GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 200,000 Max Cl/Cd: 73.04 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe310-il-200000-n5.txt Download as CSV file: xf-goe310-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 310 (MVA H.42) 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 -0.3452 0.09106 0.08770 -0.0348 1.0000 0.0191
-8.250 -0.3456 0.08951 0.08620 -0.0327 1.0000 0.0183
-8.000 -0.3549 0.08444 0.08119 -0.0372 0.9957 0.0193
-7.750 -0.3428 0.07924 0.07599 -0.0431 0.9878 0.0193
-7.500 -0.3270 0.07448 0.07121 -0.0485 0.9806 0.0192
-7.250 -0.3119 0.06759 0.06427 -0.0564 0.9725 0.0193
-6.750 -0.2747 0.05855 0.05512 -0.0659 0.9583 0.0201
-6.500 -0.2497 0.05650 0.05302 -0.0689 0.9529 0.0217
-6.250 -0.2268 0.05062 0.04699 -0.0745 0.9457 0.0230
-6.000 -0.2070 0.04098 0.03703 -0.0808 0.9373 0.0233
-5.750 -0.1964 0.02904 0.02400 -0.0842 0.9268 0.0241
-5.500 -0.1721 0.02560 0.01975 -0.0849 0.9208 0.0261
-5.250 -0.1509 0.02372 0.01771 -0.0844 0.9124 0.0273
-5.000 -0.1231 0.02196 0.01561 -0.0847 0.9064 0.0284
-4.750 -0.0990 0.02063 0.01397 -0.0841 0.8977 0.0298
-4.500 -0.0694 0.01955 0.01253 -0.0844 0.8908 0.0317
-4.250 -0.0443 0.01864 0.01132 -0.0837 0.8808 0.0325
-4.000 -0.0158 0.01785 0.01025 -0.0836 0.8721 0.0331
-3.750 0.0101 0.01632 0.00861 -0.0833 0.8624 0.0347
-3.500 0.0358 0.01550 0.00772 -0.0828 0.8512 0.0361
-3.250 0.0625 0.01485 0.00697 -0.0824 0.8395 0.0368
-3.000 0.0893 0.01429 0.00631 -0.0820 0.8268 0.0374
-2.750 0.1159 0.01382 0.00576 -0.0815 0.8135 0.0381
-2.500 0.1425 0.01343 0.00527 -0.0811 0.7993 0.0388
-2.250 0.1691 0.01312 0.00484 -0.0806 0.7842 0.0399
-2.000 0.1959 0.01286 0.00445 -0.0802 0.7688 0.0414
-1.750 0.2225 0.01265 0.00410 -0.0797 0.7536 0.0420
-1.500 0.2491 0.01248 0.00379 -0.0792 0.7394 0.0424
-1.250 0.2754 0.01232 0.00350 -0.0787 0.7257 0.0434
-1.000 0.3014 0.01220 0.00327 -0.0782 0.7126 0.0448
-0.750 0.3271 0.01211 0.00309 -0.0776 0.7002 0.0469
-0.500 0.3527 0.01201 0.00294 -0.0770 0.6891 0.0506
-0.250 0.3769 0.01172 0.00287 -0.0763 0.6788 0.1142
0.000 0.4022 0.01170 0.00290 -0.0757 0.6687 0.1440
0.250 0.4278 0.01174 0.00295 -0.0752 0.6594 0.1709
0.500 0.4536 0.01182 0.00299 -0.0747 0.6509 0.1921
0.750 0.4789 0.01185 0.00303 -0.0741 0.6417 0.2015
1.000 0.5038 0.01190 0.00303 -0.0734 0.6310 0.2099
1.250 0.5283 0.01196 0.00304 -0.0727 0.6192 0.2201
1.500 0.5523 0.01198 0.00308 -0.0719 0.6074 0.2326
1.750 0.5765 0.01199 0.00314 -0.0711 0.5981 0.2491
2.000 0.6004 0.01203 0.00318 -0.0703 0.5881 0.2619
2.250 0.6234 0.01200 0.00327 -0.0693 0.5767 0.2947
2.500 0.6456 0.01191 0.00338 -0.0681 0.5641 0.3770
3.000 0.7950 0.01125 0.00376 -0.0890 0.5068 1.0000
3.250 0.8166 0.01142 0.00386 -0.0877 0.4894 1.0000
3.500 0.8382 0.01160 0.00398 -0.0865 0.4728 1.0000
3.750 0.8590 0.01181 0.00412 -0.0850 0.4530 1.0000
4.000 0.8794 0.01204 0.00427 -0.0835 0.4270 1.0000
4.250 0.8976 0.01238 0.00444 -0.0817 0.3903 1.0000
4.500 0.9135 0.01287 0.00469 -0.0794 0.3427 1.0000
4.750 0.9281 0.01349 0.00506 -0.0771 0.2931 1.0000
5.000 0.9440 0.01407 0.00544 -0.0750 0.2557 1.0000
5.250 0.9607 0.01460 0.00583 -0.0730 0.2267 1.0000
5.500 0.9779 0.01509 0.00623 -0.0711 0.2028 1.0000
5.750 0.9953 0.01557 0.00665 -0.0693 0.1830 1.0000
6.000 1.0123 0.01605 0.00707 -0.0674 0.1630 1.0000
6.250 1.0294 0.01652 0.00750 -0.0655 0.1457 1.0000
6.500 1.0459 0.01702 0.00795 -0.0636 0.1271 1.0000
6.750 1.0556 0.01794 0.00864 -0.0606 0.0755 1.0000
7.000 1.0690 0.01861 0.00924 -0.0581 0.0690 1.0000
7.250 1.0829 0.01922 0.00989 -0.0558 0.0644 1.0000
7.500 1.0944 0.01996 0.01069 -0.0531 0.0601 1.0000
7.750 1.1052 0.02070 0.01149 -0.0502 0.0566 1.0000
8.000 1.1171 0.02126 0.01217 -0.0475 0.0538 1.0000
8.250 1.1258 0.02196 0.01299 -0.0444 0.0506 1.0000
8.500 1.1296 0.02296 0.01407 -0.0407 0.0474 1.0000
8.750 1.1414 0.02359 0.01482 -0.0383 0.0448 1.0000
9.000 1.1538 0.02422 0.01556 -0.0361 0.0405 1.0000
9.250 1.1642 0.02501 0.01643 -0.0337 0.0369 1.0000
9.500 1.1811 0.02544 0.01695 -0.0323 0.0301 1.0000
9.750 1.1932 0.02618 0.01779 -0.0303 0.0249 1.0000
10.000 1.2030 0.02709 0.01871 -0.0282 0.0216 1.0000
10.250 1.2109 0.02817 0.01980 -0.0260 0.0190 1.0000
10.500 1.2140 0.02963 0.02129 -0.0235 0.0172 1.0000
10.750 1.2168 0.03119 0.02299 -0.0212 0.0165 1.0000
11.000 1.2192 0.03288 0.02480 -0.0191 0.0156 1.0000
11.250 1.2208 0.03473 0.02677 -0.0171 0.0149 1.0000
11.500 1.2219 0.03672 0.02888 -0.0154 0.0144 1.0000
11.750 1.2233 0.03879 0.03106 -0.0139 0.0138 1.0000
12.000 1.2244 0.04098 0.03338 -0.0126 0.0133 1.0000
12.250 1.2235 0.04348 0.03597 -0.0114 0.0128 1.0000
12.500 1.2214 0.04618 0.03877 -0.0103 0.0122 1.0000
12.750 1.2221 0.04868 0.04140 -0.0093 0.0115 1.0000
13.000 1.2241 0.05108 0.04393 -0.0085 0.0113 1.0000
13.250 1.2256 0.05361 0.04662 -0.0077 0.0110 1.0000
13.500 1.2266 0.05628 0.04943 -0.0070 0.0107 1.0000
13.750 1.2264 0.05914 0.05246 -0.0064 0.0104 1.0000
14.000 1.2263 0.06207 0.05555 -0.0060 0.0102 1.0000
14.250 1.2250 0.06524 0.05889 -0.0056 0.0100 1.0000
14.500 1.2221 0.06866 0.06249 -0.0056 0.0097 1.0000
14.750 1.2188 0.07223 0.06624 -0.0058 0.0096 1.0000
15.000 1.2136 0.07617 0.07037 -0.0063 0.0095 1.0000
15.250 1.2073 0.08038 0.07476 -0.0070 0.0094 1.0000
15.500 1.1991 0.08500 0.07957 -0.0080 0.0093 1.0000
15.750 1.1901 0.08988 0.08463 -0.0095 0.0092 1.0000
16.000 1.1793 0.09527 0.09022 -0.0113 0.0092 1.0000
16.250 1.1681 0.10086 0.09597 -0.0135 0.0090 1.0000
16.500 1.1556 0.10695 0.10224 -0.0162 0.0090 1.0000
16.750 1.1405 0.11387 0.10937 -0.0194 0.0090 1.0000
17.000 1.1276 0.12057 0.11621 -0.0229 0.0089 1.0000
17.250 1.1097 0.12881 0.12465 -0.0273 0.0089 1.0000
17.500 1.0853 0.13927 0.13535 -0.0332 0.0091 1.0000
17.750 1.0545 0.15246 0.14875 -0.0409 0.0095 1.0000
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