GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 500,000 Max Cl/Cd: 86.79 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe147-il-500000.txt Download as CSV file: xf-goe147-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 147 (MVA H.6) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4952 0.09535 0.09327 0.0096 1.0000 0.0201
-8.000 -0.4995 0.08937 0.08734 0.0064 1.0000 0.0204
-7.750 -0.4960 0.08580 0.08378 0.0050 1.0000 0.0210
-7.500 -0.4851 0.08295 0.08094 0.0030 1.0000 0.0214
-7.250 -0.4730 0.07972 0.07771 0.0000 1.0000 0.0221
-7.000 -0.4595 0.07588 0.07388 -0.0041 1.0000 0.0229
-6.750 -0.4440 0.07125 0.06923 -0.0095 1.0000 0.0240
-6.500 -0.4185 0.06457 0.06250 -0.0191 1.0000 0.0267
-6.250 -0.4019 0.02867 0.02560 -0.0471 1.0000 0.0179
-6.000 -0.3764 0.02056 0.01640 -0.0503 1.0000 0.0168
-5.750 -0.3495 0.01798 0.01337 -0.0506 1.0000 0.0169
-5.500 -0.3222 0.01635 0.01148 -0.0507 1.0000 0.0174
-5.250 -0.2947 0.01509 0.01001 -0.0506 1.0000 0.0182
-5.000 -0.2670 0.01402 0.00877 -0.0504 1.0000 0.0189
-4.750 -0.2394 0.01323 0.00783 -0.0502 1.0000 0.0196
-4.500 -0.2120 0.01204 0.00648 -0.0501 1.0000 0.0211
-4.250 -0.1849 0.01123 0.00563 -0.0499 1.0000 0.0229
-4.000 -0.1577 0.01065 0.00500 -0.0496 1.0000 0.0245
-3.750 -0.1240 0.01014 0.00443 -0.0506 0.9911 0.0265
-3.500 -0.0824 0.00938 0.00358 -0.0533 0.9554 0.0312
-3.250 -0.0515 0.00905 0.00306 -0.0534 0.9020 0.0374
-3.000 -0.0269 0.00897 0.00305 -0.0520 0.8541 0.0888
-2.750 -0.0009 0.00953 0.00344 -0.0511 0.8120 0.1013
-2.500 0.0258 0.00973 0.00341 -0.0505 0.7755 0.1072
-2.250 0.0529 0.00978 0.00335 -0.0501 0.7408 0.1122
-2.000 0.0804 0.00997 0.00336 -0.0497 0.7078 0.1172
-1.750 0.1080 0.00989 0.00312 -0.0495 0.6784 0.1206
-1.500 0.1357 0.00977 0.00290 -0.0493 0.6528 0.1242
-1.250 0.1636 0.00977 0.00280 -0.0491 0.6300 0.1276
-1.000 0.1916 0.00973 0.00265 -0.0490 0.6088 0.1296
-0.750 0.2198 0.00966 0.00247 -0.0488 0.5901 0.1304
-0.500 0.2480 0.00960 0.00233 -0.0487 0.5737 0.1313
-0.250 0.2762 0.00956 0.00221 -0.0486 0.5582 0.1322
0.250 0.3327 0.00942 0.00196 -0.0485 0.5257 0.1358
0.500 0.3611 0.00938 0.00189 -0.0484 0.5087 0.1378
0.750 0.3894 0.00937 0.00184 -0.0483 0.4904 0.1398
1.000 0.4176 0.00940 0.00180 -0.0483 0.4689 0.1421
1.250 0.4458 0.00946 0.00177 -0.0482 0.4398 0.1446
1.500 0.4737 0.00958 0.00176 -0.0481 0.4021 0.1478
1.750 0.5016 0.00973 0.00181 -0.0481 0.3688 0.1548
2.000 0.5295 0.00987 0.00191 -0.0481 0.3441 0.1698
2.250 0.5575 0.00997 0.00203 -0.0481 0.3265 0.2067
2.500 0.5855 0.01001 0.00215 -0.0482 0.3126 0.2544
2.750 0.6065 0.00841 0.00229 -0.0468 0.3021 1.0000
3.000 0.6344 0.00862 0.00240 -0.0467 0.2918 1.0000
3.250 0.6624 0.00880 0.00252 -0.0467 0.2822 1.0000
3.500 0.6904 0.00897 0.00265 -0.0466 0.2737 1.0000
3.750 0.7182 0.00919 0.00281 -0.0466 0.2651 1.0000
4.000 0.7462 0.00934 0.00295 -0.0465 0.2572 1.0000
4.250 0.7739 0.00955 0.00312 -0.0464 0.2492 1.0000
4.500 0.8018 0.00972 0.00329 -0.0463 0.2410 1.0000
4.750 0.8294 0.00993 0.00347 -0.0463 0.2328 1.0000
5.000 0.8570 0.01015 0.00366 -0.0462 0.2235 1.0000
5.250 0.8846 0.01035 0.00386 -0.0461 0.2140 1.0000
5.500 0.9120 0.01059 0.00410 -0.0460 0.2035 1.0000
5.750 0.9391 0.01087 0.00434 -0.0459 0.1915 1.0000
6.000 0.9661 0.01117 0.00459 -0.0458 0.1786 1.0000
6.250 0.9930 0.01147 0.00484 -0.0457 0.1656 1.0000
6.500 1.0199 0.01177 0.00512 -0.0456 0.1554 1.0000
6.750 1.0467 0.01206 0.00543 -0.0454 0.1485 1.0000
7.000 1.0729 0.01244 0.00576 -0.0453 0.1395 1.0000
7.250 1.0996 0.01272 0.00607 -0.0451 0.1325 1.0000
7.500 1.1258 0.01309 0.00646 -0.0450 0.1239 1.0000
7.750 1.1515 0.01351 0.00685 -0.0448 0.1083 1.0000
8.000 1.1699 0.01548 0.00831 -0.0440 0.0290 1.0000
8.250 1.1940 0.01627 0.00920 -0.0435 0.0233 1.0000
8.500 1.2162 0.01741 0.01046 -0.0429 0.0197 1.0000
8.750 1.2398 0.01815 0.01131 -0.0424 0.0183 1.0000
9.000 1.2628 0.01894 0.01218 -0.0419 0.0167 1.0000
9.250 1.2841 0.01996 0.01330 -0.0412 0.0154 1.0000
9.500 1.3000 0.02174 0.01524 -0.0401 0.0143 1.0000
9.750 1.3173 0.02316 0.01680 -0.0390 0.0138 1.0000
10.000 1.3356 0.02431 0.01808 -0.0381 0.0133 1.0000
10.250 1.3519 0.02562 0.01952 -0.0369 0.0128 1.0000
10.500 1.3672 0.02696 0.02096 -0.0358 0.0122 1.0000
10.750 1.3814 0.02829 0.02238 -0.0346 0.0116 1.0000
11.000 1.3931 0.02975 0.02392 -0.0334 0.0110 1.0000
11.250 1.3992 0.03163 0.02589 -0.0317 0.0107 1.0000
11.500 1.3958 0.03392 0.02829 -0.0290 0.0104 1.0000
11.750 1.3885 0.03684 0.03134 -0.0270 0.0102 1.0000
12.000 1.3795 0.04058 0.03520 -0.0258 0.0100 1.0000
12.250 1.3788 0.04358 0.03835 -0.0257 0.0099 1.0000
12.500 1.3793 0.04665 0.04158 -0.0264 0.0098 1.0000
12.750 1.3785 0.05007 0.04515 -0.0273 0.0097 1.0000
13.000 1.3759 0.05385 0.04908 -0.0285 0.0096 1.0000
13.250 1.3719 0.05794 0.05332 -0.0298 0.0096 1.0000
13.500 1.3663 0.06232 0.05785 -0.0314 0.0095 1.0000
13.750 1.3591 0.06700 0.06268 -0.0331 0.0094 1.0000
14.000 1.3503 0.07198 0.06781 -0.0351 0.0093 1.0000
14.250 1.3400 0.07726 0.07324 -0.0372 0.0093 1.0000
14.500 1.3285 0.08285 0.07898 -0.0396 0.0093 1.0000
14.750 1.3157 0.08879 0.08507 -0.0423 0.0092 1.0000
15.000 1.3024 0.09503 0.09145 -0.0452 0.0093 1.0000
15.250 1.2885 0.10163 0.09820 -0.0485 0.0093 1.0000
15.500 1.2743 0.10862 0.10533 -0.0522 0.0093 1.0000
15.750 1.2596 0.11594 0.11280 -0.0561 0.0093 1.0000
16.000 1.2446 0.12350 0.12050 -0.0603 0.0094 1.0000
16.250 1.2291 0.13148 0.12861 -0.0648 0.0094 1.0000
16.500 1.2137 0.13971 0.13697 -0.0696 0.0095 1.0000
16.750 1.1979 0.14827 0.14566 -0.0747 0.0096 1.0000
17.000 1.1817 0.15731 0.15481 -0.0802 0.0097 1.0000
17.250 1.1644 0.16700 0.16461 -0.0860 0.0098 1.0000
17.500 0.9466 0.14558 0.14319 -0.0533 0.0102 1.0000
17.750 0.9306 0.15171 0.14945 -0.0570 0.0104 1.0000
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