GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.73 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe412-il-1000000-n5.txt Download as CSV file: xf-goe412-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8071 0.03370 0.03093 -0.1212 0.9493 0.0185
-13.500 -0.8020 0.03161 0.02869 -0.1215 0.9436 0.0187
-13.250 -0.7895 0.03002 0.02699 -0.1218 0.9378 0.0188
-13.000 -0.7756 0.02866 0.02551 -0.1216 0.9321 0.0190
-12.750 -0.7601 0.02733 0.02405 -0.1215 0.9263 0.0193
-12.500 -0.7440 0.02604 0.02262 -0.1212 0.9187 0.0195
-12.250 -0.7263 0.02487 0.02131 -0.1209 0.9108 0.0197
-12.000 -0.7074 0.02386 0.02015 -0.1204 0.9004 0.0199
-11.750 -0.6875 0.02292 0.01906 -0.1200 0.8868 0.0202
-11.500 -0.6674 0.02204 0.01799 -0.1195 0.8705 0.0204
-11.250 -0.6465 0.02122 0.01699 -0.1190 0.8542 0.0206
-10.750 -0.6011 0.01988 0.01532 -0.1183 0.8291 0.0209
-10.500 -0.5769 0.01937 0.01467 -0.1181 0.8197 0.0210
-10.250 -0.5542 0.01854 0.01369 -0.1178 0.8111 0.0212
-10.000 -0.5322 0.01751 0.01251 -0.1174 0.8041 0.0215
-9.750 -0.5080 0.01683 0.01173 -0.1172 0.7973 0.0217
-9.500 -0.4832 0.01629 0.01110 -0.1170 0.7909 0.0219
-9.250 -0.4575 0.01580 0.01053 -0.1169 0.7856 0.0220
-9.000 -0.4316 0.01533 0.00999 -0.1168 0.7799 0.0222
-8.750 -0.4056 0.01493 0.00951 -0.1167 0.7743 0.0224
-8.500 -0.3790 0.01455 0.00907 -0.1167 0.7696 0.0227
-8.250 -0.3523 0.01417 0.00862 -0.1166 0.7645 0.0229
-8.000 -0.3259 0.01376 0.00813 -0.1165 0.7594 0.0231
-7.750 -0.2992 0.01337 0.00766 -0.1165 0.7548 0.0233
-7.500 -0.2722 0.01298 0.00721 -0.1164 0.7502 0.0236
-7.250 -0.2452 0.01262 0.00678 -0.1164 0.7453 0.0238
-7.000 -0.2182 0.01230 0.00637 -0.1163 0.7405 0.0240
-6.750 -0.1907 0.01197 0.00599 -0.1163 0.7363 0.0242
-6.500 -0.1632 0.01166 0.00563 -0.1164 0.7318 0.0244
-6.250 -0.1357 0.01138 0.00529 -0.1163 0.7270 0.0246
-6.000 -0.1081 0.01113 0.00498 -0.1163 0.7226 0.0248
-5.750 -0.0801 0.01088 0.00469 -0.1164 0.7184 0.0250
-5.500 -0.0522 0.01066 0.00443 -0.1165 0.7138 0.0252
-5.250 -0.0242 0.01050 0.00421 -0.1165 0.7091 0.0254
-5.000 0.0036 0.01025 0.00392 -0.1165 0.7050 0.0257
-4.750 0.0314 0.00994 0.00358 -0.1166 0.7006 0.0261
-4.500 0.0593 0.00971 0.00331 -0.1166 0.6958 0.0265
-4.250 0.0872 0.00954 0.00309 -0.1166 0.6913 0.0269
-4.000 0.1156 0.00937 0.00291 -0.1168 0.6873 0.0272
-3.750 0.1440 0.00922 0.00274 -0.1169 0.6826 0.0276
-3.500 0.1722 0.00909 0.00258 -0.1169 0.6778 0.0280
-3.250 0.2004 0.00899 0.00244 -0.1170 0.6735 0.0285
-3.000 0.2290 0.00887 0.00231 -0.1172 0.6688 0.0289
-2.750 0.2572 0.00878 0.00219 -0.1172 0.6624 0.0294
-2.500 0.2854 0.00871 0.00209 -0.1173 0.6559 0.0299
-2.250 0.3138 0.00864 0.00199 -0.1174 0.6495 0.0304
-2.000 0.3419 0.00859 0.00191 -0.1174 0.6439 0.0310
-1.750 0.3703 0.00851 0.00182 -0.1175 0.6378 0.0326
-1.500 0.3981 0.00847 0.00175 -0.1175 0.6284 0.0346
-1.250 0.4259 0.00844 0.00169 -0.1175 0.6173 0.0378
-1.000 0.4531 0.00832 0.00165 -0.1175 0.6067 0.0662
-0.750 0.4810 0.00830 0.00162 -0.1175 0.5979 0.0757
-0.500 0.5090 0.00829 0.00161 -0.1176 0.5902 0.0833
-0.250 0.5367 0.00829 0.00161 -0.1176 0.5814 0.0921
0.000 0.5644 0.00827 0.00162 -0.1176 0.5731 0.1080
0.250 0.5919 0.00826 0.00164 -0.1176 0.5641 0.1287
0.500 0.6197 0.00825 0.00166 -0.1177 0.5565 0.1450
0.750 0.6472 0.00826 0.00168 -0.1177 0.5482 0.1614
1.000 0.6745 0.00821 0.00172 -0.1177 0.5402 0.1972
1.250 0.7012 0.00817 0.00179 -0.1176 0.5304 0.2613
1.500 0.7284 0.00818 0.00186 -0.1176 0.5200 0.2954
1.750 0.7551 0.00821 0.00193 -0.1174 0.5086 0.3272
2.000 0.7811 0.00822 0.00202 -0.1173 0.4951 0.3810
2.250 0.8060 0.00806 0.00217 -0.1170 0.4801 0.5238
2.500 0.8306 0.00808 0.00230 -0.1165 0.4597 0.6077
2.750 0.8494 0.00770 0.00250 -0.1148 0.4390 0.8472
3.000 0.8894 0.00782 0.00274 -0.1175 0.4163 0.9968
3.250 0.9157 0.00807 0.00289 -0.1174 0.3968 1.0000
3.500 0.9385 0.00834 0.00305 -0.1165 0.3768 1.0000
3.750 0.9603 0.00868 0.00326 -0.1154 0.3542 1.0000
4.000 0.9820 0.00902 0.00347 -0.1144 0.3303 1.0000
4.250 1.0044 0.00933 0.00367 -0.1135 0.3119 1.0000
4.500 1.0273 0.00960 0.00387 -0.1127 0.2973 1.0000
4.750 1.0500 0.00988 0.00408 -0.1118 0.2832 1.0000
5.000 1.0719 0.01020 0.00431 -0.1109 0.2662 1.0000
5.250 1.0930 0.01056 0.00457 -0.1098 0.2478 1.0000
5.500 1.1126 0.01098 0.00487 -0.1084 0.2256 1.0000
5.750 1.1304 0.01147 0.00522 -0.1068 0.2008 1.0000
6.000 1.1492 0.01187 0.00554 -0.1053 0.1855 1.0000
6.250 1.1689 0.01216 0.00580 -0.1039 0.1786 1.0000
6.500 1.1879 0.01249 0.00610 -0.1024 0.1720 1.0000
6.750 1.2081 0.01278 0.00638 -0.1012 0.1674 1.0000
7.000 1.2275 0.01312 0.00670 -0.0999 0.1624 1.0000
7.250 1.2467 0.01348 0.00705 -0.0986 0.1576 1.0000
7.500 1.2669 0.01380 0.00737 -0.0974 0.1533 1.0000
7.750 1.2864 0.01416 0.00773 -0.0963 0.1484 1.0000
8.000 1.3053 0.01457 0.00812 -0.0950 0.1439 1.0000
8.250 1.3241 0.01498 0.00853 -0.0937 0.1399 1.0000
8.500 1.3444 0.01532 0.00889 -0.0928 0.1368 1.0000
8.750 1.3619 0.01581 0.00936 -0.0914 0.1293 1.0000
9.000 1.3786 0.01636 0.00988 -0.0900 0.1192 1.0000
9.500 1.3941 0.01851 0.01177 -0.0848 0.0767 1.0000
9.750 1.4078 0.01929 0.01255 -0.0831 0.0719 1.0000
10.000 1.4235 0.01996 0.01326 -0.0818 0.0684 1.0000
10.250 1.4379 0.02075 0.01405 -0.0803 0.0636 1.0000
10.500 1.4503 0.02167 0.01497 -0.0787 0.0581 1.0000
10.750 1.4597 0.02283 0.01607 -0.0769 0.0470 1.0000
11.000 1.4539 0.02511 0.01817 -0.0735 0.0205 1.0000
11.250 1.4629 0.02640 0.01947 -0.0719 0.0165 1.0000
11.500 1.4740 0.02757 0.02067 -0.0705 0.0148 1.0000
11.750 1.4844 0.02883 0.02195 -0.0692 0.0134 1.0000
12.000 1.4958 0.03000 0.02317 -0.0680 0.0128 1.0000
12.250 1.5062 0.03127 0.02448 -0.0668 0.0121 1.0000
12.500 1.5159 0.03264 0.02589 -0.0656 0.0115 1.0000
12.750 1.5244 0.03414 0.02744 -0.0644 0.0109 1.0000
13.000 1.5331 0.03564 0.02899 -0.0633 0.0105 1.0000
13.250 1.5425 0.03711 0.03051 -0.0622 0.0102 1.0000
13.500 1.5510 0.03869 0.03215 -0.0612 0.0099 1.0000
13.750 1.5589 0.04035 0.03386 -0.0603 0.0095 1.0000
14.000 1.5661 0.04212 0.03568 -0.0593 0.0092 1.0000
14.250 1.5721 0.04402 0.03763 -0.0584 0.0089 1.0000
14.500 1.5773 0.04602 0.03969 -0.0575 0.0086 1.0000
14.750 1.5812 0.04821 0.04194 -0.0566 0.0083 1.0000
15.000 1.5852 0.05044 0.04423 -0.0558 0.0080 1.0000
15.250 1.5902 0.05261 0.04646 -0.0552 0.0079 1.0000
15.500 1.5945 0.05486 0.04878 -0.0546 0.0077 1.0000
15.750 1.5975 0.05729 0.05129 -0.0541 0.0075 1.0000
16.000 1.5999 0.05985 0.05392 -0.0536 0.0074 1.0000
16.250 1.6020 0.06248 0.05662 -0.0532 0.0072 1.0000
16.500 1.6032 0.06526 0.05947 -0.0529 0.0071 1.0000
16.750 1.6032 0.06823 0.06252 -0.0526 0.0069 1.0000
17.000 1.6023 0.07132 0.06568 -0.0525 0.0068 1.0000
17.250 1.6008 0.07455 0.06899 -0.0524 0.0066 1.0000
17.500 1.5984 0.07795 0.07247 -0.0524 0.0065 1.0000
17.750 1.5945 0.08160 0.07620 -0.0526 0.0064 1.0000
18.000 1.5892 0.08549 0.08017 -0.0529 0.0063 1.0000
18.250 1.5819 0.08968 0.08447 -0.0533 0.0061 1.0000
18.500 1.5748 0.09392 0.08880 -0.0539 0.0061 1.0000
18.750 1.5695 0.09799 0.09296 -0.0545 0.0060 1.0000
19.000 1.5633 0.10223 0.09729 -0.0553 0.0060 1.0000
19.250 1.5565 0.10658 0.10174 -0.0563 0.0059 1.0000
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Polar data table (+)
Polar graphs
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