GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 500,000 Max Cl/Cd: 89.15 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe122-il-500000-n5.txt Download as CSV file: xf-goe122-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4276 0.10070 0.09853 -0.0012 1.0000 0.0073
-8.500 -0.4229 0.09692 0.09477 -0.0032 1.0000 0.0073
-8.250 -0.4213 0.09203 0.08992 -0.0062 1.0000 0.0077
-8.000 -0.4127 0.08980 0.08770 -0.0074 1.0000 0.0080
-7.750 -0.4051 0.08713 0.08506 -0.0092 1.0000 0.0082
-7.500 -0.3976 0.08394 0.08189 -0.0119 1.0000 0.0085
-7.250 -0.3873 0.07973 0.07770 -0.0163 1.0000 0.0085
-7.000 -0.3662 0.07418 0.07213 -0.0243 0.9622 0.0084
-6.750 -0.3453 0.06908 0.06695 -0.0311 0.9361 0.0085
-6.500 -0.3267 0.06432 0.06211 -0.0365 0.9166 0.0087
-6.250 -0.3061 0.05936 0.05704 -0.0420 0.9016 0.0090
-6.000 -0.2825 0.05380 0.05132 -0.0478 0.8886 0.0093
-5.500 -0.2281 0.04115 0.03823 -0.0587 0.8647 0.0109
-5.250 -0.2023 0.03783 0.03473 -0.0607 0.8520 0.0113
-4.750 -0.1453 0.02370 0.01952 -0.0654 0.8312 0.0143
-4.500 -0.1194 0.02326 0.01898 -0.0654 0.8180 0.0149
-4.250 -0.0928 0.02145 0.01689 -0.0655 0.8038 0.0159
-4.000 -0.0651 0.01664 0.01125 -0.0654 0.7903 0.0189
-3.750 -0.0384 0.01642 0.01092 -0.0653 0.7731 0.0195
-3.500 -0.0115 0.01592 0.01026 -0.0652 0.7540 0.0203
-3.250 0.0158 0.01510 0.00918 -0.0650 0.7343 0.0214
-3.000 0.0433 0.01442 0.00822 -0.0648 0.7154 0.0230
-2.750 0.0711 0.01388 0.00740 -0.0646 0.6971 0.0239
-2.500 0.0989 0.01364 0.00694 -0.0644 0.6789 0.0243
-2.250 0.1260 0.01235 0.00547 -0.0644 0.6619 0.0256
-2.000 0.1536 0.01196 0.00496 -0.0643 0.6463 0.0266
-1.750 0.1813 0.01155 0.00444 -0.0643 0.6323 0.0272
-1.500 0.2090 0.01119 0.00398 -0.0642 0.6175 0.0277
-1.250 0.2366 0.01090 0.00356 -0.0641 0.5999 0.0282
-1.000 0.2643 0.01064 0.00320 -0.0640 0.5815 0.0286
-0.750 0.2920 0.01045 0.00292 -0.0639 0.5629 0.0294
-0.500 0.3198 0.01027 0.00266 -0.0638 0.5447 0.0301
-0.250 0.3474 0.01011 0.00240 -0.0638 0.5227 0.0303
0.000 0.3749 0.01002 0.00218 -0.0637 0.4951 0.0306
0.250 0.4025 0.00999 0.00202 -0.0636 0.4692 0.0310
0.500 0.4301 0.00997 0.00191 -0.0636 0.4505 0.0315
0.750 0.4579 0.00996 0.00183 -0.0636 0.4367 0.0320
1.000 0.4857 0.00993 0.00175 -0.0636 0.4257 0.0326
1.250 0.5136 0.00992 0.00168 -0.0636 0.4164 0.0337
1.500 0.5415 0.00994 0.00166 -0.0636 0.4078 0.0347
1.750 0.5693 0.00997 0.00166 -0.0636 0.4004 0.0368
2.000 0.5971 0.01002 0.00169 -0.0636 0.3914 0.0387
2.250 0.6249 0.01008 0.00173 -0.0636 0.3828 0.0402
2.750 0.6765 0.00828 0.00203 -0.0633 0.3581 1.0000
3.000 0.7039 0.00845 0.00211 -0.0633 0.3448 1.0000
3.250 0.7315 0.00858 0.00220 -0.0632 0.3356 1.0000
3.500 0.7588 0.00877 0.00232 -0.0632 0.3208 1.0000
3.750 0.7859 0.00897 0.00244 -0.0631 0.3047 1.0000
4.000 0.8131 0.00917 0.00258 -0.0630 0.2902 1.0000
4.250 0.8398 0.00942 0.00275 -0.0630 0.2705 1.0000
4.500 0.8662 0.00975 0.00295 -0.0629 0.2421 1.0000
4.750 0.8912 0.01030 0.00326 -0.0627 0.1940 1.0000
5.000 0.9168 0.01075 0.00359 -0.0625 0.1717 1.0000
5.250 0.9429 0.01110 0.00389 -0.0623 0.1594 1.0000
5.500 0.9693 0.01139 0.00417 -0.0622 0.1493 1.0000
5.750 0.9949 0.01178 0.00450 -0.0620 0.1319 1.0000
6.000 1.0159 0.01298 0.00525 -0.0614 0.0503 1.0000
6.250 1.0409 0.01344 0.00570 -0.0611 0.0408 1.0000
6.500 1.0663 0.01384 0.00612 -0.0609 0.0378 1.0000
6.750 1.0914 0.01426 0.00660 -0.0605 0.0348 1.0000
7.000 1.1164 0.01467 0.00707 -0.0602 0.0328 1.0000
7.250 1.1415 0.01503 0.00749 -0.0600 0.0317 1.0000
7.500 1.1663 0.01542 0.00796 -0.0597 0.0301 1.0000
7.750 1.1906 0.01587 0.00848 -0.0593 0.0281 1.0000
8.000 1.2141 0.01641 0.00906 -0.0589 0.0258 1.0000
8.250 1.2363 0.01712 0.00984 -0.0583 0.0232 1.0000
8.500 1.2610 0.01742 0.01019 -0.0580 0.0219 1.0000
8.750 1.2849 0.01781 0.01064 -0.0576 0.0191 1.0000
9.000 1.3075 0.01835 0.01119 -0.0571 0.0163 1.0000
9.250 1.3295 0.01894 0.01184 -0.0565 0.0143 1.0000
9.500 1.3509 0.01957 0.01246 -0.0559 0.0123 1.0000
9.750 1.3706 0.02035 0.01329 -0.0550 0.0107 1.0000
10.000 1.3901 0.02110 0.01414 -0.0541 0.0097 1.0000
10.250 1.4084 0.02193 0.01506 -0.0531 0.0089 1.0000
10.500 1.4247 0.02291 0.01611 -0.0519 0.0082 1.0000
10.750 1.4383 0.02405 0.01736 -0.0504 0.0076 1.0000
11.000 1.4522 0.02507 0.01850 -0.0489 0.0072 1.0000
11.250 1.4637 0.02616 0.01971 -0.0472 0.0068 1.0000
11.500 1.4716 0.02727 0.02092 -0.0449 0.0064 1.0000
11.750 1.4783 0.02855 0.02230 -0.0430 0.0061 1.0000
12.000 1.4832 0.03008 0.02394 -0.0412 0.0058 1.0000
12.250 1.4844 0.03209 0.02607 -0.0396 0.0056 1.0000
12.500 1.4824 0.03460 0.02870 -0.0384 0.0054 1.0000
12.750 1.4838 0.03697 0.03122 -0.0377 0.0053 1.0000
13.000 1.4836 0.03971 0.03410 -0.0373 0.0052 1.0000
13.250 1.4822 0.04277 0.03731 -0.0373 0.0050 1.0000
13.500 1.4792 0.04620 0.04089 -0.0377 0.0049 1.0000
13.750 1.4750 0.04994 0.04478 -0.0383 0.0048 1.0000
14.000 1.4695 0.05399 0.04896 -0.0392 0.0047 1.0000
14.250 1.4626 0.05830 0.05342 -0.0403 0.0047 1.0000
14.500 1.4547 0.06286 0.05812 -0.0415 0.0046 1.0000
14.750 1.4456 0.06765 0.06305 -0.0429 0.0045 1.0000
15.000 1.4360 0.07264 0.06817 -0.0445 0.0044 1.0000
15.250 1.4257 0.07786 0.07352 -0.0462 0.0044 1.0000
15.500 1.4153 0.08320 0.07899 -0.0481 0.0043 1.0000
15.750 1.4046 0.08869 0.08461 -0.0501 0.0043 1.0000
16.000 1.3934 0.09438 0.09043 -0.0522 0.0043 1.0000
16.250 1.3820 0.10017 0.09634 -0.0544 0.0042 1.0000
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Polar data table (+)
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