GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 50,000 Max Cl/Cd: 30.5 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe598-il-50000-n5.txt Download as CSV file: xf-goe598-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 598 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6100 0.10522 0.09851 0.0039 1.0000 0.0457
-8.750 -0.6087 0.10073 0.09407 0.0016 1.0000 0.0448
-8.250 -0.6155 0.08800 0.08149 -0.0118 1.0000 0.0387
-8.000 -0.6126 0.08297 0.07647 -0.0149 1.0000 0.0385
-7.750 -0.6094 0.07790 0.07136 -0.0179 1.0000 0.0383
-7.500 -0.6055 0.07276 0.06615 -0.0208 1.0000 0.0381
-7.250 -0.6002 0.06759 0.06085 -0.0235 1.0000 0.0380
-7.000 -0.5930 0.06246 0.05551 -0.0257 1.0000 0.0379
-6.750 -0.5835 0.05741 0.05018 -0.0274 1.0000 0.0377
-6.500 -0.5714 0.05250 0.04492 -0.0286 1.0000 0.0375
-6.250 -0.5567 0.04777 0.03967 -0.0293 1.0000 0.0374
-6.000 -0.5394 0.04325 0.03462 -0.0295 1.0000 0.0375
-5.750 -0.5195 0.03902 0.02973 -0.0294 1.0000 0.0383
-5.500 -0.4992 0.03584 0.02622 -0.0292 1.0000 0.0414
-5.250 -0.4762 0.03306 0.02300 -0.0288 1.0000 0.0451
-5.000 -0.4510 0.02999 0.01933 -0.0280 1.0000 0.0475
-4.750 -0.4270 0.02788 0.01700 -0.0274 1.0000 0.0540
-4.500 -0.4009 0.02591 0.01458 -0.0263 1.0000 0.0617
-4.250 -0.3762 0.02440 0.01284 -0.0255 1.0000 0.0747
-4.000 -0.3515 0.02277 0.01105 -0.0245 1.0000 0.0881
-3.750 -0.3265 0.02117 0.00934 -0.0238 1.0000 0.1065
-3.500 -0.3032 0.01970 0.00809 -0.0234 1.0000 0.1544
-3.250 -0.2800 0.01826 0.00704 -0.0230 1.0000 0.2415
-3.000 -0.2627 0.01650 0.00649 -0.0213 1.0000 0.4794
-2.750 -0.2468 0.01561 0.00626 -0.0176 1.0000 0.6757
-2.500 -0.2201 0.01510 0.00601 -0.0152 1.0000 0.8392
-2.250 -0.1444 0.01482 0.00524 -0.0238 1.0000 1.0000
-2.000 -0.1258 0.01470 0.00484 -0.0226 1.0000 1.0000
-1.750 -0.1064 0.01462 0.00451 -0.0215 1.0000 1.0000
-1.500 -0.0865 0.01457 0.00424 -0.0204 1.0000 1.0000
-1.250 -0.0661 0.01455 0.00400 -0.0194 1.0000 1.0000
-1.000 -0.0454 0.01456 0.00385 -0.0185 1.0000 1.0000
-0.750 -0.0244 0.01460 0.00375 -0.0176 1.0000 1.0000
-0.500 -0.0034 0.01466 0.00370 -0.0168 1.0000 1.0000
-0.250 0.0177 0.01475 0.00370 -0.0160 1.0000 1.0000
0.000 0.0388 0.01488 0.00375 -0.0153 1.0000 1.0000
0.250 0.0598 0.01504 0.00387 -0.0146 1.0000 1.0000
0.500 0.0809 0.01523 0.00404 -0.0140 1.0000 1.0000
0.750 0.1020 0.01547 0.00427 -0.0134 1.0000 1.0000
1.000 0.1229 0.01574 0.00456 -0.0130 1.0000 1.0000
1.250 0.1438 0.01606 0.00490 -0.0126 1.0000 1.0000
1.500 0.1771 0.01641 0.00534 -0.0146 0.9927 1.0000
1.750 0.2180 0.01678 0.00587 -0.0181 0.9806 1.0000
2.000 0.2605 0.01713 0.00640 -0.0218 0.9674 1.0000
2.250 0.3074 0.01738 0.00695 -0.0259 0.9480 1.0000
2.500 0.3577 0.01752 0.00742 -0.0302 0.9272 1.0000
2.750 0.3972 0.01767 0.00791 -0.0323 0.9062 1.0000
3.000 0.4374 0.01769 0.00837 -0.0340 0.8806 1.0000
3.250 0.4751 0.01751 0.00857 -0.0340 0.8425 1.0000
3.500 0.5052 0.01744 0.00886 -0.0326 0.8006 1.0000
3.750 0.5265 0.01726 0.00878 -0.0280 0.7099 1.0000
4.000 0.5288 0.01863 0.00816 -0.0199 0.3271 1.0000
4.250 0.5419 0.02198 0.00987 -0.0186 0.0853 1.0000
4.500 0.5641 0.02380 0.01155 -0.0177 0.0593 1.0000
4.750 0.5867 0.02553 0.01348 -0.0165 0.0510 1.0000
5.000 0.6090 0.02748 0.01545 -0.0154 0.0429 1.0000
5.250 0.6351 0.02929 0.01761 -0.0141 0.0395 1.0000
5.500 0.6616 0.03156 0.02024 -0.0131 0.0373 1.0000
5.750 0.6862 0.03403 0.02291 -0.0123 0.0345 1.0000
6.000 0.7099 0.03688 0.02622 -0.0114 0.0322 1.0000
6.250 0.7324 0.04002 0.02996 -0.0103 0.0311 1.0000
6.500 0.7522 0.04360 0.03409 -0.0092 0.0309 1.0000
6.750 0.7690 0.04746 0.03849 -0.0082 0.0309 1.0000
7.000 0.7826 0.05160 0.04314 -0.0073 0.0312 1.0000
7.250 0.7931 0.05593 0.04791 -0.0067 0.0315 1.0000
7.500 0.8007 0.06039 0.05275 -0.0062 0.0319 1.0000
7.750 0.8054 0.06494 0.05760 -0.0060 0.0323 1.0000
8.000 0.8073 0.06953 0.06243 -0.0061 0.0326 1.0000
8.250 0.8069 0.07412 0.06721 -0.0065 0.0329 1.0000
8.500 0.8047 0.07872 0.07194 -0.0071 0.0332 1.0000
8.750 0.8017 0.08330 0.07660 -0.0079 0.0334 1.0000
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Polar data table (+)
Polar graphs
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