GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 50,000 Max Cl/Cd: 34.17 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe599-il-50000.txt Download as CSV file: xf-goe599-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5091 0.09793 0.09091 -0.0061 1.0000 0.3419
-8.000 -0.4847 0.09255 0.08545 -0.0056 1.0000 0.3473
-7.750 -0.5965 0.07246 0.06561 -0.0358 1.0000 0.1645
-7.500 -0.6027 0.06523 0.05823 -0.0380 1.0000 0.1475
-7.250 -0.6136 0.05794 0.05051 -0.0399 1.0000 0.1352
-7.000 -0.6095 0.05276 0.04502 -0.0396 1.0000 0.1301
-6.750 -0.6090 0.04708 0.03821 -0.0392 1.0000 0.1237
-6.500 -0.5929 0.04374 0.03496 -0.0382 1.0000 0.1276
-6.250 -0.5777 0.04048 0.03129 -0.0370 1.0000 0.1304
-6.000 -0.5600 0.03715 0.02744 -0.0359 1.0000 0.1319
-5.750 -0.5403 0.03428 0.02397 -0.0347 1.0000 0.1362
-5.500 -0.5194 0.03197 0.02153 -0.0337 1.0000 0.1447
-5.250 -0.4960 0.02970 0.01877 -0.0325 1.0000 0.1527
-5.000 -0.4732 0.02791 0.01695 -0.0315 1.0000 0.1672
-4.750 -0.4499 0.02624 0.01535 -0.0303 1.0000 0.1859
-4.500 -0.4267 0.02466 0.01387 -0.0291 1.0000 0.2195
-4.250 -0.4044 0.02272 0.01242 -0.0277 1.0000 0.2982
-4.000 -0.3873 0.02110 0.01167 -0.0253 1.0000 0.4298
-3.750 -0.3750 0.02058 0.01182 -0.0211 1.0000 0.5512
-3.500 -0.3629 0.02028 0.01187 -0.0161 1.0000 0.6441
-3.250 -0.3495 0.01992 0.01170 -0.0113 1.0000 0.7184
-3.000 -0.3363 0.01963 0.01151 -0.0064 1.0000 0.7883
-2.750 -0.3163 0.01952 0.01142 -0.0023 1.0000 0.8651
-2.500 -0.1414 0.02038 0.01128 -0.0266 1.0000 0.9873
-2.250 -0.1219 0.01958 0.01030 -0.0288 1.0000 1.0000
-2.000 -0.1385 0.01895 0.00962 -0.0237 1.0000 1.0000
-1.750 -0.1406 0.01864 0.00914 -0.0202 1.0000 1.0000
-1.500 -0.1303 0.01857 0.00885 -0.0184 1.0000 1.0000
-1.250 -0.1149 0.01863 0.00869 -0.0173 1.0000 1.0000
-1.000 -0.0972 0.01875 0.00861 -0.0165 1.0000 1.0000
-0.750 -0.0783 0.01893 0.00862 -0.0158 1.0000 1.0000
-0.500 -0.0587 0.01916 0.00869 -0.0152 1.0000 1.0000
-0.250 -0.0387 0.01943 0.00883 -0.0148 1.0000 1.0000
0.000 -0.0185 0.01973 0.00902 -0.0143 1.0000 1.0000
0.250 0.0018 0.02008 0.00927 -0.0140 1.0000 1.0000
0.500 0.0221 0.02047 0.00959 -0.0137 1.0000 1.0000
0.750 0.0424 0.02091 0.00997 -0.0135 1.0000 1.0000
1.000 0.0625 0.02139 0.01040 -0.0133 1.0000 1.0000
1.250 0.0824 0.02193 0.01091 -0.0131 1.0000 1.0000
1.500 0.1020 0.02252 0.01149 -0.0130 1.0000 1.0000
1.750 0.1213 0.02317 0.01215 -0.0130 1.0000 1.0000
2.000 0.1402 0.02390 0.01290 -0.0131 1.0000 1.0000
2.250 0.1585 0.02470 0.01374 -0.0132 1.0000 1.0000
2.500 0.1763 0.02559 0.01468 -0.0134 1.0000 1.0000
2.750 0.2355 0.02704 0.01627 -0.0213 0.9832 1.0000
3.000 0.2885 0.02820 0.01759 -0.0278 0.9615 1.0000
3.250 0.3456 0.02932 0.01891 -0.0347 0.9415 1.0000
3.500 0.3895 0.03014 0.01996 -0.0388 0.9184 1.0000
3.750 0.4398 0.03090 0.02097 -0.0437 0.8974 1.0000
4.000 0.4954 0.03095 0.02135 -0.0481 0.8678 1.0000
4.250 0.5831 0.02848 0.01940 -0.0533 0.8232 1.0000
4.500 0.6514 0.02520 0.01659 -0.0532 0.7774 1.0000
4.750 0.6914 0.02294 0.01458 -0.0495 0.7261 1.0000
5.000 0.7142 0.02164 0.01344 -0.0443 0.6610 1.0000
5.250 0.7233 0.02117 0.01215 -0.0357 0.4635 1.0000
5.500 0.7228 0.02388 0.01313 -0.0302 0.2713 1.0000
5.750 0.7402 0.02571 0.01439 -0.0284 0.2245 1.0000
6.000 0.7672 0.02733 0.01585 -0.0278 0.2021 1.0000
6.250 0.8008 0.02912 0.01755 -0.0280 0.1873 1.0000
6.500 0.8335 0.03112 0.01953 -0.0284 0.1728 1.0000
6.750 0.8663 0.03351 0.02208 -0.0285 0.1642 1.0000
7.000 0.8950 0.03624 0.02483 -0.0285 0.1537 1.0000
7.250 0.9177 0.03872 0.02786 -0.0272 0.1470 1.0000
7.500 0.9407 0.04199 0.03126 -0.0265 0.1388 1.0000
7.750 0.9565 0.04507 0.03501 -0.0244 0.1354 1.0000
8.000 0.9705 0.04832 0.03872 -0.0224 0.1307 1.0000
8.250 0.9900 0.05251 0.04294 -0.0217 0.1263 1.0000
8.500 0.9911 0.05626 0.04752 -0.0185 0.1282 1.0000
8.750 0.9868 0.06089 0.05282 -0.0157 0.1309 1.0000
9.000 0.9789 0.06585 0.05825 -0.0134 0.1336 1.0000
9.250 0.9709 0.07092 0.06363 -0.0118 0.1361 1.0000
9.500 0.9664 0.07617 0.06906 -0.0106 0.1384 1.0000
9.750 0.9162 0.08277 0.07604 -0.0100 0.1505 1.0000
10.000 0.8636 0.09171 0.08506 -0.0144 0.1639 1.0000
10.250 0.8005 0.10975 0.10292 -0.0314 0.2074 1.0000
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Polar data table (+)
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