GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.97 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe406-il-1000000-n5.txt Download as CSV file: xf-goe406-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1544 0.10654 0.10466 -0.0731 0.9667 0.0141
-11.000 -0.1449 0.10293 0.10105 -0.0756 0.9618 0.0142
-10.750 -0.1434 0.09636 0.09446 -0.0803 0.9565 0.0148
-10.500 -0.1172 0.09403 0.09210 -0.0847 0.9457 0.0150
-10.250 -0.0790 0.08970 0.08769 -0.0940 0.9193 0.0152
-10.000 -0.0258 0.08405 0.08161 -0.1086 0.8436 0.0155
-9.750 -0.0046 0.08070 0.07805 -0.1139 0.8130 0.0156
-9.500 0.0088 0.07807 0.07528 -0.1168 0.7882 0.0160
-9.250 0.0166 0.07521 0.07237 -0.1188 0.7776 0.0161
-9.000 0.0241 0.07252 0.06962 -0.1206 0.7657 0.0165
-8.750 0.0288 0.06958 0.06664 -0.1223 0.7545 0.0165
-8.250 0.0056 0.05998 0.05700 -0.1281 0.7369 0.0175
-8.000 0.0064 0.05843 0.05544 -0.1273 0.7307 0.0176
-7.750 0.0118 0.05714 0.05412 -0.1265 0.7214 0.0178
-7.250 0.0197 0.05272 0.04964 -0.1266 0.7087 0.0180
-7.000 0.0263 0.05074 0.04761 -0.1262 0.7013 0.0182
-6.750 0.0283 0.04769 0.04448 -0.1258 0.6962 0.0182
-6.500 0.0356 0.04531 0.04205 -0.1252 0.6895 0.0183
-6.250 0.0426 0.04283 0.03948 -0.1241 0.6827 0.0184
-6.000 0.0500 0.04016 0.03670 -0.1228 0.6777 0.0186
-5.750 0.0579 0.03736 0.03379 -0.1212 0.6724 0.0187
-5.500 0.0657 0.03459 0.03088 -0.1191 0.6664 0.0188
-5.250 0.0747 0.03194 0.02807 -0.1167 0.6614 0.0192
-5.000 0.0795 0.02828 0.02419 -0.1131 0.6561 0.0196
-4.750 0.0423 0.01689 0.01169 -0.1008 0.6535 0.0203
-4.500 0.0554 0.01528 0.00974 -0.0978 0.6467 0.0206
-4.250 0.0743 0.01438 0.00867 -0.0960 0.6395 0.0207
-4.000 0.0951 0.01388 0.00805 -0.0945 0.6310 0.0209
-3.750 0.1172 0.01347 0.00755 -0.0932 0.6240 0.0210
-3.500 0.1398 0.01306 0.00704 -0.0920 0.6176 0.0212
-3.000 0.1856 0.01220 0.00598 -0.0897 0.6048 0.0215
-2.750 0.2090 0.01183 0.00552 -0.0887 0.5982 0.0217
-2.500 0.2324 0.01151 0.00511 -0.0876 0.5907 0.0219
-2.250 0.2564 0.01117 0.00469 -0.0867 0.5835 0.0220
-2.000 0.2800 0.01096 0.00441 -0.0857 0.5762 0.0224
-1.750 0.3041 0.01067 0.00405 -0.0848 0.5679 0.0225
-1.500 0.3275 0.01047 0.00378 -0.0837 0.5588 0.0228
-1.250 0.3508 0.01028 0.00352 -0.0826 0.5472 0.0229
-1.000 0.3734 0.01014 0.00330 -0.0814 0.5335 0.0231
-0.750 0.3955 0.01002 0.00309 -0.0801 0.5179 0.0233
-0.500 0.4172 0.00996 0.00295 -0.0787 0.5007 0.0235
-0.250 0.4380 0.00994 0.00283 -0.0771 0.4802 0.0236
0.000 0.4586 0.01002 0.00281 -0.0755 0.4583 0.0239
0.250 0.4768 0.00999 0.00265 -0.0734 0.4303 0.0243
0.500 0.4963 0.01003 0.00260 -0.0716 0.4089 0.0246
0.750 0.5162 0.01008 0.00258 -0.0699 0.3901 0.0249
1.000 0.5358 0.01014 0.00256 -0.0681 0.3737 0.0252
1.250 0.5549 0.01020 0.00256 -0.0662 0.3596 0.0256
1.500 0.5750 0.01021 0.00253 -0.0645 0.3504 0.0259
1.750 0.5946 0.01025 0.00253 -0.0627 0.3421 0.0264
2.000 0.6153 0.01026 0.00253 -0.0611 0.3355 0.0268
2.250 0.6355 0.01032 0.00256 -0.0595 0.3290 0.0273
2.500 0.6566 0.01036 0.00258 -0.0580 0.3240 0.0276
2.750 0.6779 0.01038 0.00260 -0.0566 0.3195 0.0282
3.000 0.6984 0.01045 0.00265 -0.0550 0.3139 0.0293
3.250 0.7190 0.01053 0.00272 -0.0535 0.3093 0.0302
3.500 0.7407 0.01059 0.00279 -0.0522 0.3064 0.0314
3.750 0.7622 0.01066 0.00287 -0.0509 0.3028 0.0326
4.000 0.7834 0.01075 0.00295 -0.0495 0.2994 0.0346
4.250 0.8044 0.01084 0.00306 -0.0481 0.2961 0.0419
4.500 0.8253 0.01087 0.00324 -0.0468 0.2927 0.1235
5.000 1.1745 0.01065 0.00473 -0.1147 0.2757 1.0000
5.250 1.1966 0.01078 0.00486 -0.1136 0.2742 1.0000
5.500 1.2180 0.01092 0.00500 -0.1123 0.2700 1.0000
5.750 1.2382 0.01111 0.00516 -0.1109 0.2650 1.0000
6.000 1.2579 0.01130 0.00534 -0.1093 0.2609 1.0000
6.250 1.2784 0.01146 0.00551 -0.1079 0.2586 1.0000
6.500 1.2988 0.01160 0.00567 -0.1065 0.2561 1.0000
6.750 1.3178 0.01177 0.00584 -0.1048 0.2527 1.0000
7.000 1.3345 0.01194 0.00602 -0.1026 0.2497 1.0000
7.250 1.3493 0.01215 0.00621 -0.1000 0.2451 1.0000
7.500 1.3661 0.01232 0.00640 -0.0979 0.2428 1.0000
7.750 1.3834 0.01248 0.00659 -0.0959 0.2393 1.0000
8.000 1.3991 0.01271 0.00681 -0.0936 0.2337 1.0000
8.250 1.4140 0.01297 0.00706 -0.0912 0.2289 1.0000
8.500 1.4307 0.01319 0.00730 -0.0892 0.2241 1.0000
8.750 1.4453 0.01349 0.00758 -0.0869 0.2169 1.0000
9.000 1.4594 0.01383 0.00790 -0.0844 0.2083 1.0000
9.250 1.4681 0.01439 0.00836 -0.0812 0.1897 1.0000
9.500 1.4743 0.01508 0.00894 -0.0775 0.1688 1.0000
9.750 1.4580 0.01683 0.01034 -0.0704 0.1161 1.0000
10.000 1.4644 0.01765 0.01110 -0.0671 0.1026 1.0000
10.250 1.4706 0.01850 0.01191 -0.0639 0.0890 1.0000
10.500 1.4611 0.02026 0.01344 -0.0587 0.0537 1.0000
10.750 1.4637 0.02146 0.01459 -0.0555 0.0412 1.0000
11.000 1.4731 0.02231 0.01546 -0.0533 0.0377 1.0000
11.250 1.4825 0.02321 0.01638 -0.0512 0.0352 1.0000
11.500 1.4909 0.02420 0.01740 -0.0491 0.0325 1.0000
11.750 1.5007 0.02516 0.01839 -0.0473 0.0310 1.0000
12.000 1.5095 0.02623 0.01950 -0.0456 0.0296 1.0000
12.250 1.5165 0.02748 0.02076 -0.0438 0.0276 1.0000
12.500 1.5257 0.02858 0.02192 -0.0423 0.0269 1.0000
12.750 1.5341 0.02979 0.02319 -0.0408 0.0262 1.0000
13.000 1.5413 0.03113 0.02457 -0.0393 0.0250 1.0000
13.250 1.5474 0.03260 0.02608 -0.0378 0.0239 1.0000
13.500 1.5529 0.03415 0.02767 -0.0364 0.0228 1.0000
13.750 1.5592 0.03566 0.02924 -0.0351 0.0223 1.0000
14.000 1.5648 0.03728 0.03092 -0.0339 0.0217 1.0000
14.250 1.5687 0.03910 0.03278 -0.0327 0.0204 1.0000
14.500 1.5716 0.04105 0.03478 -0.0316 0.0197 1.0000
14.750 1.5738 0.04310 0.03689 -0.0305 0.0190 1.0000
15.000 1.5768 0.04513 0.03899 -0.0296 0.0184 1.0000
15.250 1.5785 0.04735 0.04128 -0.0287 0.0179 1.0000
15.500 1.5788 0.04977 0.04376 -0.0279 0.0171 1.0000
15.750 1.5789 0.05228 0.04634 -0.0273 0.0169 1.0000
16.000 1.5764 0.05513 0.04925 -0.0267 0.0161 1.0000
16.250 1.5732 0.05816 0.05235 -0.0262 0.0156 1.0000
16.500 1.5713 0.06111 0.05539 -0.0259 0.0153 1.0000
16.750 1.5681 0.06427 0.05863 -0.0257 0.0149 1.0000
17.000 1.5629 0.06775 0.06219 -0.0256 0.0144 1.0000
17.250 1.5566 0.07146 0.06597 -0.0257 0.0139 1.0000
17.500 1.5496 0.07535 0.06996 -0.0260 0.0138 1.0000
17.750 1.5402 0.07964 0.07434 -0.0264 0.0135 1.0000
18.000 1.5302 0.08407 0.07887 -0.0269 0.0132 1.0000
18.250 1.5207 0.08851 0.08340 -0.0276 0.0130 1.0000
18.500 1.5077 0.09356 0.08853 -0.0285 0.0126 1.0000
18.750 1.4974 0.09823 0.09330 -0.0294 0.0125 1.0000
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