GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 474 AIRFOIL (goe474-il) Reynolds number: 200,000 Max Cl/Cd: 77.12 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe474-il-200000.txt Download as CSV file: xf-goe474-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 474 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4293 0.08817 0.08462 -0.0266 1.0000 0.0529
-8.000 -0.4334 0.08523 0.08176 -0.0276 1.0000 0.0550
-7.750 -0.4470 0.08238 0.07901 -0.0298 1.0000 0.0567
-7.500 -0.4559 0.07793 0.07456 -0.0388 1.0000 0.0579
-7.250 -0.4600 0.07279 0.06946 -0.0387 1.0000 0.0588
-7.000 -0.4549 0.07081 0.06753 -0.0346 1.0000 0.0600
-6.750 -0.4510 0.06873 0.06547 -0.0325 1.0000 0.0614
-6.500 -0.4488 0.06652 0.06327 -0.0314 1.0000 0.0638
-6.250 -0.4490 0.06159 0.05798 -0.0388 1.0000 0.0700
-6.000 -0.4506 0.05764 0.05419 -0.0355 1.0000 0.0715
-5.750 -0.4457 0.05650 0.05312 -0.0320 1.0000 0.0733
-5.500 -0.4395 0.05426 0.05085 -0.0306 1.0000 0.0760
-5.250 -0.4355 0.03367 0.02910 -0.0364 1.0000 0.0440
-5.000 -0.4234 0.02516 0.01948 -0.0356 1.0000 0.0401
-4.750 -0.3907 0.02164 0.01523 -0.0370 0.9971 0.0406
-4.500 -0.3553 0.02014 0.01332 -0.0387 0.9938 0.0444
-4.250 -0.3213 0.01867 0.01143 -0.0397 0.9900 0.0464
-4.000 -0.2884 0.01680 0.00937 -0.0409 0.9869 0.0501
-3.750 -0.2508 0.01616 0.00861 -0.0429 0.9837 0.0564
-3.500 -0.2189 0.01523 0.00764 -0.0438 0.9787 0.0620
-3.250 -0.1833 0.01475 0.00714 -0.0454 0.9741 0.0725
-3.000 -0.1447 0.01441 0.00687 -0.0476 0.9708 0.0915
-2.750 -0.1127 0.01446 0.00694 -0.0484 0.9645 0.1280
-2.500 -0.0755 0.01457 0.00696 -0.0505 0.9597 0.1487
-2.250 -0.0355 0.01452 0.00686 -0.0531 0.9566 0.1633
-2.000 -0.0068 0.01440 0.00674 -0.0534 0.9495 0.1746
-1.750 0.0298 0.01417 0.00649 -0.0553 0.9455 0.1846
-1.500 0.0700 0.01400 0.00629 -0.0579 0.9428 0.1958
-1.250 0.0981 0.01374 0.00612 -0.0581 0.9356 0.2063
-1.000 0.1350 0.01342 0.00587 -0.0599 0.9317 0.2174
-0.750 0.1749 0.01307 0.00562 -0.0624 0.9292 0.2308
-0.500 0.2057 0.01279 0.00544 -0.0630 0.9223 0.2469
-0.250 0.2438 0.01223 0.00512 -0.0649 0.9168 0.2855
0.000 0.3404 0.01001 0.00490 -0.0788 0.9222 1.0000
0.250 0.3790 0.00983 0.00463 -0.0806 0.9157 1.0000
0.500 0.4092 0.00972 0.00447 -0.0807 0.9053 1.0000
0.750 0.4405 0.00954 0.00424 -0.0807 0.8939 1.0000
1.000 0.4686 0.00938 0.00402 -0.0800 0.8806 1.0000
1.250 0.4946 0.00928 0.00388 -0.0790 0.8672 1.0000
1.500 0.5206 0.00924 0.00379 -0.0780 0.8553 1.0000
1.750 0.5444 0.00925 0.00379 -0.0768 0.8424 1.0000
2.000 0.5682 0.00922 0.00373 -0.0754 0.8275 1.0000
2.250 0.5907 0.00920 0.00368 -0.0737 0.8092 1.0000
2.500 0.6136 0.00920 0.00365 -0.0721 0.7904 1.0000
2.750 0.6372 0.00922 0.00367 -0.0707 0.7727 1.0000
3.000 0.6611 0.00926 0.00368 -0.0694 0.7544 1.0000
3.250 0.6837 0.00932 0.00375 -0.0679 0.7319 1.0000
3.500 0.7064 0.00939 0.00379 -0.0664 0.7059 1.0000
3.750 0.7283 0.00951 0.00385 -0.0647 0.6716 1.0000
4.000 0.7488 0.00971 0.00391 -0.0627 0.6245 1.0000
4.250 0.7668 0.01007 0.00401 -0.0603 0.5477 1.0000
4.500 0.7782 0.01092 0.00423 -0.0569 0.4315 1.0000
4.750 0.7918 0.01185 0.00472 -0.0542 0.3505 1.0000
5.000 0.8078 0.01271 0.00524 -0.0521 0.2828 1.0000
5.250 0.8252 0.01352 0.00576 -0.0503 0.2358 1.0000
5.500 0.8442 0.01423 0.00630 -0.0488 0.2044 1.0000
5.750 0.8639 0.01491 0.00685 -0.0474 0.1828 1.0000
6.000 0.8838 0.01561 0.00748 -0.0461 0.1665 1.0000
6.250 0.9048 0.01619 0.00803 -0.0449 0.1514 1.0000
6.500 0.9264 0.01667 0.00852 -0.0439 0.1367 1.0000
6.750 0.9481 0.01712 0.00901 -0.0429 0.1222 1.0000
7.000 0.9699 0.01755 0.00948 -0.0419 0.1053 1.0000
7.250 0.9885 0.01835 0.01020 -0.0404 0.0840 1.0000
7.500 1.0072 0.01923 0.01104 -0.0389 0.0612 1.0000
7.750 1.0241 0.02035 0.01210 -0.0371 0.0491 1.0000
8.000 1.0417 0.02151 0.01335 -0.0352 0.0430 1.0000
8.250 1.0566 0.02314 0.01494 -0.0333 0.0384 1.0000
8.500 1.0757 0.02431 0.01628 -0.0318 0.0352 1.0000
8.750 1.0943 0.02572 0.01783 -0.0304 0.0328 1.0000
9.000 1.1125 0.02736 0.01954 -0.0290 0.0309 1.0000
9.250 1.1309 0.03022 0.02254 -0.0279 0.0293 1.0000
9.500 1.1468 0.03273 0.02537 -0.0263 0.0282 1.0000
9.750 1.1611 0.03441 0.02736 -0.0244 0.0270 1.0000
10.000 1.1724 0.03676 0.03004 -0.0222 0.0260 1.0000
10.250 1.1797 0.03956 0.03321 -0.0197 0.0255 1.0000
10.500 1.1814 0.04275 0.03680 -0.0168 0.0254 1.0000
10.750 1.1767 0.04615 0.04060 -0.0135 0.0253 1.0000
11.000 1.1641 0.04946 0.04425 -0.0093 0.0254 1.0000
11.250 1.1468 0.05297 0.04806 -0.0056 0.0256 1.0000
11.500 1.1273 0.05676 0.05212 -0.0028 0.0259 1.0000
11.750 1.1050 0.06111 0.05672 -0.0012 0.0261 1.0000
12.000 1.0827 0.06585 0.06166 -0.0011 0.0264 1.0000
12.250 1.0583 0.07147 0.06748 -0.0026 0.0266 1.0000
12.500 1.0327 0.07820 0.07437 -0.0059 0.0268 1.0000
12.750 1.0062 0.08635 0.08268 -0.0112 0.0271 1.0000
13.000 0.9774 0.09698 0.09343 -0.0189 0.0276 1.0000
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Polar data table (+)
Polar graphs
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