GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 500,000 Max Cl/Cd: 97.01 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe414-il-500000-n5.txt Download as CSV file: xf-goe414-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5531 0.06504 0.06246 -0.0891 0.9811 0.0093
-12.500 -0.6606 0.03520 0.03199 -0.1204 0.9538 0.0085
-12.250 -0.6619 0.03060 0.02708 -0.1233 0.9445 0.0086
-12.000 -0.6541 0.02797 0.02423 -0.1237 0.9365 0.0089
-11.750 -0.6409 0.02614 0.02220 -0.1236 0.9292 0.0091
-11.500 -0.6245 0.02468 0.02058 -0.1234 0.9223 0.0094
-11.250 -0.6059 0.02345 0.01917 -0.1231 0.9169 0.0097
-11.000 -0.5861 0.02237 0.01794 -0.1228 0.9107 0.0101
-10.750 -0.5654 0.02135 0.01675 -0.1225 0.9056 0.0106
-10.500 -0.5438 0.02042 0.01565 -0.1222 0.9004 0.0111
-10.250 -0.5219 0.01952 0.01458 -0.1218 0.8946 0.0115
-10.000 -0.4998 0.01860 0.01354 -0.1214 0.8892 0.0122
-9.750 -0.4762 0.01796 0.01281 -0.1211 0.8822 0.0128
-9.500 -0.4519 0.01737 0.01209 -0.1208 0.8758 0.0135
-9.250 -0.4274 0.01679 0.01139 -0.1206 0.8689 0.0143
-9.000 -0.4026 0.01623 0.01068 -0.1203 0.8624 0.0150
-8.750 -0.3778 0.01568 0.01005 -0.1200 0.8557 0.0160
-8.500 -0.3517 0.01535 0.00965 -0.1199 0.8488 0.0171
-8.250 -0.3255 0.01501 0.00922 -0.1198 0.8425 0.0184
-8.000 -0.2993 0.01465 0.00874 -0.1196 0.8362 0.0196
-7.750 -0.2732 0.01426 0.00823 -0.1194 0.8300 0.0205
-7.500 -0.2476 0.01378 0.00770 -0.1192 0.8224 0.0219
-7.250 -0.2212 0.01350 0.00732 -0.1191 0.8145 0.0233
-7.000 -0.1947 0.01321 0.00694 -0.1189 0.8058 0.0248
-6.750 -0.1679 0.01294 0.00656 -0.1188 0.7985 0.0260
-6.500 -0.1408 0.01273 0.00625 -0.1187 0.7908 0.0268
-6.250 -0.1153 0.01219 0.00562 -0.1184 0.7829 0.0288
-6.000 -0.0890 0.01187 0.00522 -0.1183 0.7735 0.0304
-5.750 -0.0623 0.01161 0.00487 -0.1181 0.7634 0.0320
-5.500 -0.0356 0.01138 0.00453 -0.1179 0.7525 0.0334
-5.250 -0.0090 0.01120 0.00423 -0.1177 0.7400 0.0346
-5.000 0.0174 0.01100 0.00392 -0.1174 0.7263 0.0363
-4.500 0.0703 0.01063 0.00339 -0.1169 0.6989 0.0418
-4.250 0.0968 0.01046 0.00319 -0.1167 0.6871 0.0488
-4.000 0.1233 0.01033 0.00306 -0.1165 0.6761 0.0653
-3.750 0.1500 0.01027 0.00295 -0.1163 0.6658 0.0753
-3.500 0.1771 0.01022 0.00284 -0.1162 0.6560 0.0814
-3.250 0.2041 0.01017 0.00274 -0.1161 0.6473 0.0870
-3.000 0.2311 0.01016 0.00265 -0.1160 0.6387 0.0908
-2.750 0.2583 0.01012 0.00256 -0.1159 0.6307 0.0945
-2.250 0.3123 0.01006 0.00243 -0.1157 0.6145 0.1063
-1.750 0.3663 0.01000 0.00232 -0.1155 0.5991 0.1201
-1.500 0.3930 0.00998 0.00228 -0.1153 0.5915 0.1300
-1.250 0.4202 0.00993 0.00225 -0.1153 0.5837 0.1434
-1.000 0.4466 0.00990 0.00223 -0.1151 0.5755 0.1632
-0.750 0.4733 0.00978 0.00222 -0.1151 0.5665 0.2016
-0.500 0.4994 0.00971 0.00225 -0.1149 0.5571 0.2489
-0.250 0.5257 0.00970 0.00227 -0.1147 0.5462 0.2791
0.000 0.5521 0.00972 0.00230 -0.1145 0.5341 0.3028
0.250 0.5780 0.00975 0.00234 -0.1143 0.5207 0.3266
0.500 0.6034 0.00981 0.00239 -0.1139 0.5052 0.3523
0.750 0.6282 0.00988 0.00245 -0.1135 0.4888 0.3797
1.000 0.6528 0.00997 0.00254 -0.1130 0.4739 0.4108
1.250 0.6774 0.00999 0.00263 -0.1126 0.4617 0.4610
1.500 0.6917 0.00912 0.00285 -0.1099 0.4535 0.8384
2.000 0.7756 0.00935 0.00315 -0.1163 0.4402 1.0000
2.250 0.8001 0.00948 0.00324 -0.1157 0.4360 1.0000
2.500 0.8244 0.00962 0.00335 -0.1152 0.4320 1.0000
2.750 0.8484 0.00978 0.00346 -0.1145 0.4278 1.0000
3.000 0.8727 0.00994 0.00359 -0.1139 0.4240 1.0000
3.250 0.8976 0.01007 0.00371 -0.1135 0.4203 1.0000
3.500 0.9222 0.01022 0.00384 -0.1130 0.4170 1.0000
3.750 0.9465 0.01039 0.00399 -0.1125 0.4136 1.0000
4.000 0.9704 0.01059 0.00415 -0.1118 0.4103 1.0000
4.250 0.9956 0.01072 0.00430 -0.1115 0.4076 1.0000
4.750 1.0453 0.01101 0.00463 -0.1107 0.4022 1.0000
5.000 1.0694 0.01120 0.00481 -0.1101 0.3990 1.0000
5.250 1.0924 0.01142 0.00501 -0.1094 0.3938 1.0000
5.500 1.1166 0.01157 0.00519 -0.1089 0.3869 1.0000
5.750 1.1386 0.01182 0.00540 -0.1080 0.3798 1.0000
6.000 1.1622 0.01198 0.00559 -0.1074 0.3708 1.0000
6.250 1.1836 0.01221 0.00581 -0.1064 0.3612 1.0000
6.500 1.2040 0.01245 0.00604 -0.1052 0.3504 1.0000
6.750 1.2233 0.01274 0.00629 -0.1039 0.3352 1.0000
7.000 1.2404 0.01314 0.00660 -0.1022 0.3097 1.0000
7.250 1.2458 0.01415 0.00728 -0.0986 0.2562 1.0000
7.500 1.2512 0.01526 0.00817 -0.0953 0.2181 1.0000
7.750 1.2570 0.01641 0.00909 -0.0922 0.1788 1.0000
8.000 1.2458 0.01859 0.01080 -0.0868 0.0979 1.0000
8.250 1.2351 0.02085 0.01271 -0.0819 0.0266 1.0000
8.500 1.2459 0.02185 0.01371 -0.0799 0.0183 1.0000
8.750 1.2584 0.02276 0.01466 -0.0783 0.0156 1.0000
9.000 1.2718 0.02364 0.01559 -0.0768 0.0141 1.0000
9.250 1.2849 0.02456 0.01659 -0.0754 0.0131 1.0000
9.500 1.2968 0.02558 0.01768 -0.0739 0.0123 1.0000
9.750 1.3070 0.02676 0.01892 -0.0723 0.0115 1.0000
10.000 1.3147 0.02816 0.02040 -0.0706 0.0108 1.0000
10.250 1.3225 0.02960 0.02192 -0.0690 0.0103 1.0000
10.500 1.3319 0.03095 0.02334 -0.0676 0.0099 1.0000
10.750 1.3399 0.03245 0.02491 -0.0663 0.0094 1.0000
11.000 1.3468 0.03409 0.02664 -0.0650 0.0089 1.0000
11.250 1.3525 0.03589 0.02851 -0.0637 0.0086 1.0000
11.500 1.3568 0.03787 0.03056 -0.0624 0.0083 1.0000
11.750 1.3600 0.04005 0.03282 -0.0613 0.0080 1.0000
12.000 1.3605 0.04258 0.03544 -0.0602 0.0078 1.0000
12.250 1.3575 0.04557 0.03853 -0.0591 0.0076 1.0000
12.500 1.3566 0.04846 0.04152 -0.0583 0.0074 1.0000
12.750 1.3573 0.05125 0.04440 -0.0577 0.0073 1.0000
13.000 1.3571 0.05420 0.04745 -0.0572 0.0071 1.0000
13.250 1.3561 0.05728 0.05063 -0.0567 0.0070 1.0000
13.500 1.3545 0.06050 0.05394 -0.0564 0.0068 1.0000
13.750 1.3528 0.06378 0.05733 -0.0562 0.0066 1.0000
14.000 1.3508 0.06716 0.06081 -0.0560 0.0064 1.0000
14.250 1.3494 0.07049 0.06421 -0.0560 0.0062 1.0000
14.500 1.3471 0.07398 0.06779 -0.0560 0.0061 1.0000
14.750 1.3452 0.07747 0.07136 -0.0561 0.0059 1.0000
15.000 1.3430 0.08106 0.07502 -0.0563 0.0058 1.0000
15.250 1.3404 0.08472 0.07876 -0.0566 0.0057 1.0000
15.500 1.3371 0.08849 0.08261 -0.0569 0.0056 1.0000
15.750 1.3333 0.09236 0.08655 -0.0573 0.0055 1.0000
16.000 1.3288 0.09632 0.09059 -0.0577 0.0054 1.0000
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