GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 50,000 Max Cl/Cd: 32.44 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe114-il-50000-n5.txt Download as CSV file: xf-goe114-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 114 (MVA MK.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3843 0.09878 0.09233 -0.0442 1.0000 0.0566
-8.500 -0.3911 0.09469 0.08839 -0.0459 1.0000 0.0529
-8.250 -0.3963 0.09099 0.08479 -0.0472 1.0000 0.0487
-8.000 -0.3988 0.08799 0.08190 -0.0464 1.0000 0.0470
-7.750 -0.4065 0.08508 0.07912 -0.0459 1.0000 0.0457
-7.500 -0.4180 0.08212 0.07631 -0.0454 1.0000 0.0446
-7.250 -0.4278 0.07864 0.07297 -0.0460 1.0000 0.0431
-6.750 -0.4498 0.06873 0.06304 -0.0528 1.0000 0.0386
-6.500 -0.4527 0.06552 0.05984 -0.0521 1.0000 0.0378
-6.250 -0.4553 0.06180 0.05604 -0.0526 1.0000 0.0371
-6.000 -0.4550 0.05774 0.05181 -0.0535 1.0000 0.0363
-5.750 -0.4505 0.05364 0.04744 -0.0547 1.0000 0.0353
-5.500 -0.4415 0.04955 0.04295 -0.0558 1.0000 0.0342
-5.250 -0.4282 0.04580 0.03870 -0.0565 1.0000 0.0332
-5.000 -0.3962 0.04183 0.03379 -0.0597 0.9954 0.0315
-4.750 -0.3626 0.03904 0.03025 -0.0618 0.9899 0.0304
-4.500 -0.3310 0.03596 0.02673 -0.0633 0.9851 0.0295
-4.250 -0.2981 0.03356 0.02393 -0.0645 0.9802 0.0289
-4.000 -0.2665 0.03165 0.02168 -0.0651 0.9749 0.0286
-3.750 -0.2337 0.03007 0.01980 -0.0659 0.9696 0.0287
-3.500 -0.2030 0.02892 0.01833 -0.0665 0.9634 0.0300
-3.250 -0.1698 0.02745 0.01661 -0.0681 0.9578 0.0333
-3.000 -0.1365 0.02635 0.01509 -0.0695 0.9514 0.0363
-2.750 -0.1008 0.02543 0.01373 -0.0713 0.9453 0.0404
-2.500 -0.0621 0.02342 0.01272 -0.0745 0.9411 0.2382
-2.250 -0.0326 0.02404 0.01317 -0.0746 0.9323 0.3606
-2.000 -0.0077 0.02443 0.01354 -0.0740 0.9242 0.4344
-1.750 0.0241 0.02441 0.01330 -0.0748 0.9175 0.4729
-1.500 0.0551 0.02429 0.01288 -0.0757 0.9098 0.4825
-1.250 0.0921 0.02416 0.01242 -0.0778 0.9036 0.4925
-1.000 0.1224 0.02412 0.01214 -0.0787 0.8954 0.5020
-0.750 0.1597 0.02399 0.01189 -0.0808 0.8894 0.5124
-0.500 0.1888 0.02396 0.01174 -0.0814 0.8809 0.5230
-0.250 0.2271 0.02383 0.01157 -0.0836 0.8752 0.5358
0.000 0.2544 0.02382 0.01157 -0.0839 0.8661 0.5493
0.250 0.2911 0.02364 0.01149 -0.0857 0.8603 0.5685
0.500 0.3175 0.02358 0.01158 -0.0857 0.8510 0.5924
0.750 0.3459 0.02335 0.01167 -0.0859 0.8431 0.6338
1.000 0.3889 0.02259 0.01169 -0.0886 0.8364 1.0000
1.250 0.4169 0.02287 0.01193 -0.0890 0.8269 1.0000
1.500 0.4531 0.02296 0.01201 -0.0905 0.8205 1.0000
1.750 0.4771 0.02329 0.01237 -0.0901 0.8099 1.0000
2.000 0.5046 0.02357 0.01273 -0.0902 0.8008 1.0000
2.250 0.5373 0.02370 0.01309 -0.0910 0.7932 1.0000
2.500 0.5607 0.02408 0.01365 -0.0903 0.7825 1.0000
2.750 0.6034 0.02225 0.01203 -0.0891 0.7481 1.0000
3.000 0.6281 0.02045 0.01028 -0.0841 0.6799 1.0000
3.250 0.6458 0.01991 0.00955 -0.0797 0.5907 1.0000
3.500 0.6419 0.02190 0.00915 -0.0731 0.2317 1.0000
3.750 0.6459 0.02453 0.01075 -0.0701 0.0442 1.0000
4.000 0.6638 0.02563 0.01200 -0.0684 0.0382 1.0000
4.250 0.6820 0.02662 0.01325 -0.0667 0.0350 1.0000
4.500 0.6964 0.02795 0.01485 -0.0647 0.0312 1.0000
4.750 0.7095 0.02931 0.01643 -0.0625 0.0292 1.0000
5.000 0.7217 0.03067 0.01804 -0.0602 0.0285 1.0000
5.250 0.7325 0.03210 0.01968 -0.0576 0.0282 1.0000
5.500 0.7429 0.03358 0.02135 -0.0549 0.0281 1.0000
5.750 0.7588 0.03504 0.02296 -0.0528 0.0282 1.0000
6.000 0.7978 0.03677 0.02492 -0.0528 0.0282 1.0000
6.250 0.8550 0.03912 0.02741 -0.0548 0.0275 1.0000
6.500 0.8990 0.04186 0.03039 -0.0558 0.0271 1.0000
6.750 0.9342 0.04500 0.03381 -0.0558 0.0283 1.0000
7.000 0.9655 0.04890 0.03787 -0.0559 0.0298 1.0000
7.250 0.9863 0.05078 0.04039 -0.0534 0.0324 1.0000
7.500 1.0055 0.05411 0.04417 -0.0515 0.0354 1.0000
7.750 1.0319 0.05997 0.05003 -0.0517 0.0387 1.0000
8.000 1.0359 0.06047 0.05147 -0.0468 0.0434 1.0000
8.250 1.0600 0.06652 0.05764 -0.0467 0.0495 1.0000
8.500 1.0551 0.06740 0.05940 -0.0417 0.0553 1.0000
8.750 1.0658 0.07130 0.06369 -0.0395 0.0644 1.0000
9.000 1.0616 0.07522 0.06801 -0.0368 0.0700 1.0000
9.250 1.0820 0.08228 0.07522 -0.0365 0.0859 1.0000
9.750 1.0770 0.09261 0.08642 -0.0334 0.1267 1.0000
10.250 1.0147 0.09782 0.09182 -0.0291 0.1125 1.0000
10.500 0.9915 0.10232 0.09640 -0.0296 0.1125 1.0000
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Polar data table (+)
Polar graphs
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