GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 200,000 Max Cl/Cd: 70.12 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe143-il-200000-n5.txt Download as CSV file: xf-goe143-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4110 0.09288 0.08940 -0.0114 1.0000 0.0217
-8.000 -0.4099 0.08876 0.08533 -0.0142 1.0000 0.0225
-7.750 -0.4094 0.08430 0.08092 -0.0178 1.0000 0.0228
-7.500 -0.4045 0.07866 0.07530 -0.0241 1.0000 0.0231
-7.250 -0.3953 0.07429 0.07095 -0.0283 1.0000 0.0236
-7.000 -0.3825 0.07247 0.06913 -0.0287 1.0000 0.0242
-6.750 -0.3697 0.07007 0.06674 -0.0304 1.0000 0.0253
-6.500 -0.3575 0.06653 0.06319 -0.0336 1.0000 0.0268
-6.250 -0.3450 0.06160 0.05822 -0.0382 1.0000 0.0279
-6.000 -0.3299 0.05497 0.05147 -0.0442 1.0000 0.0288
-5.750 -0.3077 0.04977 0.04611 -0.0490 0.9983 0.0305
-5.500 -0.2733 0.04831 0.04460 -0.0524 0.9927 0.0325
-5.250 -0.2301 0.04238 0.03837 -0.0604 0.9860 0.0343
-5.000 -0.1839 0.03322 0.02843 -0.0687 0.9780 0.0378
-4.750 -0.1503 0.03060 0.02561 -0.0717 0.9694 0.0387
-4.500 -0.1165 0.02907 0.02394 -0.0740 0.9622 0.0398
-4.250 -0.0849 0.02752 0.02222 -0.0755 0.9520 0.0418
-4.000 -0.0520 0.02483 0.01915 -0.0773 0.9420 0.0429
-3.750 -0.0190 0.02236 0.01628 -0.0786 0.9319 0.0437
-3.500 0.0122 0.02037 0.01391 -0.0794 0.9197 0.0446
-3.250 0.0423 0.01895 0.01215 -0.0797 0.9061 0.0461
-3.000 0.0719 0.01799 0.01087 -0.0798 0.8917 0.0472
-2.750 0.1006 0.01702 0.00964 -0.0797 0.8769 0.0476
-2.500 0.1284 0.01564 0.00803 -0.0796 0.8620 0.0485
-2.250 0.1556 0.01485 0.00709 -0.0792 0.8465 0.0496
-2.000 0.1827 0.01429 0.00642 -0.0787 0.8311 0.0506
-1.750 0.2096 0.01383 0.00584 -0.0783 0.8152 0.0519
-1.500 0.2366 0.01342 0.00533 -0.0778 0.7991 0.0532
-1.250 0.2636 0.01310 0.00491 -0.0774 0.7823 0.0553
-1.000 0.2907 0.01284 0.00456 -0.0769 0.7643 0.0579
-0.750 0.3177 0.01256 0.00418 -0.0765 0.7450 0.0596
-0.500 0.3446 0.01224 0.00378 -0.0760 0.7243 0.0610
-0.250 0.3715 0.01194 0.00346 -0.0757 0.7009 0.0636
0.000 0.3984 0.01181 0.00325 -0.0753 0.6757 0.0664
0.250 0.4253 0.01175 0.00307 -0.0748 0.6492 0.0699
0.500 0.4521 0.01173 0.00294 -0.0745 0.6223 0.0750
0.750 0.4790 0.01175 0.00288 -0.0742 0.5961 0.0817
1.000 0.5060 0.01178 0.00281 -0.0738 0.5716 0.0893
1.250 0.5331 0.01182 0.00276 -0.0736 0.5486 0.1023
1.500 0.5599 0.01183 0.00274 -0.0733 0.5248 0.1311
2.000 0.6083 0.01023 0.00288 -0.0718 0.4782 1.0000
2.250 0.6350 0.01049 0.00296 -0.0715 0.4564 1.0000
2.500 0.6618 0.01075 0.00306 -0.0713 0.4378 1.0000
2.750 0.6887 0.01099 0.00318 -0.0710 0.4199 1.0000
3.000 0.7155 0.01123 0.00332 -0.0708 0.4023 1.0000
3.250 0.7423 0.01147 0.00347 -0.0706 0.3858 1.0000
3.500 0.7692 0.01170 0.00364 -0.0704 0.3716 1.0000
3.750 0.7961 0.01194 0.00383 -0.0702 0.3591 1.0000
4.000 0.8228 0.01218 0.00402 -0.0700 0.3463 1.0000
4.250 0.8495 0.01243 0.00423 -0.0697 0.3326 1.0000
4.750 0.9024 0.01296 0.00472 -0.0693 0.3020 1.0000
5.000 0.9286 0.01326 0.00498 -0.0690 0.2838 1.0000
5.250 0.9544 0.01361 0.00528 -0.0687 0.2615 1.0000
5.500 0.9796 0.01403 0.00562 -0.0683 0.2344 1.0000
5.750 1.0040 0.01456 0.00601 -0.0679 0.2033 1.0000
6.000 1.0282 0.01515 0.00648 -0.0675 0.1768 1.0000
6.500 1.0759 0.01635 0.00754 -0.0666 0.1440 1.0000
7.000 1.1237 0.01745 0.00860 -0.0656 0.1223 1.0000
7.250 1.1473 0.01800 0.00917 -0.0652 0.1137 1.0000
7.500 1.1709 0.01853 0.00972 -0.0647 0.1051 1.0000
7.750 1.1948 0.01900 0.01025 -0.0642 0.0963 1.0000
8.000 1.2180 0.01956 0.01080 -0.0636 0.0819 1.0000
8.250 1.2343 0.02102 0.01187 -0.0624 0.0328 1.0000
8.500 1.2533 0.02211 0.01308 -0.0613 0.0266 1.0000
8.750 1.2721 0.02318 0.01428 -0.0601 0.0231 1.0000
9.000 1.2888 0.02447 0.01573 -0.0587 0.0203 1.0000
9.250 1.3074 0.02543 0.01685 -0.0576 0.0191 1.0000
9.500 1.3242 0.02652 0.01812 -0.0562 0.0179 1.0000
9.750 1.3393 0.02771 0.01946 -0.0548 0.0167 1.0000
10.000 1.3520 0.02903 0.02092 -0.0532 0.0156 1.0000
10.250 1.3590 0.03073 0.02278 -0.0510 0.0146 1.0000
10.500 1.3597 0.03261 0.02480 -0.0481 0.0141 1.0000
10.750 1.3639 0.03416 0.02649 -0.0457 0.0137 1.0000
11.000 1.3660 0.03598 0.02845 -0.0435 0.0134 1.0000
11.250 1.3669 0.03805 0.03067 -0.0416 0.0131 1.0000
11.500 1.3668 0.04041 0.03315 -0.0402 0.0128 1.0000
11.750 1.3662 0.04300 0.03588 -0.0392 0.0125 1.0000
12.000 1.3655 0.04578 0.03880 -0.0386 0.0121 1.0000
12.250 1.3644 0.04876 0.04190 -0.0383 0.0118 1.0000
12.500 1.3629 0.05194 0.04521 -0.0384 0.0115 1.0000
12.750 1.3605 0.05536 0.04875 -0.0388 0.0112 1.0000
13.000 1.3573 0.05902 0.05256 -0.0395 0.0109 1.0000
13.250 1.3533 0.06291 0.05655 -0.0404 0.0106 1.0000
13.500 1.3481 0.06701 0.06076 -0.0413 0.0104 1.0000
13.750 1.3422 0.07125 0.06509 -0.0423 0.0102 1.0000
14.000 1.3360 0.07547 0.06940 -0.0429 0.0100 1.0000
14.250 1.3304 0.07976 0.07382 -0.0437 0.0099 1.0000
14.500 1.3244 0.08434 0.07856 -0.0452 0.0098 1.0000
14.750 1.3177 0.08914 0.08352 -0.0468 0.0098 1.0000
15.000 1.3097 0.09433 0.08888 -0.0488 0.0097 1.0000
15.250 1.3013 0.09973 0.09444 -0.0511 0.0096 1.0000
15.500 1.2921 0.10543 0.10032 -0.0536 0.0095 1.0000
15.750 1.2820 0.11144 0.10650 -0.0565 0.0095 1.0000
16.000 1.2716 0.11773 0.11295 -0.0596 0.0094 1.0000
16.250 1.2609 0.12429 0.11967 -0.0631 0.0094 1.0000
16.500 1.2497 0.13116 0.12671 -0.0670 0.0094 1.0000
16.750 1.2384 0.13830 0.13400 -0.0711 0.0094 1.0000
17.000 1.2267 0.14583 0.14169 -0.0756 0.0094 1.0000
17.250 1.2150 0.15371 0.14972 -0.0805 0.0094 1.0000
17.500 1.2031 0.16203 0.15818 -0.0857 0.0094 1.0000
17.750 1.1906 0.17091 0.16720 -0.0914 0.0095 1.0000
18.000 1.1776 0.18042 0.17683 -0.0975 0.0095 1.0000
18.250 1.1640 0.19079 0.18732 -0.1041 0.0096 1.0000
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