GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 10K AIRFOIL (goe10k-il) Reynolds number: 500,000 Max Cl/Cd: 74.84 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe10k-il-500000-n5.txt Download as CSV file: xf-goe10k-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 10K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5344 0.09012 0.08788 -0.0113 1.0000 0.0046
-7.750 -0.5369 0.08707 0.08485 -0.0107 1.0000 0.0047
-7.250 -0.5392 0.08079 0.07863 -0.0127 1.0000 0.0048
-7.000 -0.5348 0.07673 0.07457 -0.0157 1.0000 0.0047
-6.750 -0.5300 0.07321 0.07106 -0.0175 1.0000 0.0049
-6.500 -0.5227 0.06922 0.06705 -0.0200 1.0000 0.0049
-6.250 -0.5137 0.06521 0.06301 -0.0222 1.0000 0.0050
-6.000 -0.5032 0.06100 0.05874 -0.0243 1.0000 0.0052
-5.750 -0.4907 0.05681 0.05448 -0.0260 1.0000 0.0052
-5.500 -0.4769 0.05267 0.05024 -0.0273 1.0000 0.0053
-5.250 -0.4618 0.04839 0.04585 -0.0282 1.0000 0.0055
-5.000 -0.4310 0.04306 0.04031 -0.0321 0.9982 0.0056
-4.500 -0.3690 0.03193 0.02858 -0.0368 0.9942 0.0037
-4.250 -0.3393 0.02603 0.02223 -0.0373 0.9917 0.0033
-4.000 -0.3104 0.02211 0.01791 -0.0376 0.9896 0.0035
-3.750 -0.2808 0.01799 0.01325 -0.0373 0.9881 0.0042
-3.500 -0.2517 0.01492 0.00962 -0.0369 0.9868 0.0042
-3.250 -0.2254 0.01287 0.00713 -0.0361 0.9845 0.0042
-3.000 -0.1977 0.01139 0.00533 -0.0357 0.9825 0.0044
-2.750 -0.1695 0.01031 0.00408 -0.0357 0.9807 0.0049
-2.500 -0.1395 0.00977 0.00345 -0.0362 0.9791 0.0063
-2.250 -0.1090 0.00919 0.00278 -0.0368 0.9779 0.0082
-2.000 -0.0829 0.00879 0.00231 -0.0364 0.9745 0.0125
-1.750 -0.0549 0.00835 0.00194 -0.0365 0.9718 0.0430
-1.500 -0.0250 0.00810 0.00178 -0.0372 0.9697 0.0769
-1.250 0.0048 0.00767 0.00165 -0.0380 0.9679 0.1707
-1.000 0.0349 0.00716 0.00154 -0.0389 0.9665 0.3117
-0.500 0.0841 0.00594 0.00138 -0.0380 0.9563 0.6607
-0.250 0.1541 0.00517 0.00148 -0.0473 0.9592 0.9873
0.000 0.1938 0.00513 0.00142 -0.0500 0.9550 1.0000
0.250 0.2292 0.00502 0.00129 -0.0517 0.9431 1.0000
0.500 0.2685 0.00494 0.00121 -0.0543 0.9340 1.0000
0.750 0.3260 0.00476 0.00100 -0.0608 0.9039 1.0000
1.000 0.3652 0.00488 0.00087 -0.0630 0.8202 1.0000
1.250 0.3813 0.00539 0.00089 -0.0601 0.6970 1.0000
1.500 0.3870 0.00667 0.00112 -0.0555 0.4346 1.0000
1.750 0.4052 0.00735 0.00135 -0.0538 0.3007 1.0000
2.000 0.4208 0.00844 0.00164 -0.0517 0.0914 1.0000
2.250 0.4434 0.00882 0.00189 -0.0507 0.0544 1.0000
2.500 0.4652 0.00935 0.00225 -0.0494 0.0116 1.0000
2.750 0.4881 0.00979 0.00277 -0.0483 0.0079 1.0000
3.000 0.5108 0.01026 0.00332 -0.0471 0.0060 1.0000
3.250 0.5324 0.01094 0.00405 -0.0457 0.0051 1.0000
3.500 0.5532 0.01185 0.00510 -0.0440 0.0047 1.0000
3.750 0.5760 0.01244 0.00578 -0.0430 0.0035 1.0000
4.000 0.5971 0.01375 0.00725 -0.0413 0.0032 1.0000
4.250 0.6197 0.01558 0.00941 -0.0396 0.0030 1.0000
4.500 0.6423 0.01797 0.01219 -0.0377 0.0030 1.0000
4.750 0.6633 0.02087 0.01554 -0.0355 0.0030 1.0000
5.000 0.6817 0.02392 0.01901 -0.0331 0.0032 1.0000
5.500 0.7071 0.03375 0.02962 -0.0266 0.0070 1.0000
5.750 0.7220 0.03757 0.03378 -0.0240 0.0070 1.0000
6.000 0.7409 0.04240 0.03900 -0.0209 0.0064 1.0000
6.250 0.7532 0.04673 0.04358 -0.0189 0.0061 1.0000
6.500 0.7638 0.05102 0.04808 -0.0173 0.0058 1.0000
6.750 0.7729 0.05526 0.05250 -0.0161 0.0057 1.0000
7.000 0.7802 0.05954 0.05695 -0.0153 0.0055 1.0000
7.250 0.7849 0.06338 0.06090 -0.0148 0.0052 1.0000
7.500 0.7867 0.06676 0.06438 -0.0145 0.0051 1.0000
7.750 0.7867 0.07383 0.07157 -0.0158 0.0044 1.0000
8.000 0.7843 0.07852 0.07632 -0.0171 0.0044 1.0000
8.250 0.7771 0.08249 0.08033 -0.0178 0.0046 1.0000
8.500 0.7687 0.08616 0.08400 -0.0191 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 10K AIRFOIL (goe10k-il)