GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 200,000 Max Cl/Cd: 64.83 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe488-il-200000-n5.txt Download as CSV file: xf-goe488-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4291 0.09649 0.09282 -0.0270 1.0000 0.0214
-9.000 -0.4344 0.09220 0.08860 -0.0291 1.0000 0.0223
-8.750 -0.4351 0.08917 0.08560 -0.0292 1.0000 0.0226
-8.500 -0.4237 0.08849 0.08494 -0.0275 1.0000 0.0238
-8.250 -0.4229 0.08627 0.08275 -0.0273 1.0000 0.0247
-8.000 -0.4295 0.08349 0.08003 -0.0271 1.0000 0.0248
-7.750 -0.4400 0.08087 0.07749 -0.0264 1.0000 0.0249
-7.500 -0.4455 0.07787 0.07454 -0.0268 1.0000 0.0252
-7.250 -0.4511 0.07478 0.07148 -0.0270 1.0000 0.0253
-7.000 -0.4557 0.07161 0.06833 -0.0272 1.0000 0.0256
-6.750 -0.4509 0.06792 0.06462 -0.0294 0.9989 0.0268
-6.500 -0.4245 0.06127 0.05780 -0.0381 0.9940 0.0287
-6.250 -0.3979 0.05366 0.04996 -0.0460 0.9886 0.0298
-6.000 -0.3716 0.04464 0.04054 -0.0531 0.9834 0.0320
-5.750 -0.3483 0.04323 0.03907 -0.0545 0.9799 0.0335
-5.500 -0.3203 0.03986 0.03549 -0.0572 0.9770 0.0345
-5.250 -0.2967 0.03539 0.03070 -0.0589 0.9718 0.0352
-5.000 -0.2689 0.03216 0.02715 -0.0607 0.9687 0.0369
-4.750 -0.2428 0.02843 0.02297 -0.0617 0.9646 0.0381
-4.500 -0.2156 0.02519 0.01922 -0.0624 0.9602 0.0386
-4.000 -0.1551 0.02107 0.01429 -0.0641 0.9518 0.0397
-3.750 -0.1214 0.01971 0.01262 -0.0653 0.9480 0.0406
-3.500 -0.0853 0.01863 0.01125 -0.0670 0.9449 0.0416
-3.250 -0.0575 0.01760 0.01001 -0.0669 0.9386 0.0417
-3.000 -0.0240 0.01658 0.00880 -0.0680 0.9351 0.0418
-2.750 0.0058 0.01575 0.00784 -0.0682 0.9300 0.0419
-2.500 0.0357 0.01502 0.00700 -0.0685 0.9246 0.0422
-2.250 0.0695 0.01432 0.00623 -0.0696 0.9208 0.0426
-2.000 0.0956 0.01383 0.00569 -0.0691 0.9134 0.0431
-1.750 0.1266 0.01312 0.00498 -0.0696 0.9083 0.0443
-1.500 0.1537 0.01262 0.00449 -0.0693 0.9010 0.0461
-1.250 0.1839 0.01223 0.00410 -0.0696 0.8941 0.0484
-1.000 0.2116 0.01195 0.00380 -0.0693 0.8858 0.0507
-0.750 0.2420 0.01167 0.00349 -0.0696 0.8782 0.0537
-0.500 0.2688 0.01146 0.00327 -0.0691 0.8678 0.0582
-0.250 0.2968 0.01117 0.00303 -0.0689 0.8562 0.0705
0.000 0.3236 0.01075 0.00287 -0.0685 0.8444 0.1275
0.250 0.3505 0.01044 0.00281 -0.0682 0.8336 0.2131
0.500 0.3764 0.01024 0.00275 -0.0677 0.8216 0.2720
1.000 0.4827 0.00844 0.00273 -0.0778 0.7915 1.0000
1.500 0.5305 0.00854 0.00263 -0.0756 0.7430 1.0000
1.750 0.5539 0.00863 0.00257 -0.0743 0.7021 1.0000
2.000 0.5750 0.00887 0.00248 -0.0724 0.6426 1.0000
2.250 0.5933 0.00929 0.00252 -0.0702 0.5766 1.0000
2.500 0.6096 0.00985 0.00265 -0.0677 0.4928 1.0000
2.750 0.6259 0.01045 0.00283 -0.0655 0.4234 1.0000
3.000 0.6458 0.01088 0.00304 -0.0639 0.3877 1.0000
3.250 0.6672 0.01122 0.00324 -0.0626 0.3648 1.0000
3.500 0.6893 0.01153 0.00347 -0.0615 0.3476 1.0000
3.750 0.7124 0.01179 0.00368 -0.0605 0.3353 1.0000
4.000 0.7357 0.01203 0.00392 -0.0596 0.3253 1.0000
4.250 0.7589 0.01230 0.00416 -0.0587 0.3155 1.0000
4.500 0.7826 0.01254 0.00443 -0.0578 0.3055 1.0000
4.750 0.8062 0.01278 0.00470 -0.0570 0.2953 1.0000
5.000 0.8294 0.01305 0.00496 -0.0561 0.2792 1.0000
5.250 0.8517 0.01338 0.00521 -0.0551 0.2485 1.0000
5.500 0.8732 0.01379 0.00545 -0.0540 0.2080 1.0000
5.750 0.8936 0.01436 0.00580 -0.0528 0.1672 1.0000
6.000 0.9139 0.01500 0.00625 -0.0517 0.1333 1.0000
6.250 0.9351 0.01557 0.00673 -0.0506 0.1084 1.0000
6.500 0.9533 0.01650 0.00739 -0.0492 0.0603 1.0000
6.750 0.9730 0.01727 0.00810 -0.0478 0.0381 1.0000
7.000 0.9921 0.01812 0.00885 -0.0464 0.0219 1.0000
7.250 1.0125 0.01882 0.00962 -0.0451 0.0195 1.0000
7.500 1.0318 0.01963 0.01053 -0.0437 0.0171 1.0000
7.750 1.0496 0.02060 0.01169 -0.0420 0.0151 1.0000
8.000 1.0672 0.02152 0.01276 -0.0404 0.0145 1.0000
8.250 1.0842 0.02243 0.01383 -0.0387 0.0140 1.0000
8.500 1.0995 0.02347 0.01501 -0.0367 0.0135 1.0000
8.750 1.1136 0.02459 0.01627 -0.0347 0.0131 1.0000
9.000 1.1268 0.02578 0.01759 -0.0325 0.0125 1.0000
9.250 1.1400 0.02693 0.01886 -0.0305 0.0118 1.0000
9.500 1.1516 0.02822 0.02025 -0.0283 0.0111 1.0000
9.750 1.1606 0.02962 0.02180 -0.0258 0.0106 1.0000
10.000 1.1686 0.03114 0.02343 -0.0232 0.0103 1.0000
10.250 1.1753 0.03289 0.02530 -0.0206 0.0101 1.0000
10.500 1.1813 0.03490 0.02744 -0.0181 0.0098 1.0000
10.750 1.1866 0.03727 0.02997 -0.0158 0.0096 1.0000
11.000 1.1910 0.03992 0.03280 -0.0136 0.0095 1.0000
11.250 1.1928 0.04255 0.03564 -0.0113 0.0094 1.0000
11.500 1.1925 0.04477 0.03810 -0.0090 0.0093 1.0000
11.750 1.1898 0.04723 0.04080 -0.0069 0.0092 1.0000
12.000 1.1849 0.04998 0.04377 -0.0051 0.0092 1.0000
12.250 1.1773 0.05307 0.04711 -0.0038 0.0091 1.0000
12.500 1.1684 0.05654 0.05080 -0.0031 0.0091 1.0000
12.750 1.1585 0.06025 0.05473 -0.0030 0.0091 1.0000
13.000 1.1461 0.06467 0.05937 -0.0038 0.0091 1.0000
13.250 1.1319 0.06975 0.06466 -0.0055 0.0091 1.0000
13.500 1.1173 0.07533 0.07046 -0.0083 0.0090 1.0000
13.750 1.1025 0.08155 0.07686 -0.0117 0.0091 1.0000
14.000 1.0860 0.08866 0.08415 -0.0160 0.0091 1.0000
14.250 1.0692 0.09636 0.09200 -0.0207 0.0092 1.0000
14.500 1.0518 0.10468 0.10047 -0.0260 0.0092 1.0000
14.750 1.0351 0.11319 0.10912 -0.0314 0.0093 1.0000
15.000 1.0180 0.12211 0.11815 -0.0368 0.0093 1.0000
15.250 0.8501 0.12694 0.12356 -0.0380 0.0101 1.0000
15.500 0.8001 0.14319 0.14005 -0.0482 0.0107 1.0000
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Polar data table (+)
Polar graphs
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