GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 200,000 Max Cl/Cd: 72.43 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe142-il-200000-n5.txt Download as CSV file: xf-goe142-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 142 (MVA H.19) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4018 0.10496 0.10140 -0.0072 1.0000 0.0208
-8.250 -0.3982 0.10283 0.09932 -0.0114 1.0000 0.0216
-8.000 -0.3948 0.10020 0.09673 -0.0146 1.0000 0.0217
-7.500 -0.3012 0.07931 0.07616 -0.0247 1.0000 0.0220
-7.250 -0.3019 0.07491 0.07181 -0.0242 1.0000 0.0223
-7.000 -0.3007 0.07148 0.06842 -0.0234 1.0000 0.0225
-6.750 -0.2997 0.06829 0.06527 -0.0232 1.0000 0.0228
-6.500 -0.3002 0.06525 0.06228 -0.0232 1.0000 0.0229
-6.250 -0.3015 0.06237 0.05945 -0.0231 1.0000 0.0231
-6.000 -0.2937 0.05850 0.05557 -0.0257 0.9977 0.0232
-5.750 -0.2710 0.05282 0.04984 -0.0328 0.9922 0.0231
-5.500 -0.2951 0.06468 0.06133 -0.0376 1.0000 0.0219
-5.250 -0.2874 0.06083 0.05751 -0.0368 0.9973 0.0201
-5.000 -0.2511 0.05517 0.05173 -0.0445 0.9921 0.0182
-4.750 -0.2089 0.04870 0.04506 -0.0531 0.9866 0.0172
-4.500 -0.1699 0.04466 0.04086 -0.0589 0.9820 0.0190
-4.250 -0.1293 0.03952 0.03547 -0.0645 0.9760 0.0199
-4.000 -0.0879 0.03432 0.02994 -0.0697 0.9714 0.0194
-3.750 -0.0502 0.02925 0.02446 -0.0730 0.9643 0.0195
-3.500 -0.0109 0.02355 0.01814 -0.0760 0.9585 0.0201
-3.250 0.0248 0.01897 0.01272 -0.0776 0.9516 0.0224
-3.000 0.0581 0.01747 0.01097 -0.0789 0.9438 0.0239
-2.750 0.0896 0.01602 0.00920 -0.0795 0.9340 0.0254
-2.500 0.1216 0.01474 0.00761 -0.0800 0.9245 0.0275
-2.250 0.1527 0.01405 0.00668 -0.0802 0.9136 0.0307
-2.000 0.1813 0.01316 0.00571 -0.0802 0.9006 0.0342
-1.750 0.2096 0.01258 0.00504 -0.0799 0.8866 0.0378
-1.500 0.2374 0.01214 0.00448 -0.0796 0.8718 0.0430
-1.250 0.2646 0.01172 0.00403 -0.0791 0.8557 0.0481
-1.000 0.2916 0.01145 0.00364 -0.0786 0.8381 0.0542
-0.750 0.3184 0.01115 0.00333 -0.0781 0.8195 0.0625
-0.500 0.3451 0.01093 0.00301 -0.0775 0.8000 0.0705
-0.250 0.3718 0.01080 0.00281 -0.0770 0.7784 0.0830
0.250 0.4248 0.01055 0.00248 -0.0760 0.7323 0.1181
0.500 0.4513 0.01044 0.00238 -0.0756 0.7079 0.1590
0.750 0.4689 0.00878 0.00242 -0.0736 0.6853 0.7890
1.250 0.5272 0.00883 0.00225 -0.0734 0.6335 1.0000
1.500 0.5537 0.00902 0.00225 -0.0730 0.6084 1.0000
1.750 0.5800 0.00923 0.00228 -0.0725 0.5833 1.0000
2.000 0.6063 0.00945 0.00233 -0.0721 0.5590 1.0000
2.250 0.6327 0.00967 0.00240 -0.0717 0.5344 1.0000
2.500 0.6590 0.00991 0.00249 -0.0714 0.5110 1.0000
2.750 0.6851 0.01016 0.00262 -0.0710 0.4880 1.0000
3.000 0.7114 0.01041 0.00276 -0.0707 0.4657 1.0000
3.250 0.7375 0.01068 0.00291 -0.0704 0.4444 1.0000
3.500 0.7638 0.01094 0.00309 -0.0701 0.4237 1.0000
3.750 0.7898 0.01122 0.00330 -0.0697 0.4045 1.0000
4.000 0.8159 0.01150 0.00352 -0.0694 0.3862 1.0000
4.250 0.8419 0.01179 0.00375 -0.0691 0.3681 1.0000
4.500 0.8678 0.01209 0.00400 -0.0688 0.3513 1.0000
4.750 0.8937 0.01240 0.00430 -0.0685 0.3353 1.0000
5.000 0.9193 0.01273 0.00459 -0.0682 0.3197 1.0000
5.250 0.9450 0.01306 0.00490 -0.0679 0.3053 1.0000
5.500 0.9705 0.01340 0.00524 -0.0675 0.2911 1.0000
5.750 0.9959 0.01375 0.00562 -0.0672 0.2773 1.0000
6.000 1.0212 0.01411 0.00600 -0.0668 0.2641 1.0000
6.250 1.0463 0.01449 0.00640 -0.0664 0.2508 1.0000
6.500 1.0712 0.01489 0.00682 -0.0660 0.2366 1.0000
6.750 1.0955 0.01534 0.00725 -0.0656 0.2167 1.0000
7.000 1.1191 0.01585 0.00773 -0.0651 0.1935 1.0000
7.250 1.1431 0.01634 0.00822 -0.0647 0.1735 1.0000
7.500 1.1663 0.01691 0.00876 -0.0641 0.1528 1.0000
7.750 1.1889 0.01757 0.00936 -0.0636 0.1272 1.0000
8.000 1.2099 0.01845 0.01010 -0.0628 0.0932 1.0000
8.250 1.2283 0.01968 0.01115 -0.0619 0.0577 1.0000
8.500 1.2466 0.02092 0.01231 -0.0608 0.0387 1.0000
8.750 1.2650 0.02208 0.01350 -0.0596 0.0295 1.0000
9.000 1.2837 0.02314 0.01467 -0.0585 0.0249 1.0000
9.250 1.2995 0.02450 0.01615 -0.0570 0.0217 1.0000
9.500 1.3169 0.02555 0.01738 -0.0558 0.0194 1.0000
9.750 1.3327 0.02671 0.01870 -0.0544 0.0173 1.0000
10.000 1.3441 0.02825 0.02037 -0.0526 0.0159 1.0000
10.250 1.3509 0.03013 0.02239 -0.0502 0.0149 1.0000
10.500 1.3605 0.03162 0.02406 -0.0482 0.0143 1.0000
10.750 1.3661 0.03324 0.02585 -0.0456 0.0138 1.0000
11.000 1.3693 0.03501 0.02779 -0.0430 0.0132 1.0000
11.250 1.3718 0.03691 0.02986 -0.0407 0.0127 1.0000
11.500 1.3740 0.03891 0.03201 -0.0388 0.0121 1.0000
11.750 1.3756 0.04103 0.03428 -0.0373 0.0115 1.0000
12.000 1.3758 0.04341 0.03678 -0.0361 0.0110 1.0000
12.250 1.3733 0.04627 0.03981 -0.0353 0.0106 1.0000
12.500 1.3673 0.04976 0.04344 -0.0347 0.0103 1.0000
12.750 1.3602 0.05366 0.04750 -0.0344 0.0100 1.0000
13.000 1.3562 0.05731 0.05137 -0.0347 0.0099 1.0000
13.250 1.3507 0.06136 0.05563 -0.0354 0.0097 1.0000
13.500 1.3433 0.06583 0.06031 -0.0364 0.0096 1.0000
13.750 1.3345 0.07073 0.06542 -0.0380 0.0095 1.0000
14.000 1.3242 0.07602 0.07091 -0.0399 0.0094 1.0000
14.250 1.3123 0.08175 0.07685 -0.0422 0.0093 1.0000
14.500 1.2996 0.08784 0.08313 -0.0450 0.0093 1.0000
14.750 1.2855 0.09439 0.08987 -0.0481 0.0092 1.0000
15.000 1.2709 0.10133 0.09699 -0.0516 0.0092 1.0000
15.250 1.2556 0.10870 0.10453 -0.0556 0.0092 1.0000
15.500 1.2399 0.11643 0.11243 -0.0598 0.0092 1.0000
15.750 1.2240 0.12456 0.12072 -0.0644 0.0093 1.0000
16.000 1.2078 0.13314 0.12945 -0.0694 0.0093 1.0000
16.250 1.1913 0.14218 0.13863 -0.0748 0.0094 1.0000
16.500 1.1746 0.15176 0.14833 -0.0805 0.0095 1.0000
16.750 1.1573 0.16209 0.15877 -0.0867 0.0096 1.0000
17.000 1.1388 0.17363 0.17038 -0.0936 0.0097 1.0000
17.250 1.1187 0.18675 0.18354 -0.1011 0.0099 1.0000
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