GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 100,000 Max Cl/Cd: 63.4 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe450-il-100000.txt Download as CSV file: xf-goe450-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3483 0.10818 0.10349 -0.0317 1.0000 0.0726
-8.000 -0.3696 0.10830 0.10374 -0.0292 1.0000 0.0729
-7.750 -0.3861 0.10796 0.10351 -0.0294 1.0000 0.0732
-7.500 -0.3967 0.10705 0.10267 -0.0319 1.0000 0.0734
-7.250 -0.3936 0.10142 0.09708 -0.0269 1.0000 0.0744
-7.000 -0.3868 0.09762 0.09330 -0.0219 1.0000 0.0762
-6.750 -0.3889 0.09541 0.09114 -0.0200 1.0000 0.0778
-6.500 -0.3927 0.09339 0.08917 -0.0189 1.0000 0.0795
-6.250 -0.3961 0.09133 0.08715 -0.0187 1.0000 0.0816
-6.000 -0.3977 0.08921 0.08507 -0.0203 1.0000 0.0844
-5.750 -0.3822 0.08767 0.08336 -0.0371 1.0000 0.0878
-5.500 -0.3809 0.08251 0.07836 -0.0298 0.9980 0.0895
-5.250 -0.3575 0.07885 0.07468 -0.0308 0.9933 0.0939
-5.000 -0.2990 0.07309 0.06861 -0.0505 0.9849 0.1034
-4.750 -0.2828 0.06946 0.06506 -0.0489 0.9794 0.1062
-4.500 -0.2285 0.06480 0.06006 -0.0630 0.9723 0.1186
-4.250 -0.1885 0.06249 0.05747 -0.0699 0.9644 0.1328
-4.000 -0.1696 0.05778 0.05295 -0.0694 0.9595 0.1360
-3.750 -0.1295 0.05447 0.04943 -0.0759 0.9528 0.1502
-3.500 -0.0929 0.05156 0.04636 -0.0806 0.9459 0.1652
-3.250 -0.0526 0.04852 0.04324 -0.0850 0.9419 0.1819
-3.000 -0.0288 0.04646 0.04115 -0.0860 0.9327 0.1994
-2.000 0.1819 0.03323 0.02528 -0.1084 0.9128 0.1176
-1.750 0.2129 0.03080 0.02279 -0.1096 0.9048 0.1115
-1.500 0.2599 0.02913 0.02046 -0.1123 0.8998 0.1012
-1.250 0.3017 0.02768 0.01877 -0.1148 0.8945 0.0992
-1.000 0.3360 0.02673 0.01763 -0.1157 0.8862 0.0987
-0.750 0.3841 0.02578 0.01646 -0.1189 0.8825 0.1023
-0.500 0.4110 0.02504 0.01579 -0.1188 0.8724 0.1060
-0.250 0.4574 0.02400 0.01481 -0.1217 0.8684 0.1117
0.000 0.4853 0.02360 0.01441 -0.1215 0.8587 0.1189
0.250 0.5275 0.02265 0.01357 -0.1235 0.8539 0.1452
0.500 0.5572 0.02027 0.01323 -0.1231 0.8465 1.0000
0.750 0.5933 0.02007 0.01277 -0.1239 0.8395 1.0000
1.000 0.6211 0.02014 0.01270 -0.1236 0.8298 1.0000
1.250 0.6579 0.01983 0.01225 -0.1246 0.8237 1.0000
1.500 0.6837 0.01995 0.01229 -0.1239 0.8132 1.0000
1.750 0.7211 0.01955 0.01180 -0.1249 0.8077 1.0000
2.000 0.7455 0.01971 0.01192 -0.1240 0.7963 1.0000
2.250 0.7763 0.01958 0.01174 -0.1240 0.7880 1.0000
2.500 0.8072 0.01942 0.01155 -0.1239 0.7793 1.0000
2.750 0.8332 0.01952 0.01164 -0.1233 0.7683 1.0000
3.000 0.8692 0.01911 0.01119 -0.1239 0.7618 1.0000
3.250 0.8935 0.01929 0.01139 -0.1230 0.7494 1.0000
3.500 0.9197 0.01940 0.01152 -0.1223 0.7378 1.0000
3.750 0.9490 0.01937 0.01150 -0.1220 0.7276 1.0000
4.000 0.9801 0.01922 0.01133 -0.1219 0.7174 1.0000
4.250 1.0057 0.01936 0.01152 -0.1211 0.7041 1.0000
4.500 1.0317 0.01948 0.01166 -0.1204 0.6907 1.0000
4.750 1.0582 0.01958 0.01179 -0.1196 0.6770 1.0000
5.000 1.0846 0.01970 0.01196 -0.1189 0.6631 1.0000
5.250 1.1109 0.01983 0.01212 -0.1182 0.6489 1.0000
5.500 1.1366 0.01987 0.01218 -0.1172 0.6326 1.0000
5.750 1.1621 0.01982 0.01214 -0.1160 0.6144 1.0000
6.000 1.1881 0.01968 0.01193 -0.1148 0.5949 1.0000
6.250 1.2080 0.01979 0.01213 -0.1129 0.5731 1.0000
6.500 1.2304 0.01986 0.01222 -0.1114 0.5529 1.0000
6.750 1.2527 0.01998 0.01240 -0.1100 0.5334 1.0000
7.000 1.2710 0.02015 0.01266 -0.1079 0.5093 1.0000
7.250 1.2889 0.02033 0.01287 -0.1058 0.4830 1.0000
7.500 1.3041 0.02060 0.01313 -0.1032 0.4508 1.0000
7.750 1.3177 0.02106 0.01357 -0.1004 0.4161 1.0000
8.000 1.3250 0.02178 0.01417 -0.0967 0.3657 1.0000
8.250 1.3181 0.02333 0.01519 -0.0910 0.2625 1.0000
8.500 1.2972 0.02625 0.01711 -0.0842 0.1570 1.0000
8.750 1.2886 0.02874 0.01922 -0.0792 0.1149 1.0000
9.000 1.2870 0.03074 0.02108 -0.0754 0.1004 1.0000
9.250 1.2871 0.03268 0.02300 -0.0721 0.0918 1.0000
9.500 1.2853 0.03485 0.02509 -0.0688 0.0856 1.0000
9.750 1.2916 0.03663 0.02696 -0.0662 0.0805 1.0000
10.000 1.3002 0.03845 0.02879 -0.0640 0.0760 1.0000
10.250 1.3174 0.04043 0.03066 -0.0624 0.0711 1.0000
10.500 1.3357 0.04202 0.03241 -0.0610 0.0670 1.0000
10.750 1.3632 0.04389 0.03429 -0.0605 0.0635 1.0000
11.000 1.4059 0.04687 0.03728 -0.0621 0.0594 1.0000
11.250 1.4226 0.04908 0.03982 -0.0606 0.0573 1.0000
11.500 1.4442 0.05205 0.04311 -0.0598 0.0560 1.0000
11.750 1.4571 0.05513 0.04653 -0.0582 0.0551 1.0000
12.000 1.4633 0.05803 0.04971 -0.0561 0.0539 1.0000
12.250 1.4732 0.06096 0.05280 -0.0546 0.0523 1.0000
12.500 1.4761 0.06436 0.05644 -0.0527 0.0514 1.0000
12.750 1.4694 0.06791 0.06032 -0.0498 0.0515 1.0000
13.000 1.4551 0.07153 0.06431 -0.0467 0.0518 1.0000
13.250 1.4280 0.07553 0.06873 -0.0436 0.0524 1.0000
13.500 1.3997 0.08022 0.07380 -0.0415 0.0531 1.0000
13.750 1.3715 0.08554 0.07946 -0.0406 0.0538 1.0000
14.000 1.3427 0.09141 0.08564 -0.0408 0.0545 1.0000
14.250 1.3132 0.09790 0.09238 -0.0422 0.0552 1.0000
14.500 1.2832 0.10506 0.09978 -0.0447 0.0559 1.0000
14.750 1.2527 0.11304 0.10796 -0.0485 0.0566 1.0000
15.000 1.2226 0.12199 0.11708 -0.0535 0.0575 1.0000
15.250 1.1949 0.13171 0.12693 -0.0593 0.0585 1.0000
15.500 1.1754 0.14093 0.13621 -0.0645 0.0595 1.0000
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Polar data table (+)
Polar graphs
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