GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 100,000 Max Cl/Cd: 47.22 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe344-il-100000-n5.txt Download as CSV file: xf-goe344-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 344 (PFALZ 71) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5008 0.09391 0.08868 -0.0133 1.0000 0.0427
-8.250 -0.5064 0.08985 0.08468 -0.0149 1.0000 0.0420
-8.000 -0.5104 0.08538 0.08026 -0.0175 1.0000 0.0414
-7.750 -0.5089 0.08139 0.07627 -0.0195 1.0000 0.0419
-7.500 -0.5053 0.07754 0.07243 -0.0215 1.0000 0.0431
-7.250 -0.5010 0.07313 0.06799 -0.0238 1.0000 0.0441
-7.000 -0.4953 0.06826 0.06306 -0.0262 1.0000 0.0445
-6.750 -0.4875 0.06302 0.05772 -0.0286 1.0000 0.0445
-6.500 -0.4775 0.05748 0.05203 -0.0308 1.0000 0.0449
-6.250 -0.4654 0.05043 0.04466 -0.0335 1.0000 0.0467
-6.000 -0.4534 0.04194 0.03559 -0.0354 1.0000 0.0479
-5.750 -0.4393 0.03546 0.02835 -0.0357 1.0000 0.0485
-5.500 -0.4208 0.03348 0.02623 -0.0350 1.0000 0.0500
-5.250 -0.4003 0.03251 0.02520 -0.0341 1.0000 0.0521
-5.000 -0.3798 0.03008 0.02240 -0.0334 1.0000 0.0538
-4.750 -0.3583 0.02732 0.01915 -0.0327 1.0000 0.0549
-4.500 -0.3356 0.02515 0.01651 -0.0319 1.0000 0.0563
-4.250 -0.3119 0.02344 0.01437 -0.0311 1.0000 0.0581
-4.000 -0.2879 0.02218 0.01279 -0.0303 1.0000 0.0606
-3.750 -0.2643 0.02132 0.01188 -0.0296 1.0000 0.0628
-3.500 -0.2400 0.02044 0.01089 -0.0289 1.0000 0.0648
-3.250 -0.2153 0.01962 0.00992 -0.0282 1.0000 0.0672
-3.000 -0.1904 0.01886 0.00902 -0.0275 1.0000 0.0702
-2.750 -0.1654 0.01817 0.00824 -0.0269 1.0000 0.0737
-2.500 -0.1409 0.01770 0.00780 -0.0263 1.0000 0.0786
-2.250 -0.1162 0.01731 0.00738 -0.0256 1.0000 0.0874
-2.000 -0.0916 0.01702 0.00716 -0.0251 1.0000 0.0981
-1.750 -0.0667 0.01677 0.00695 -0.0245 1.0000 0.1108
-1.500 -0.0418 0.01659 0.00679 -0.0240 1.0000 0.1252
-1.250 -0.0172 0.01651 0.00671 -0.0235 1.0000 0.1425
-1.000 0.0230 0.01627 0.00660 -0.0264 0.9933 0.1688
-0.750 0.0698 0.01583 0.00629 -0.0304 0.9809 0.1927
-0.500 0.1136 0.01545 0.00600 -0.0336 0.9675 0.2176
-0.250 0.1532 0.01508 0.00577 -0.0359 0.9541 0.2475
0.000 0.1906 0.01466 0.00558 -0.0378 0.9404 0.3007
0.250 0.2263 0.01387 0.00533 -0.0394 0.9259 0.4390
0.750 0.3331 0.01255 0.00510 -0.0486 0.8920 1.0000
1.000 0.3702 0.01244 0.00489 -0.0500 0.8614 1.0000
1.250 0.4054 0.01235 0.00469 -0.0509 0.8183 1.0000
1.500 0.4437 0.01229 0.00441 -0.0523 0.7632 1.0000
2.000 0.5032 0.01267 0.00425 -0.0519 0.6641 1.0000
2.250 0.5285 0.01295 0.00433 -0.0509 0.6192 1.0000
2.500 0.5528 0.01327 0.00444 -0.0499 0.5761 1.0000
2.750 0.5766 0.01361 0.00459 -0.0488 0.5358 1.0000
3.000 0.6001 0.01397 0.00477 -0.0478 0.4985 1.0000
3.250 0.6237 0.01434 0.00498 -0.0467 0.4637 1.0000
3.500 0.6473 0.01471 0.00522 -0.0458 0.4322 1.0000
3.750 0.6709 0.01509 0.00548 -0.0448 0.4053 1.0000
4.000 0.6948 0.01548 0.00578 -0.0440 0.3826 1.0000
4.250 0.7186 0.01589 0.00612 -0.0431 0.3634 1.0000
4.500 0.7423 0.01632 0.00648 -0.0423 0.3460 1.0000
4.750 0.7658 0.01677 0.00684 -0.0414 0.3272 1.0000
5.000 0.7893 0.01718 0.00723 -0.0406 0.3065 1.0000
5.250 0.8126 0.01760 0.00764 -0.0397 0.2869 1.0000
5.500 0.8362 0.01801 0.00805 -0.0389 0.2700 1.0000
5.750 0.8598 0.01842 0.00848 -0.0382 0.2536 1.0000
6.000 0.8832 0.01884 0.00892 -0.0374 0.2369 1.0000
6.250 0.9068 0.01924 0.00941 -0.0366 0.2175 1.0000
6.500 0.9298 0.01969 0.00990 -0.0357 0.1963 1.0000
6.750 0.9524 0.02022 0.01044 -0.0349 0.1738 1.0000
7.000 0.9739 0.02089 0.01105 -0.0339 0.1494 1.0000
7.250 0.9951 0.02167 0.01181 -0.0329 0.1274 1.0000
7.500 1.0154 0.02256 0.01268 -0.0317 0.1126 1.0000
7.750 1.0353 0.02351 0.01366 -0.0305 0.1024 1.0000
8.000 1.0540 0.02457 0.01468 -0.0292 0.0940 1.0000
8.250 1.0739 0.02551 0.01578 -0.0280 0.0863 1.0000
8.500 1.0912 0.02669 0.01699 -0.0265 0.0806 1.0000
8.750 1.1104 0.02768 0.01817 -0.0252 0.0738 1.0000
9.000 1.1264 0.02892 0.01941 -0.0238 0.0679 1.0000
9.250 1.1445 0.02998 0.02071 -0.0224 0.0619 1.0000
9.500 1.1590 0.03129 0.02206 -0.0208 0.0569 1.0000
9.750 1.1745 0.03265 0.02369 -0.0192 0.0520 1.0000
10.000 1.1882 0.03397 0.02516 -0.0175 0.0476 1.0000
10.250 1.1989 0.03563 0.02689 -0.0156 0.0439 1.0000
10.500 1.2105 0.03729 0.02885 -0.0136 0.0403 1.0000
10.750 1.2195 0.03888 0.03057 -0.0115 0.0375 1.0000
11.000 1.2251 0.04070 0.03242 -0.0093 0.0354 1.0000
11.250 1.2291 0.04273 0.03482 -0.0067 0.0331 1.0000
11.500 1.2295 0.04476 0.03709 -0.0039 0.0314 1.0000
11.750 1.2285 0.04695 0.03946 -0.0014 0.0302 1.0000
12.000 1.2264 0.04924 0.04193 0.0006 0.0292 1.0000
12.250 1.2232 0.05177 0.04455 0.0022 0.0284 1.0000
12.500 1.2162 0.05504 0.04799 0.0033 0.0277 1.0000
12.750 1.2047 0.05912 0.05241 0.0036 0.0271 1.0000
13.000 1.1907 0.06390 0.05749 0.0026 0.0267 1.0000
13.250 1.1746 0.06953 0.06339 0.0004 0.0263 1.0000
13.500 1.1562 0.07609 0.07021 -0.0031 0.0262 1.0000
13.750 1.1352 0.08374 0.07808 -0.0077 0.0262 1.0000
14.000 1.1113 0.09249 0.08704 -0.0132 0.0265 1.0000
14.250 1.0854 0.10220 0.09688 -0.0192 0.0269 1.0000
14.500 1.0578 0.11275 0.10755 -0.0256 0.0273 1.0000
14.750 1.0294 0.12399 0.11888 -0.0322 0.0278 1.0000
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Polar data table (+)
Polar graphs
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