GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.92 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe426-il-1000000.txt Download as CSV file: xf-goe426-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1329 0.08347 0.08171 -0.0710 0.9271 0.0250
-10.250 -0.1270 0.08029 0.07845 -0.0722 0.9067 0.0254
-10.000 -0.1233 0.07723 0.07531 -0.0729 0.8829 0.0259
-9.750 -0.1222 0.07392 0.07189 -0.0736 0.8575 0.0265
-9.500 -0.1437 0.06505 0.06297 -0.0785 0.8406 0.0284
-9.250 -0.1502 0.05987 0.05771 -0.0805 0.8190 0.0284
-9.000 -0.1657 0.05255 0.05032 -0.0839 0.8009 0.0285
-8.750 -0.2612 0.04871 0.04634 -0.1056 0.8368 0.0285
-8.500 -0.3039 0.04027 0.03755 -0.1067 0.8082 0.0289
-8.250 -0.2935 0.03860 0.03574 -0.1063 0.7872 0.0291
-8.000 -0.2809 0.03710 0.03411 -0.1060 0.7697 0.0293
-7.750 -0.2670 0.03557 0.03244 -0.1058 0.7556 0.0295
-7.500 -0.2520 0.03392 0.03065 -0.1056 0.7434 0.0298
-7.250 -0.2350 0.03239 0.02898 -0.1054 0.7324 0.0302
-7.000 -0.2183 0.03043 0.02684 -0.1053 0.7226 0.0309
-6.750 -0.2222 0.02070 0.01593 -0.1036 0.7149 0.0281
-6.500 -0.2005 0.01896 0.01392 -0.1031 0.7060 0.0281
-6.250 -0.1770 0.01774 0.01245 -0.1027 0.6964 0.0282
-6.000 -0.1508 0.01747 0.01202 -0.1025 0.6873 0.0285
-5.750 -0.1292 0.01503 0.00930 -0.1020 0.6784 0.0290
-5.500 -0.1033 0.01419 0.00836 -0.1018 0.6691 0.0293
-5.250 -0.0772 0.01359 0.00767 -0.1016 0.6590 0.0295
-5.000 -0.0508 0.01306 0.00705 -0.1014 0.6478 0.0298
-4.750 -0.0241 0.01260 0.00651 -0.1012 0.6367 0.0301
-4.500 0.0025 0.01218 0.00601 -0.1010 0.6255 0.0303
-4.250 0.0292 0.01181 0.00556 -0.1008 0.6136 0.0307
-4.000 0.0560 0.01144 0.00513 -0.1006 0.6021 0.0310
-3.750 0.0828 0.01112 0.00473 -0.1004 0.5918 0.0314
-3.500 0.1096 0.01084 0.00438 -0.1001 0.5820 0.0319
-3.250 0.1369 0.01060 0.00409 -0.1000 0.5737 0.0325
-3.000 0.1641 0.01046 0.00388 -0.0998 0.5656 0.0331
-2.750 0.1916 0.01026 0.00365 -0.0997 0.5590 0.0334
-2.500 0.2187 0.01002 0.00335 -0.0995 0.5524 0.0338
-2.250 0.2451 0.00961 0.00290 -0.0993 0.5467 0.0346
-2.000 0.2727 0.00941 0.00269 -0.0993 0.5416 0.0354
-1.750 0.3004 0.00930 0.00254 -0.0992 0.5364 0.0362
-1.500 0.3278 0.00922 0.00242 -0.0991 0.5314 0.0371
-1.250 0.3561 0.00910 0.00230 -0.0991 0.5277 0.0383
-1.000 0.3841 0.00903 0.00221 -0.0991 0.5235 0.0393
-0.750 0.4117 0.00890 0.00205 -0.0990 0.5194 0.0413
-0.500 0.4393 0.00886 0.00198 -0.0989 0.5151 0.0436
-0.250 0.4677 0.00879 0.00191 -0.0990 0.5121 0.0460
0.000 0.4958 0.00870 0.00183 -0.0990 0.5085 0.0509
0.250 0.5236 0.00857 0.00177 -0.0990 0.5049 0.0774
0.500 0.5481 0.00776 0.00177 -0.0989 0.5012 0.3793
0.750 0.5742 0.00743 0.00183 -0.0988 0.4977 0.5186
1.000 0.6015 0.00728 0.00189 -0.0987 0.4947 0.5983
1.250 0.6288 0.00720 0.00194 -0.0985 0.4913 0.6472
1.500 0.6555 0.00714 0.00201 -0.0983 0.4878 0.7020
1.750 0.6817 0.00713 0.00210 -0.0979 0.4839 0.7521
2.000 0.7081 0.00708 0.00216 -0.0975 0.4808 0.7967
2.250 0.7317 0.00688 0.00222 -0.0964 0.4776 0.8743
2.500 0.7771 0.00678 0.00227 -0.1001 0.4737 1.0000
2.750 0.8042 0.00688 0.00232 -0.0999 0.4700 1.0000
3.000 0.8312 0.00700 0.00240 -0.0998 0.4660 1.0000
3.250 0.8592 0.00705 0.00245 -0.0998 0.4627 1.0000
3.500 0.8867 0.00712 0.00251 -0.0998 0.4587 1.0000
3.750 0.9139 0.00723 0.00259 -0.0996 0.4547 1.0000
4.000 0.9406 0.00736 0.00269 -0.0995 0.4504 1.0000
4.250 0.9684 0.00742 0.00276 -0.0995 0.4468 1.0000
4.500 0.9958 0.00750 0.00284 -0.0994 0.4422 1.0000
4.750 1.0225 0.00763 0.00294 -0.0992 0.4374 1.0000
5.000 1.0494 0.00774 0.00304 -0.0991 0.4328 1.0000
5.250 1.0767 0.00782 0.00314 -0.0991 0.4273 1.0000
5.500 1.1029 0.00797 0.00325 -0.0988 0.4213 1.0000
5.750 1.1297 0.00808 0.00337 -0.0987 0.4156 1.0000
6.000 1.1561 0.00820 0.00349 -0.0985 0.4086 1.0000
6.250 1.1820 0.00836 0.00362 -0.0982 0.4002 1.0000
6.500 1.2075 0.00853 0.00376 -0.0979 0.3911 1.0000
6.750 1.2333 0.00869 0.00392 -0.0976 0.3833 1.0000
7.250 1.2825 0.00913 0.00429 -0.0967 0.3616 1.0000
7.500 1.3067 0.00936 0.00449 -0.0962 0.3500 1.0000
7.750 1.3301 0.00964 0.00473 -0.0956 0.3376 1.0000
8.000 1.3527 0.00995 0.00499 -0.0948 0.3237 1.0000
8.250 1.3745 0.01030 0.00528 -0.0939 0.3080 1.0000
8.500 1.3956 0.01067 0.00559 -0.0930 0.2924 1.0000
8.750 1.4161 0.01107 0.00592 -0.0919 0.2763 1.0000
9.000 1.4347 0.01154 0.00630 -0.0905 0.2571 1.0000
9.250 1.4487 0.01221 0.00682 -0.0884 0.2284 1.0000
9.500 1.4524 0.01325 0.00760 -0.0846 0.1855 1.0000
9.750 1.4449 0.01453 0.00861 -0.0790 0.1419 1.0000
10.000 1.4419 0.01572 0.00963 -0.0744 0.1129 1.0000
10.250 1.4435 0.01679 0.01059 -0.0708 0.0922 1.0000
10.500 1.4380 0.01830 0.01193 -0.0666 0.0641 1.0000
10.750 1.4340 0.01988 0.01341 -0.0630 0.0444 1.0000
11.000 1.4302 0.02162 0.01506 -0.0598 0.0295 1.0000
11.250 1.4326 0.02313 0.01657 -0.0575 0.0233 1.0000
11.500 1.4373 0.02460 0.01806 -0.0557 0.0209 1.0000
11.750 1.4437 0.02605 0.01956 -0.0542 0.0195 1.0000
12.000 1.4495 0.02761 0.02117 -0.0529 0.0185 1.0000
12.250 1.4525 0.02950 0.02311 -0.0516 0.0175 1.0000
12.500 1.4555 0.03148 0.02515 -0.0505 0.0167 1.0000
12.750 1.4611 0.03329 0.02703 -0.0496 0.0163 1.0000
13.000 1.4653 0.03530 0.02910 -0.0488 0.0158 1.0000
13.250 1.4684 0.03746 0.03133 -0.0481 0.0154 1.0000
13.500 1.4700 0.03983 0.03376 -0.0474 0.0150 1.0000
13.750 1.4693 0.04253 0.03653 -0.0469 0.0145 1.0000
14.000 1.4663 0.04556 0.03963 -0.0464 0.0142 1.0000
14.250 1.4604 0.04902 0.04319 -0.0462 0.0138 1.0000
14.500 1.4613 0.05181 0.04606 -0.0460 0.0136 1.0000
14.750 1.4617 0.05471 0.04904 -0.0460 0.0134 1.0000
15.000 1.4621 0.05766 0.05206 -0.0461 0.0132 1.0000
15.250 1.4620 0.06074 0.05521 -0.0463 0.0129 1.0000
15.500 1.4606 0.06405 0.05860 -0.0465 0.0127 1.0000
15.750 1.4603 0.06726 0.06187 -0.0469 0.0124 1.0000
16.000 1.4584 0.07072 0.06541 -0.0473 0.0122 1.0000
16.250 1.4553 0.07441 0.06917 -0.0479 0.0121 1.0000
16.500 1.4533 0.07803 0.07286 -0.0486 0.0118 1.0000
16.750 1.4475 0.08222 0.07712 -0.0494 0.0116 1.0000
17.000 1.4386 0.08697 0.08196 -0.0505 0.0113 1.0000
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