GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 100,000 Max Cl/Cd: 49.93 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe147-il-100000-n5.txt Download as CSV file: xf-goe147-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4606 0.11440 0.10965 0.0127 1.0000 0.0463
-8.750 -0.4555 0.11079 0.10607 0.0111 1.0000 0.0459
-8.500 -0.4597 0.10402 0.09933 0.0057 1.0000 0.0287
-8.250 -0.4522 0.10046 0.09579 0.0053 1.0000 0.0278
-8.000 -0.4469 0.09681 0.09219 0.0039 1.0000 0.0271
-7.750 -0.4425 0.09311 0.08854 0.0020 1.0000 0.0266
-7.500 -0.4386 0.08935 0.08483 -0.0004 1.0000 0.0264
-7.250 -0.4315 0.08516 0.08069 -0.0041 1.0000 0.0265
-7.000 -0.4220 0.08065 0.07621 -0.0085 1.0000 0.0267
-6.750 -0.4101 0.07587 0.07145 -0.0133 1.0000 0.0269
-6.500 -0.3959 0.07078 0.06636 -0.0185 1.0000 0.0269
-6.250 -0.3793 0.06536 0.06092 -0.0240 1.0000 0.0266
-6.000 -0.3598 0.05949 0.05499 -0.0298 1.0000 0.0263
-5.750 -0.3369 0.05283 0.04820 -0.0361 1.0000 0.0261
-5.500 -0.3093 0.04386 0.03894 -0.0439 1.0000 0.0259
-5.250 -0.2746 0.02972 0.02366 -0.0536 1.0000 0.0259
-5.000 -0.2459 0.02538 0.01853 -0.0555 1.0000 0.0279
-4.750 -0.2183 0.02283 0.01544 -0.0561 1.0000 0.0298
-4.500 -0.1918 0.02084 0.01318 -0.0563 1.0000 0.0319
-4.250 -0.1651 0.01946 0.01156 -0.0562 1.0000 0.0348
-4.000 -0.1385 0.01826 0.01010 -0.0560 1.0000 0.0400
-3.750 -0.1123 0.01714 0.00894 -0.0557 1.0000 0.0470
-3.500 -0.0867 0.01662 0.00861 -0.0554 1.0000 0.0628
-3.250 -0.0618 0.01697 0.00881 -0.0545 1.0000 0.0944
-3.000 -0.0227 0.01733 0.00902 -0.0570 0.9840 0.1177
-2.750 0.0180 0.01756 0.00915 -0.0596 0.9607 0.1363
-2.500 0.0587 0.01748 0.00894 -0.0621 0.9298 0.1480
-2.250 0.0978 0.01702 0.00813 -0.0638 0.8922 0.1538
-2.000 0.1295 0.01657 0.00749 -0.0639 0.8527 0.1555
-1.750 0.1574 0.01625 0.00697 -0.0632 0.8188 0.1570
-1.500 0.1842 0.01599 0.00654 -0.0624 0.7881 0.1587
-1.250 0.2106 0.01578 0.00615 -0.0616 0.7595 0.1606
-1.000 0.2372 0.01559 0.00580 -0.0609 0.7329 0.1631
-0.750 0.2639 0.01546 0.00549 -0.0602 0.7078 0.1666
-0.500 0.2905 0.01532 0.00526 -0.0596 0.6848 0.1698
-0.250 0.3170 0.01520 0.00506 -0.0590 0.6628 0.1729
0.000 0.3436 0.01512 0.00486 -0.0584 0.6427 0.1766
0.250 0.3705 0.01507 0.00469 -0.0578 0.6227 0.1812
0.500 0.3973 0.01502 0.00460 -0.0573 0.6035 0.1865
0.750 0.4244 0.01503 0.00450 -0.0569 0.5846 0.1949
1.000 0.4515 0.01503 0.00445 -0.0565 0.5657 0.2059
1.250 0.4788 0.01503 0.00442 -0.0562 0.5466 0.2231
1.500 0.5060 0.01500 0.00443 -0.0559 0.5275 0.2515
1.750 0.5330 0.01486 0.00447 -0.0558 0.5078 0.3214
2.250 0.5823 0.01374 0.00450 -0.0537 0.4635 1.0000
2.500 0.6092 0.01398 0.00459 -0.0534 0.4372 1.0000
2.750 0.6358 0.01425 0.00468 -0.0531 0.4099 1.0000
3.000 0.6622 0.01457 0.00480 -0.0527 0.3837 1.0000
3.500 0.7148 0.01530 0.00522 -0.0521 0.3438 1.0000
3.750 0.7412 0.01568 0.00550 -0.0519 0.3303 1.0000
4.250 0.7941 0.01645 0.00620 -0.0514 0.3071 1.0000
4.500 0.8205 0.01685 0.00658 -0.0511 0.2968 1.0000
4.750 0.8465 0.01729 0.00698 -0.0508 0.2874 1.0000
5.000 0.8728 0.01769 0.00745 -0.0506 0.2773 1.0000
5.250 0.8988 0.01814 0.00792 -0.0503 0.2682 1.0000
5.500 0.9246 0.01860 0.00839 -0.0500 0.2592 1.0000
5.750 0.9506 0.01905 0.00896 -0.0497 0.2499 1.0000
6.000 0.9759 0.01957 0.00947 -0.0493 0.2418 1.0000
6.250 1.0016 0.02006 0.01008 -0.0490 0.2329 1.0000
6.500 1.0267 0.02062 0.01068 -0.0487 0.2258 1.0000
6.750 1.0521 0.02118 0.01141 -0.0483 0.2185 1.0000
7.000 1.0768 0.02181 0.01207 -0.0479 0.2133 1.0000
7.250 1.1020 0.02246 0.01292 -0.0475 0.2076 1.0000
7.500 1.1268 0.02313 0.01374 -0.0471 0.2029 1.0000
7.750 1.1511 0.02379 0.01445 -0.0467 0.1982 1.0000
8.000 1.1749 0.02412 0.01507 -0.0463 0.1866 1.0000
8.250 1.1979 0.02427 0.01537 -0.0459 0.1670 1.0000
8.500 1.2209 0.02470 0.01592 -0.0456 0.1480 1.0000
8.750 1.2421 0.02548 0.01669 -0.0451 0.1200 1.0000
9.000 1.2534 0.02796 0.01864 -0.0442 0.0443 1.0000
9.250 1.2642 0.03051 0.02127 -0.0428 0.0325 1.0000
9.500 1.2763 0.03261 0.02363 -0.0415 0.0282 1.0000
9.750 1.2832 0.03514 0.02637 -0.0401 0.0257 1.0000
10.000 1.2920 0.03713 0.02866 -0.0388 0.0238 1.0000
10.250 1.2964 0.03940 0.03118 -0.0374 0.0221 1.0000
10.500 1.2949 0.04189 0.03390 -0.0358 0.0209 1.0000
10.750 1.2879 0.04485 0.03714 -0.0346 0.0203 1.0000
11.000 1.2789 0.04864 0.04113 -0.0350 0.0199 1.0000
11.250 1.2685 0.05331 0.04601 -0.0368 0.0196 1.0000
11.500 1.2571 0.05873 0.05162 -0.0396 0.0194 1.0000
11.750 1.2447 0.06461 0.05767 -0.0426 0.0192 1.0000
12.000 1.2319 0.07063 0.06385 -0.0456 0.0191 1.0000
12.250 1.2196 0.07656 0.06992 -0.0483 0.0189 1.0000
12.500 1.2087 0.08218 0.07565 -0.0505 0.0188 1.0000
12.750 1.2002 0.08724 0.08081 -0.0523 0.0185 1.0000
13.000 1.1944 0.09159 0.08522 -0.0533 0.0182 1.0000
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Polar data table (+)
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