GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 384 AIRFOIL (goe384-il) Reynolds number: 200,000 Max Cl/Cd: 63.43 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe384-il-200000.txt Download as CSV file: xf-goe384-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 384 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
------ -------- --------- --------- -------- -------- --------
-10.500 0.0117 0.10430 0.10006 -0.0881 0.7950 0.0745
-10.250 0.0200 0.10170 0.09744 -0.0891 0.7869 0.0761
-10.000 -0.0153 0.09652 0.09225 -0.0995 0.7804 0.0800
-9.750 0.0016 0.09351 0.08916 -0.0976 0.7748 0.0806
-9.500 0.0219 0.09149 0.08712 -0.0962 0.7667 0.0813
-9.250 0.0360 0.08941 0.08498 -0.0958 0.7602 0.0824
-9.000 0.0454 0.08702 0.08254 -0.0965 0.7547 0.0841
-8.750 -0.0175 0.07717 0.07274 -0.1166 0.7497 0.0892
-8.500 0.0178 0.07647 0.07203 -0.1099 0.7442 0.0897
-8.250 0.0373 0.07500 0.07048 -0.1074 0.7396 0.0904
-8.000 0.0522 0.07314 0.06861 -0.1069 0.7342 0.0914
-7.750 0.0619 0.07074 0.06620 -0.1079 0.7287 0.0930
-7.500 0.0039 0.05997 0.05505 -0.1252 0.7253 0.0997
-7.250 0.0276 0.05784 0.05297 -0.1240 0.7211 0.1005
-7.000 0.0475 0.05649 0.05168 -0.1230 0.7160 0.1015
-6.750 0.0638 0.05487 0.05006 -0.1228 0.7113 0.1032
-6.500 0.0522 0.04936 0.04394 -0.1273 0.7080 0.1116
-6.250 0.0738 0.04707 0.04171 -0.1271 0.7046 0.1127
-6.000 0.0936 0.04538 0.04001 -0.1270 0.7011 0.1142
-5.750 0.0860 0.03564 0.02879 -0.1269 0.6983 0.0895
-5.500 0.1097 0.03354 0.02678 -0.1270 0.6940 0.0878
-5.250 0.1306 0.03127 0.02428 -0.1267 0.6902 0.0861
-5.000 0.1512 0.02842 0.02092 -0.1260 0.6869 0.0829
-4.750 0.1751 0.02662 0.01869 -0.1255 0.6836 0.0822
-4.500 0.1993 0.02568 0.01764 -0.1251 0.6795 0.0831
-4.250 0.2248 0.02491 0.01674 -0.1249 0.6752 0.0847
-4.000 0.2515 0.02406 0.01566 -0.1247 0.6711 0.0862
-3.750 0.2796 0.02325 0.01457 -0.1246 0.6673 0.0873
-3.500 0.3059 0.02271 0.01384 -0.1243 0.6630 0.0886
-3.250 0.3315 0.02195 0.01305 -0.1241 0.6583 0.0905
-3.000 0.3588 0.02150 0.01259 -0.1241 0.6539 0.0930
-2.750 0.3877 0.02108 0.01206 -0.1242 0.6498 0.0956
-2.500 0.4155 0.02079 0.01164 -0.1241 0.6454 0.0980
-2.250 0.4404 0.02035 0.01121 -0.1237 0.6399 0.1006
-2.000 0.4674 0.01994 0.01084 -0.1236 0.6347 0.1043
-1.750 0.4967 0.01967 0.01047 -0.1237 0.6302 0.1085
-1.500 0.5224 0.01940 0.01020 -0.1234 0.6251 0.1122
-1.250 0.5466 0.01909 0.01001 -0.1229 0.6193 0.1176
-1.000 0.5741 0.01885 0.00972 -0.1228 0.6139 0.1243
-0.750 0.6029 0.01853 0.00938 -0.1230 0.6092 0.1337
-0.500 0.6243 0.01829 0.00930 -0.1220 0.6025 0.1459
-0.250 0.6499 0.01798 0.00909 -0.1217 0.5962 0.1713
0.000 0.6738 0.01698 0.00896 -0.1215 0.5913 0.4124
0.250 0.6832 0.01599 0.00932 -0.1173 0.5853 0.7860
0.500 0.7431 0.01595 0.00944 -0.1226 0.5776 0.9693
0.750 0.8188 0.01600 0.00919 -0.1322 0.5712 1.0000
1.000 0.8329 0.01612 0.00933 -0.1299 0.5633 1.0000
1.250 0.8540 0.01614 0.00922 -0.1287 0.5569 1.0000
1.500 0.8776 0.01620 0.00911 -0.1280 0.5516 1.0000
1.750 0.8930 0.01634 0.00926 -0.1259 0.5436 1.0000
2.000 0.9152 0.01638 0.00917 -0.1250 0.5378 1.0000
2.250 0.9363 0.01650 0.00920 -0.1238 0.5319 1.0000
2.500 0.9545 0.01663 0.00930 -0.1222 0.5246 1.0000
2.750 0.9782 0.01668 0.00921 -0.1215 0.5192 1.0000
3.000 0.9977 0.01687 0.00936 -0.1202 0.5126 1.0000
3.250 1.0182 0.01702 0.00946 -0.1191 0.5062 1.0000
3.500 1.0436 0.01713 0.00942 -0.1188 0.5015 1.0000
3.750 1.0629 0.01741 0.00969 -0.1175 0.4955 1.0000
4.000 1.0841 0.01763 0.00987 -0.1165 0.4899 1.0000
4.250 1.1095 0.01780 0.00991 -0.1163 0.4853 1.0000
4.500 1.1305 0.01812 0.01019 -0.1154 0.4801 1.0000
4.750 1.1504 0.01842 0.01047 -0.1143 0.4748 1.0000
5.000 1.1745 0.01866 0.01063 -0.1140 0.4703 1.0000
5.250 1.2020 0.01897 0.01081 -0.1142 0.4662 1.0000
5.500 1.2192 0.01940 0.01129 -0.1128 0.4617 1.0000
5.750 1.2405 0.01977 0.01164 -0.1120 0.4574 1.0000
6.000 1.2655 0.02010 0.01189 -0.1119 0.4537 1.0000
6.250 1.2978 0.02046 0.01212 -0.1131 0.4500 1.0000
6.500 1.3110 0.02097 0.01272 -0.1111 0.4461 1.0000
6.750 1.3291 0.02142 0.01319 -0.1099 0.4421 1.0000
7.000 1.3519 0.02182 0.01356 -0.1095 0.4385 1.0000
7.250 1.3819 0.02222 0.01387 -0.1104 0.4353 1.0000
7.500 1.4096 0.02275 0.01436 -0.1109 0.4321 1.0000
7.750 1.4195 0.02335 0.01507 -0.1084 0.4290 1.0000
8.000 1.4347 0.02392 0.01570 -0.1069 0.4257 1.0000
8.250 1.4554 0.02442 0.01620 -0.1062 0.4225 1.0000
8.500 1.4832 0.02483 0.01657 -0.1068 0.4194 1.0000
8.750 1.5245 0.02532 0.01694 -0.1097 0.4163 1.0000
9.000 1.5276 0.02609 0.01786 -0.1063 0.4137 1.0000
9.250 1.5343 0.02691 0.01879 -0.1036 0.4108 1.0000
9.500 1.5473 0.02766 0.01962 -0.1020 0.4079 1.0000
9.750 1.5667 0.02828 0.02026 -0.1014 0.4051 1.0000
10.000 1.5947 0.02871 0.02066 -0.1020 0.4023 1.0000
10.250 1.6360 0.02909 0.02096 -0.1047 0.3995 1.0000
10.500 1.6402 0.03014 0.02213 -0.1019 0.3970 1.0000
10.750 1.6351 0.03140 0.02358 -0.0981 0.3943 1.0000
11.000 1.6364 0.03260 0.02489 -0.0952 0.3912 1.0000
11.250 1.6496 0.03334 0.02568 -0.0940 0.3878 1.0000
11.500 1.6842 0.03331 0.02555 -0.0953 0.3842 1.0000
11.750 1.7116 0.03381 0.02603 -0.0959 0.3805 1.0000
12.000 1.6853 0.03592 0.02837 -0.0900 0.3769 1.0000
12.250 1.6770 0.03767 0.03026 -0.0867 0.3734 1.0000
12.500 1.6884 0.03861 0.03126 -0.0856 0.3702 1.0000
12.750 1.7172 0.03875 0.03138 -0.0862 0.3675 1.0000
13.000 1.7636 0.03838 0.03092 -0.0887 0.3649 1.0000
13.250 1.7365 0.04121 0.03399 -0.0838 0.3619 1.0000
13.500 1.6976 0.04512 0.03815 -0.0786 0.3581 1.0000
13.750 1.6854 0.04775 0.04091 -0.0761 0.3545 1.0000
14.000 1.7058 0.04822 0.04139 -0.0760 0.3518 1.0000
14.250 1.7515 0.04702 0.04012 -0.0776 0.3494 1.0000
14.500 1.7567 0.04862 0.04180 -0.0764 0.3462 1.0000
14.750 1.5924 0.06460 0.05832 -0.0673 0.3378 1.0000
15.000 1.6253 0.06362 0.05732 -0.0676 0.3355 1.0000
15.250 1.6920 0.05940 0.05301 -0.0692 0.3337 1.0000
15.500 1.7743 0.05438 0.04779 -0.0719 0.3310 1.0000
15.750 1.4568 0.09092 0.08508 -0.0636 0.3141 1.0000
16.000 1.5109 0.08680 0.08095 -0.0637 0.3138 1.0000
16.250 1.5796 0.08103 0.07515 -0.0641 0.3135 1.0000
16.500 1.4443 0.10104 0.09537 -0.0638 0.2992 1.0000
16.750 1.4957 0.09691 0.09125 -0.0636 0.2989 1.0000
17.000 1.5597 0.09128 0.08560 -0.0636 0.2985 1.0000
17.500 1.5011 0.10459 0.09909 -0.0643 0.2843 1.0000
17.750 1.5826 0.09639 0.09084 -0.0640 0.2846 1.0000
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