GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 415 AIRFOIL (goe415-il) Reynolds number: 50,000 Max Cl/Cd: 33.98 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe415-il-50000.txt Download as CSV file: xf-goe415-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 415 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4203 0.10228 0.09612 0.0001 1.0000 0.2055
-7.500 -0.4270 0.10091 0.09487 -0.0020 1.0000 0.2159
-7.250 -0.4209 0.09763 0.09162 -0.0019 1.0000 0.2297
-7.000 -0.4165 0.09464 0.08872 -0.0027 1.0000 0.2440
-6.750 -0.4139 0.09196 0.08611 -0.0044 1.0000 0.2586
-6.500 -0.3943 0.08694 0.08112 0.0000 1.0000 0.2772
-6.250 -0.3863 0.08381 0.07807 0.0006 1.0000 0.2956
-6.000 -0.3902 0.08210 0.07647 -0.0025 1.0000 0.3155
-5.750 -0.3729 0.07766 0.07208 0.0017 1.0000 0.3361
-5.500 -0.3701 0.07503 0.06955 0.0018 1.0000 0.3605
-5.000 -0.3553 0.06911 0.06380 0.0066 1.0000 0.4180
-4.750 -0.3448 0.06596 0.06072 0.0105 1.0000 0.4507
-4.500 -0.3402 0.06326 0.05810 0.0144 1.0000 0.4901
-3.500 -0.1912 0.03867 0.03113 -0.0435 1.0000 0.1600
-3.250 -0.1641 0.03520 0.02721 -0.0439 1.0000 0.1448
-3.000 -0.1379 0.03216 0.02377 -0.0440 1.0000 0.1350
-2.750 -0.1107 0.02984 0.02097 -0.0437 1.0000 0.1267
-2.500 -0.0833 0.02778 0.01839 -0.0433 1.0000 0.1207
-2.250 -0.0568 0.02648 0.01657 -0.0426 1.0000 0.1179
-2.000 -0.0325 0.02492 0.01498 -0.0423 1.0000 0.1218
-1.750 -0.0091 0.02400 0.01389 -0.0418 1.0000 0.1281
-1.500 0.0145 0.02334 0.01303 -0.0413 1.0000 0.1319
-1.250 0.0390 0.02274 0.01242 -0.0416 1.0000 0.1399
-1.000 0.0609 0.02255 0.01223 -0.0421 1.0000 0.1581
-0.750 0.1140 0.02041 0.01182 -0.0480 0.9904 0.4497
-0.500 0.1840 0.01951 0.01122 -0.0546 0.9603 1.0000
-0.250 0.2561 0.01988 0.01102 -0.0631 0.9310 1.0000
0.000 0.3206 0.02002 0.01077 -0.0696 0.9029 1.0000
0.250 0.3697 0.02011 0.01060 -0.0728 0.8744 1.0000
0.500 0.4079 0.02021 0.01049 -0.0737 0.8461 1.0000
0.750 0.4397 0.02033 0.01041 -0.0733 0.8188 1.0000
1.000 0.4686 0.02048 0.01038 -0.0724 0.7928 1.0000
1.250 0.4961 0.02064 0.01037 -0.0712 0.7686 1.0000
1.500 0.5232 0.02082 0.01037 -0.0698 0.7462 1.0000
1.750 0.5480 0.02124 0.01067 -0.0685 0.7226 1.0000
2.000 0.5737 0.02161 0.01087 -0.0672 0.7021 1.0000
2.250 0.5979 0.02223 0.01140 -0.0662 0.6803 1.0000
2.500 0.6231 0.02277 0.01181 -0.0650 0.6617 1.0000
2.750 0.6475 0.02349 0.01250 -0.0642 0.6429 1.0000
3.000 0.6719 0.02425 0.01323 -0.0635 0.6252 1.0000
3.250 0.6965 0.02502 0.01396 -0.0628 0.6090 1.0000
3.500 0.7211 0.02585 0.01477 -0.0621 0.5939 1.0000
3.750 0.7455 0.02677 0.01576 -0.0616 0.5798 1.0000
4.000 0.7694 0.02776 0.01679 -0.0611 0.5661 1.0000
4.250 0.7930 0.02884 0.01794 -0.0606 0.5530 1.0000
4.500 0.8164 0.03001 0.01920 -0.0602 0.5409 1.0000
4.750 0.8399 0.03115 0.02041 -0.0597 0.5291 1.0000
5.000 0.8641 0.03215 0.02152 -0.0589 0.5177 1.0000
5.250 0.8869 0.03327 0.02275 -0.0582 0.5050 1.0000
5.500 0.9092 0.03425 0.02383 -0.0573 0.4907 1.0000
5.750 0.9315 0.03519 0.02488 -0.0562 0.4763 1.0000
6.000 0.9532 0.03624 0.02612 -0.0553 0.4622 1.0000
6.250 0.9739 0.03750 0.02757 -0.0544 0.4486 1.0000
6.500 0.9937 0.03895 0.02924 -0.0536 0.4352 1.0000
6.750 1.0129 0.04045 0.03095 -0.0528 0.4217 1.0000
7.000 1.0311 0.04213 0.03287 -0.0519 0.4083 1.0000
7.250 1.0463 0.04442 0.03543 -0.0513 0.3959 1.0000
7.500 1.0597 0.04698 0.03832 -0.0507 0.3840 1.0000
7.750 1.0738 0.04939 0.04098 -0.0499 0.3727 1.0000
8.000 1.0914 0.05081 0.04261 -0.0486 0.3595 1.0000
8.250 1.1359 0.04490 0.03658 -0.0443 0.3296 1.0000
8.500 1.1750 0.04092 0.03246 -0.0417 0.3073 1.0000
8.750 1.1919 0.04073 0.03262 -0.0398 0.2882 1.0000
9.000 1.2141 0.03800 0.02997 -0.0372 0.2605 1.0000
9.250 1.2262 0.03609 0.02817 -0.0342 0.2250 1.0000
9.500 1.2274 0.03663 0.02889 -0.0315 0.1731 1.0000
9.750 1.2202 0.03929 0.03107 -0.0290 0.1265 1.0000
10.000 1.2107 0.04268 0.03416 -0.0267 0.1070 1.0000
10.250 1.2022 0.04588 0.03733 -0.0247 0.0956 1.0000
10.500 1.1957 0.04922 0.04071 -0.0233 0.0881 1.0000
10.750 1.1905 0.05262 0.04414 -0.0226 0.0827 1.0000
11.000 1.1884 0.05600 0.04759 -0.0218 0.0787 1.0000
11.250 1.1894 0.05930 0.05115 -0.0210 0.0751 1.0000
11.500 1.1922 0.06244 0.05437 -0.0201 0.0720 1.0000
11.750 1.2037 0.06493 0.05680 -0.0179 0.0691 1.0000
12.000 1.2055 0.06891 0.06115 -0.0174 0.0680 1.0000
12.250 1.2004 0.07365 0.06620 -0.0179 0.0673 1.0000
12.500 1.1898 0.07911 0.07195 -0.0195 0.0670 1.0000
12.750 1.1748 0.08534 0.07843 -0.0220 0.0671 1.0000
13.000 1.1566 0.09234 0.08566 -0.0254 0.0676 1.0000
13.250 1.1369 0.09995 0.09344 -0.0294 0.0682 1.0000
13.500 1.1170 0.10798 0.10160 -0.0337 0.0689 1.0000
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Polar data table (+)
Polar graphs
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