GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.33 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe290-il-1000000.txt Download as CSV file: xf-goe290-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 290 (MVA 290) 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
------ -------- --------- --------- -------- -------- --------
-19.000 -1.0092 0.09819 0.09531 -0.0437 1.0000 0.0292
-18.750 -1.0340 0.09024 0.08722 -0.0487 1.0000 0.0293
-18.500 -1.0525 0.08353 0.08039 -0.0529 1.0000 0.0294
-18.250 -1.0686 0.07744 0.07418 -0.0567 1.0000 0.0294
-18.000 -1.0913 0.07086 0.06746 -0.0605 1.0000 0.0296
-17.750 -1.1116 0.06500 0.06148 -0.0638 1.0000 0.0298
-17.500 -1.1258 0.05991 0.05629 -0.0667 1.0000 0.0300
-17.250 -1.1353 0.05537 0.05167 -0.0693 1.0000 0.0301
-17.000 -1.1415 0.05115 0.04738 -0.0719 1.0000 0.0303
-16.750 -1.1448 0.04724 0.04340 -0.0744 1.0000 0.0305
-16.500 -1.1455 0.04359 0.03967 -0.0769 1.0000 0.0307
-16.250 -1.1443 0.04020 0.03620 -0.0793 1.0000 0.0308
-16.000 -1.1413 0.03711 0.03304 -0.0815 1.0000 0.0310
-15.750 -1.1369 0.03438 0.03021 -0.0833 1.0000 0.0312
-15.500 -1.1314 0.03201 0.02777 -0.0846 1.0000 0.0314
-15.250 -1.1252 0.03000 0.02568 -0.0853 1.0000 0.0316
-15.000 -1.1184 0.02833 0.02393 -0.0853 1.0000 0.0318
-14.750 -1.1112 0.02693 0.02246 -0.0846 1.0000 0.0321
-14.500 -1.1044 0.02578 0.02123 -0.0832 1.0000 0.0323
-14.250 -1.1007 0.02487 0.02025 -0.0807 1.0000 0.0325
-14.000 -1.1030 0.02422 0.01955 -0.0764 1.0000 0.0327
-13.750 -1.1003 0.02364 0.01891 -0.0728 1.0000 0.0329
-13.500 -1.0774 0.02294 0.01814 -0.0728 0.9984 0.0332
-13.250 -1.0479 0.02225 0.01739 -0.0740 0.9962 0.0334
-13.000 -1.0230 0.02090 0.01596 -0.0750 0.9941 0.0339
-12.750 -0.9950 0.01990 0.01493 -0.0762 0.9921 0.0344
-12.500 -0.9674 0.01920 0.01420 -0.0769 0.9882 0.0348
-12.250 -0.9383 0.01859 0.01357 -0.0777 0.9841 0.0352
-12.000 -0.9101 0.01804 0.01299 -0.0782 0.9791 0.0356
-11.750 -0.8863 0.01755 0.01246 -0.0777 0.9713 0.0361
-11.500 -0.8636 0.01709 0.01196 -0.0769 0.9630 0.0365
-11.250 -0.8416 0.01669 0.01150 -0.0758 0.9539 0.0370
-11.000 -0.8190 0.01632 0.01107 -0.0749 0.9429 0.0374
-10.750 -0.7959 0.01597 0.01065 -0.0740 0.9299 0.0377
-10.500 -0.7752 0.01537 0.00997 -0.0728 0.9097 0.0382
-10.250 -0.7552 0.01484 0.00932 -0.0713 0.8710 0.0389
-9.750 -0.7072 0.01431 0.00850 -0.0698 0.8104 0.0401
-9.500 -0.6814 0.01406 0.00816 -0.0694 0.7907 0.0407
-9.250 -0.6552 0.01382 0.00782 -0.0691 0.7720 0.0414
-9.000 -0.6286 0.01360 0.00750 -0.0689 0.7527 0.0420
-8.750 -0.6016 0.01341 0.00720 -0.0687 0.7310 0.0426
-8.500 -0.5763 0.01302 0.00671 -0.0683 0.7046 0.0437
-8.250 -0.5497 0.01283 0.00641 -0.0681 0.6744 0.0448
-7.750 -0.4954 0.01258 0.00592 -0.0678 0.6189 0.0468
-7.500 -0.4676 0.01248 0.00570 -0.0677 0.5992 0.0477
-7.250 -0.4407 0.01221 0.00536 -0.0676 0.5841 0.0493
-7.000 -0.4127 0.01203 0.00515 -0.0676 0.5729 0.0507
-6.750 -0.3844 0.01191 0.00497 -0.0676 0.5637 0.0522
-6.500 -0.3557 0.01181 0.00481 -0.0677 0.5563 0.0536
-6.250 -0.3280 0.01159 0.00456 -0.0676 0.5489 0.0558
-6.000 -0.2992 0.01146 0.00442 -0.0677 0.5437 0.0578
-5.750 -0.2702 0.01137 0.00430 -0.0678 0.5384 0.0597
-5.500 -0.2419 0.01119 0.00409 -0.0679 0.5332 0.0621
-5.250 -0.2133 0.01109 0.00397 -0.0680 0.5281 0.0644
-5.000 -0.1840 0.01098 0.00385 -0.0681 0.5252 0.0665
-4.750 -0.1551 0.01083 0.00368 -0.0683 0.5217 0.0689
-4.500 -0.1263 0.01068 0.00354 -0.0684 0.5177 0.0717
-4.250 -0.0973 0.01063 0.00344 -0.0685 0.5128 0.0743
-4.000 -0.0684 0.01054 0.00331 -0.0687 0.5083 0.0769
-3.750 -0.0393 0.01036 0.00316 -0.0688 0.5053 0.0804
-3.500 -0.0100 0.01025 0.00305 -0.0690 0.5024 0.0834
-3.250 0.0191 0.01014 0.00293 -0.0692 0.4994 0.0874
-3.000 0.0481 0.01003 0.00282 -0.0693 0.4964 0.0929
-2.750 0.0769 0.00992 0.00273 -0.0695 0.4931 0.1023
-2.500 0.1053 0.00969 0.00263 -0.0696 0.4900 0.1360
-2.250 0.1329 0.00918 0.00245 -0.0698 0.4878 0.2154
-2.000 0.1615 0.00890 0.00240 -0.0700 0.4847 0.2818
-1.750 0.1908 0.00881 0.00239 -0.0702 0.4816 0.3064
-1.500 0.2201 0.00878 0.00238 -0.0704 0.4786 0.3224
-1.250 0.2495 0.00880 0.00238 -0.0706 0.4756 0.3342
-1.000 0.2785 0.00882 0.00241 -0.0708 0.4720 0.3467
-0.750 0.3084 0.00879 0.00241 -0.0711 0.4704 0.3556
-0.500 0.3380 0.00875 0.00241 -0.0713 0.4680 0.3675
-0.250 0.3677 0.00872 0.00240 -0.0716 0.4651 0.3776
0.000 0.3972 0.00871 0.00241 -0.0719 0.4622 0.3869
0.250 0.4265 0.00872 0.00242 -0.0721 0.4594 0.3964
0.500 0.4556 0.00874 0.00244 -0.0723 0.4561 0.4080
0.750 0.4849 0.00874 0.00247 -0.0725 0.4528 0.4203
1.000 0.5145 0.00868 0.00248 -0.0728 0.4498 0.4367
1.250 0.5438 0.00862 0.00248 -0.0731 0.4460 0.4580
1.500 0.5728 0.00858 0.00250 -0.0733 0.4420 0.4851
1.750 0.6012 0.00851 0.00255 -0.0734 0.4380 0.5305
2.000 0.6292 0.00832 0.00262 -0.0735 0.4350 0.6136
2.250 0.6569 0.00807 0.00268 -0.0735 0.4322 0.7104
2.500 0.6836 0.00788 0.00276 -0.0731 0.4284 0.7977
2.750 0.7085 0.00776 0.00285 -0.0723 0.4242 0.8734
3.000 0.7324 0.00776 0.00295 -0.0711 0.4198 0.9282
3.250 0.7617 0.00778 0.00301 -0.0712 0.4161 0.9620
3.500 0.7963 0.00784 0.00306 -0.0726 0.4099 0.9811
3.750 0.8327 0.00798 0.00313 -0.0744 0.4018 0.9922
4.250 0.9046 0.00822 0.00328 -0.0780 0.3833 1.0000
4.500 0.9297 0.00834 0.00336 -0.0775 0.3736 1.0000
4.750 0.9548 0.00850 0.00346 -0.0770 0.3623 1.0000
5.000 0.9795 0.00872 0.00360 -0.0765 0.3458 1.0000
5.250 1.0031 0.00907 0.00380 -0.0758 0.3223 1.0000
5.500 1.0256 0.00952 0.00408 -0.0750 0.2927 1.0000
5.750 1.0474 0.01003 0.00442 -0.0742 0.2646 1.0000
6.000 1.0708 0.01043 0.00472 -0.0735 0.2485 1.0000
6.250 1.0953 0.01075 0.00497 -0.0731 0.2386 1.0000
6.500 1.1196 0.01106 0.00523 -0.0726 0.2304 1.0000
6.750 1.1448 0.01131 0.00546 -0.0723 0.2247 1.0000
7.000 1.1697 0.01157 0.00569 -0.0719 0.2194 1.0000
7.250 1.1934 0.01190 0.00598 -0.0713 0.2129 1.0000
7.500 1.2187 0.01212 0.00620 -0.0710 0.2089 1.0000
7.750 1.2423 0.01243 0.00648 -0.0705 0.2027 1.0000
8.000 1.2658 0.01274 0.00676 -0.0699 0.1969 1.0000
8.250 1.2893 0.01303 0.00704 -0.0694 0.1895 1.0000
8.500 1.3110 0.01341 0.00737 -0.0685 0.1801 1.0000
8.750 1.3231 0.01429 0.00800 -0.0663 0.1423 1.0000
9.000 1.3199 0.01569 0.00916 -0.0615 0.1052 1.0000
9.250 1.3279 0.01651 0.00994 -0.0586 0.0937 1.0000
9.500 1.3376 0.01734 0.01072 -0.0561 0.0820 1.0000
10.000 1.3355 0.02042 0.01358 -0.0492 0.0348 1.0000
10.250 1.3463 0.02146 0.01465 -0.0477 0.0329 1.0000
10.500 1.3582 0.02249 0.01572 -0.0464 0.0318 1.0000
10.750 1.3701 0.02360 0.01687 -0.0453 0.0312 1.0000
11.000 1.3810 0.02487 0.01818 -0.0443 0.0306 1.0000
11.250 1.3904 0.02632 0.01968 -0.0433 0.0300 1.0000
11.500 1.3986 0.02796 0.02137 -0.0425 0.0295 1.0000
11.750 1.4052 0.02982 0.02328 -0.0418 0.0290 1.0000
12.000 1.4097 0.03193 0.02546 -0.0411 0.0285 1.0000
12.250 1.4128 0.03428 0.02787 -0.0406 0.0281 1.0000
12.500 1.4188 0.03640 0.03006 -0.0402 0.0280 1.0000
12.750 1.4232 0.03871 0.03244 -0.0399 0.0278 1.0000
13.000 1.4266 0.04117 0.03496 -0.0397 0.0275 1.0000
13.250 1.4287 0.04380 0.03767 -0.0395 0.0272 1.0000
13.500 1.4296 0.04661 0.04055 -0.0394 0.0269 1.0000
13.750 1.4291 0.04957 0.04358 -0.0393 0.0267 1.0000
14.000 1.4278 0.05268 0.04676 -0.0393 0.0265 1.0000
14.250 1.4257 0.05590 0.05005 -0.0393 0.0263 1.0000
14.500 1.4226 0.05925 0.05348 -0.0393 0.0261 1.0000
14.750 1.4186 0.06277 0.05707 -0.0395 0.0259 1.0000
15.000 1.4141 0.06640 0.06077 -0.0397 0.0257 1.0000
15.250 1.4094 0.07004 0.06449 -0.0399 0.0255 1.0000
15.500 1.4030 0.07398 0.06851 -0.0403 0.0253 1.0000
15.750 1.3957 0.07812 0.07272 -0.0407 0.0252 1.0000
16.000 1.3881 0.08231 0.07699 -0.0412 0.0250 1.0000
16.250 1.3789 0.08676 0.08152 -0.0419 0.0248 1.0000
16.500 1.3676 0.09160 0.08644 -0.0426 0.0246 1.0000
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