582 0.04925 0.04068 -0.0243 0.3114 1.0000
13.250 1.2707 0.05017 0.04156 -0.0234 0.3033 1.0000
13.500 1.2692 0.05256 0.04406 -0.0222 0.2943 1.0000
13.750 1.2820 0.05351 0.04496 -0.0214 0.2869 1.0000
14.000 1.2805 0.05603 0.04759 -0.0204 0.2786 1.0000
14.250 1.2910 0.05723 0.04878 -0.0196 0.2711 1.0000
14.500 1.2897 0.05981 0.05146 -0.0188 0.2629 1.0000
14.750 1.2973 0.06137 0.05301 -0.0181 0.2554 1.0000
15.000 1.2980 0.06381 0.05553 -0.0175 0.2479 1.0000
15.250 1.3022 0.06584 0.05760 -0.0169 0.2405 1.0000
15.500 1.3067 0.06788 0.05968 -0.0164 0.2336 1.0000
15.750 1.3052 0.07067 0.06255 -0.0160 0.2259 1.0000
16.000 1.3113 0.07251 0.06437 -0.0156 0.2190 1.0000
16.250 1.3060 0.07591 0.06789 -0.0154 0.2114 1.0000
16.750 1.3080 0.08116 0.07325 -0.0152 0.1987 1.0000
17.000 1.3104 0.08361 0.07575 -0.0152 0.1929 1.0000
17.250 1.3141 0.08594 0.07813 -0.0152 0.1877 1.0000
17.500 1.3093 0.08954 0.08187 -0.0155 0.1822 1.0000
17.750 1.3146 0.09165 0.08400 -0.0156 0.1774 1.0000
18.000 1.3155 0.09447 0.08690 -0.0158 0.1729 1.0000
18.250 1.3098 0.09829 0.09087 -0.0165 0.1681 1.0000
18.500 1.3130 0.10075 0.09338 -0.0168 0.1639 1.0000
18.750 1.3159 0.10328 0.09596 -0.0172 0.1597 1.0000
19.000 1.3054 0.10794 0.10080 -0.0184 0.1552 1.0000
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