GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 200,000 Max Cl/Cd: 64.3 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe147-il-200000.txt Download as CSV file: xf-goe147-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3724 0.09388 0.09076 0.0036 1.0000 0.0505
-8.250 -0.3690 0.09039 0.08729 0.0027 1.0000 0.0524
-8.000 -0.4785 0.09791 0.09467 0.0099 1.0000 0.0482
-7.750 -0.4694 0.09492 0.09170 0.0097 1.0000 0.0497
-7.500 -0.4628 0.09181 0.08862 0.0082 1.0000 0.0516
-7.250 -0.4568 0.08837 0.08521 0.0051 1.0000 0.0541
-7.000 -0.4376 0.08240 0.07920 -0.0162 1.0000 0.0571
-6.750 -0.4338 0.07799 0.07485 -0.0115 1.0000 0.0582
-6.500 -0.4215 0.07535 0.07223 -0.0095 1.0000 0.0596
-6.250 -0.4059 0.07219 0.06908 -0.0113 1.0000 0.0622
-6.000 -0.3737 0.06464 0.06135 -0.0279 1.0000 0.0686
-5.750 -0.3615 0.06166 0.05842 -0.0259 1.0000 0.0696
-5.500 -0.3258 0.03302 0.02872 -0.0462 1.0000 0.0358
-5.250 -0.2991 0.02542 0.02018 -0.0496 1.0000 0.0358
-5.000 -0.2720 0.02129 0.01532 -0.0506 1.0000 0.0364
-4.750 -0.2446 0.01833 0.01186 -0.0508 1.0000 0.0369
-4.500 -0.2175 0.01634 0.00963 -0.0507 1.0000 0.0385
-4.250 -0.1903 0.01511 0.00826 -0.0504 1.0000 0.0408
-4.000 -0.1631 0.01422 0.00723 -0.0501 1.0000 0.0452
-3.750 -0.1362 0.01315 0.00612 -0.0497 1.0000 0.0502
-3.500 -0.1093 0.01245 0.00542 -0.0493 1.0000 0.0595
-3.250 -0.0826 0.01288 0.00593 -0.0485 1.0000 0.0917
-3.000 -0.0581 0.01366 0.00669 -0.0478 1.0000 0.1173
-2.750 -0.0302 0.01398 0.00702 -0.0481 0.9968 0.1321
-2.500 0.0170 0.01405 0.00709 -0.0522 0.9759 0.1457
-2.250 0.0602 0.01404 0.00712 -0.0552 0.9462 0.1571
-2.000 0.0976 0.01385 0.00683 -0.0568 0.9080 0.1654
-1.750 0.1257 0.01362 0.00643 -0.0560 0.8662 0.1685
-1.500 0.1507 0.01335 0.00594 -0.0547 0.8272 0.1695
-1.250 0.1759 0.01314 0.00551 -0.0535 0.7934 0.1707
-1.000 0.2019 0.01296 0.00512 -0.0527 0.7634 0.1722
-0.750 0.2285 0.01281 0.00479 -0.0520 0.7361 0.1739
-0.500 0.2554 0.01265 0.00449 -0.0514 0.7110 0.1763
-0.250 0.2822 0.01249 0.00425 -0.0509 0.6884 0.1791
0.000 0.3094 0.01237 0.00406 -0.0504 0.6665 0.1817
0.250 0.3366 0.01230 0.00389 -0.0500 0.6465 0.1851
0.500 0.3640 0.01225 0.00375 -0.0496 0.6256 0.1891
0.750 0.3912 0.01216 0.00362 -0.0493 0.6041 0.1939
1.000 0.4185 0.01213 0.00354 -0.0489 0.5813 0.2012
1.250 0.4457 0.01208 0.00345 -0.0486 0.5579 0.2114
1.500 0.4732 0.01200 0.00338 -0.0483 0.5336 0.2321
1.750 0.5004 0.01169 0.00334 -0.0483 0.5090 0.3090
2.000 0.5215 0.01019 0.00324 -0.0463 0.4836 1.0000
2.250 0.5488 0.01040 0.00324 -0.0460 0.4536 1.0000
2.500 0.5762 0.01064 0.00329 -0.0458 0.4246 1.0000
2.750 0.6035 0.01090 0.00340 -0.0456 0.3990 1.0000
3.000 0.6307 0.01121 0.00354 -0.0454 0.3782 1.0000
3.250 0.6578 0.01153 0.00372 -0.0452 0.3604 1.0000
3.500 0.6849 0.01187 0.00395 -0.0450 0.3452 1.0000
3.750 0.7120 0.01221 0.00421 -0.0448 0.3317 1.0000
4.000 0.7390 0.01258 0.00449 -0.0446 0.3197 1.0000
4.250 0.7658 0.01297 0.00478 -0.0444 0.3086 1.0000
4.500 0.7930 0.01328 0.00511 -0.0443 0.2973 1.0000
4.750 0.8199 0.01364 0.00546 -0.0441 0.2866 1.0000
5.000 0.8466 0.01403 0.00581 -0.0439 0.2761 1.0000
5.250 0.8732 0.01445 0.00617 -0.0437 0.2655 1.0000
5.500 0.9000 0.01478 0.00658 -0.0435 0.2542 1.0000
5.750 0.9264 0.01522 0.00703 -0.0432 0.2433 1.0000
6.000 0.9525 0.01573 0.00751 -0.0430 0.2337 1.0000
6.250 0.9788 0.01618 0.00799 -0.0427 0.2248 1.0000
6.500 1.0050 0.01676 0.00863 -0.0424 0.2176 1.0000
6.750 1.0311 0.01722 0.00911 -0.0422 0.2108 1.0000
7.000 1.0569 0.01748 0.00946 -0.0419 0.2011 1.0000
7.250 1.0825 0.01769 0.00969 -0.0417 0.1912 1.0000
7.500 1.1084 0.01788 0.01000 -0.0415 0.1823 1.0000
7.750 1.1343 0.01812 0.01037 -0.0413 0.1732 1.0000
8.000 1.1599 0.01833 0.01067 -0.0410 0.1628 1.0000
8.250 1.1857 0.01844 0.01083 -0.0409 0.1410 1.0000
8.500 1.2041 0.02015 0.01194 -0.0403 0.0520 1.0000
8.750 1.2219 0.02205 0.01395 -0.0392 0.0393 1.0000
9.000 1.2394 0.02378 0.01588 -0.0382 0.0344 1.0000
9.250 1.2575 0.02520 0.01751 -0.0372 0.0319 1.0000
9.500 1.2728 0.02686 0.01931 -0.0360 0.0300 1.0000
9.750 1.2844 0.02882 0.02137 -0.0346 0.0285 1.0000
10.000 1.2897 0.03145 0.02405 -0.0326 0.0270 1.0000
10.250 1.3007 0.03336 0.02607 -0.0310 0.0259 1.0000
10.500 1.3127 0.03504 0.02792 -0.0296 0.0249 1.0000
10.750 1.3226 0.03703 0.03003 -0.0279 0.0243 1.0000
11.000 1.3315 0.03913 0.03225 -0.0262 0.0237 1.0000
11.250 1.3377 0.04133 0.03458 -0.0243 0.0233 1.0000
11.500 1.3424 0.04374 0.03716 -0.0225 0.0230 1.0000
11.750 1.3456 0.04640 0.03999 -0.0211 0.0228 1.0000
12.000 1.3469 0.04933 0.04312 -0.0199 0.0226 1.0000
12.250 1.3458 0.05250 0.04649 -0.0193 0.0225 1.0000
12.500 1.3425 0.05593 0.05013 -0.0192 0.0222 1.0000
12.750 1.3380 0.05960 0.05397 -0.0196 0.0219 1.0000
13.000 1.3323 0.06358 0.05812 -0.0205 0.0216 1.0000
13.250 1.3245 0.06796 0.06268 -0.0219 0.0213 1.0000
13.500 1.3145 0.07281 0.06770 -0.0239 0.0211 1.0000
13.750 1.3025 0.07816 0.07324 -0.0264 0.0211 1.0000
14.000 1.2884 0.08404 0.07932 -0.0295 0.0211 1.0000
14.250 1.2715 0.09066 0.08617 -0.0332 0.0213 1.0000
14.500 1.2476 0.09887 0.09462 -0.0386 0.0216 1.0000
14.750 1.2214 0.10808 0.10409 -0.0448 0.0221 1.0000
15.000 1.1925 0.11882 0.11507 -0.0521 0.0229 1.0000
15.250 1.1649 0.13002 0.12645 -0.0595 0.0237 1.0000
15.500 1.1386 0.14160 0.13818 -0.0670 0.0246 1.0000
15.750 1.1127 0.15362 0.15030 -0.0745 0.0255 1.0000
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