GOE 444 AIRFOIL (goe444-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 444 AIRFOIL (goe444-il) Reynolds number: 50,000 Max Cl/Cd: 16.46 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe444-il-50000-n5.txt Download as CSV file: xf-goe444-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 444 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6463 0.10472 0.09810 0.0068 1.0000 0.1220
-8.500 -0.6538 0.10095 0.09445 0.0040 1.0000 0.1291
-8.000 -0.6621 0.09343 0.08708 0.0002 1.0000 0.1426
-7.500 -0.6491 0.07981 0.07327 -0.0102 1.0000 0.0671
-7.250 -0.6445 0.07382 0.06715 -0.0127 1.0000 0.0495
-7.000 -0.6376 0.06907 0.06224 -0.0137 1.0000 0.0416
-6.750 -0.6327 0.06425 0.05719 -0.0147 1.0000 0.0381
-6.500 -0.6228 0.06003 0.05266 -0.0147 1.0000 0.0343
-6.250 -0.6129 0.05586 0.04828 -0.0144 1.0000 0.0327
-6.000 -0.6011 0.05176 0.04386 -0.0139 1.0000 0.0310
-5.750 -0.5871 0.04777 0.03942 -0.0130 1.0000 0.0294
-5.500 -0.5705 0.04414 0.03524 -0.0117 1.0000 0.0283
-5.250 -0.5529 0.04085 0.03142 -0.0105 1.0000 0.0283
-5.000 -0.5343 0.03775 0.02793 -0.0093 1.0000 0.0297
-4.750 -0.5132 0.03490 0.02461 -0.0080 1.0000 0.0306
-4.500 -0.4901 0.03220 0.02143 -0.0066 1.0000 0.0309
-4.250 -0.4652 0.02964 0.01844 -0.0053 1.0000 0.0311
-4.000 -0.4392 0.02733 0.01576 -0.0040 1.0000 0.0318
-3.750 -0.4128 0.02538 0.01349 -0.0026 1.0000 0.0344
-3.500 -0.3885 0.02360 0.01149 -0.0014 1.0000 0.0399
-3.250 -0.3642 0.02217 0.00975 0.0000 1.0000 0.0448
-3.000 -0.3404 0.02073 0.00808 0.0010 1.0000 0.0581
-2.750 -0.2030 0.01596 0.00620 -0.0150 1.0000 1.0000
-2.500 -0.1856 0.01564 0.00554 -0.0138 1.0000 1.0000
-2.250 -0.1678 0.01537 0.00496 -0.0125 1.0000 1.0000
-2.000 -0.1498 0.01515 0.00447 -0.0112 1.0000 1.0000
-1.750 -0.1314 0.01497 0.00405 -0.0098 1.0000 1.0000
-1.500 -0.1128 0.01482 0.00364 -0.0085 1.0000 1.0000
-1.250 -0.0942 0.01469 0.00335 -0.0071 1.0000 1.0000
-1.000 -0.0754 0.01460 0.00313 -0.0057 1.0000 1.0000
-0.750 -0.0565 0.01452 0.00296 -0.0043 1.0000 1.0000
-0.500 -0.0377 0.01447 0.00282 -0.0029 1.0000 1.0000
-0.250 -0.0188 0.01444 0.00274 -0.0015 1.0000 1.0000
0.000 0.0000 0.01443 0.00272 0.0000 1.0000 1.0000
0.250 0.0188 0.01444 0.00274 0.0015 1.0000 1.0000
0.500 0.0377 0.01447 0.00282 0.0029 1.0000 1.0000
0.750 0.0565 0.01452 0.00296 0.0043 1.0000 1.0000
1.000 0.0753 0.01460 0.00313 0.0057 1.0000 1.0000
1.250 0.0941 0.01470 0.00335 0.0071 1.0000 1.0000
1.500 0.1127 0.01482 0.00363 0.0085 1.0000 1.0000
1.750 0.1313 0.01497 0.00406 0.0099 1.0000 1.0000
2.000 0.1496 0.01516 0.00446 0.0112 1.0000 1.0000
2.250 0.1676 0.01538 0.00496 0.0125 1.0000 1.0000
2.500 0.1853 0.01565 0.00553 0.0138 1.0000 1.0000
2.750 0.2027 0.01597 0.00621 0.0151 1.0000 1.0000
3.000 0.3409 0.02074 0.00811 -0.0011 0.0578 1.0000
3.250 0.3646 0.02216 0.00974 -0.0001 0.0449 1.0000
3.500 0.3889 0.02362 0.01151 0.0013 0.0399 1.0000
3.750 0.4133 0.02539 0.01352 0.0025 0.0342 1.0000
4.000 0.4395 0.02733 0.01577 0.0039 0.0319 1.0000
4.250 0.4655 0.02962 0.01841 0.0052 0.0312 1.0000
4.500 0.4904 0.03217 0.02141 0.0065 0.0310 1.0000
4.750 0.5135 0.03493 0.02465 0.0079 0.0306 1.0000
5.000 0.5343 0.03778 0.02796 0.0093 0.0295 1.0000
5.250 0.5528 0.04085 0.03142 0.0104 0.0283 1.0000
5.500 0.5702 0.04416 0.03523 0.0117 0.0281 1.0000
5.750 0.5869 0.04775 0.03940 0.0130 0.0293 1.0000
6.000 0.6009 0.05177 0.04387 0.0139 0.0310 1.0000
6.250 0.6126 0.05582 0.04825 0.0145 0.0327 1.0000
6.500 0.6224 0.06000 0.05263 0.0148 0.0343 1.0000
6.750 0.6324 0.06414 0.05708 0.0148 0.0380 1.0000
7.000 0.6372 0.06902 0.06220 0.0138 0.0416 1.0000
7.250 0.6438 0.07385 0.06719 0.0128 0.0497 1.0000
7.750 0.5719 0.07062 0.06448 0.0144 0.0479 1.0000
8.000 0.5579 0.07532 0.06916 0.0115 0.0491 1.0000
8.250 0.5476 0.08056 0.07434 0.0076 0.0510 1.0000
8.500 0.5434 0.08555 0.07928 0.0056 0.0549 1.0000
9.000 0.6466 0.10842 0.10174 -0.0081 0.1171 1.0000
9.500 0.6476 0.11632 0.10952 -0.0111 0.1089 1.0000
9.750 0.6476 0.11992 0.11307 -0.0128 0.1040 1.0000
10.000 0.6578 0.12442 0.11759 -0.0122 0.1003 1.0000
10.250 0.6641 0.12953 0.12265 -0.0125 0.0981 1.0000
10.500 0.6531 0.13165 0.12466 -0.0172 0.0941 1.0000
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Polar data table (+)
Polar graphs
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