GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 500,000 Max Cl/Cd: 120.72 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe332-il-500000.txt Download as CSV file: xf-goe332-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 332 (PFALZ 61) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.0555 0.07392 0.07138 -0.1030 0.8922 0.0320
-7.750 -0.0437 0.07128 0.06862 -0.1025 0.8724 0.0323
-7.500 -0.0306 0.06914 0.06637 -0.1029 0.8552 0.0326
-7.250 -0.0171 0.06691 0.06407 -0.1042 0.8406 0.0330
-7.000 -0.0028 0.06444 0.06153 -0.1064 0.8277 0.0335
-6.750 0.0129 0.06166 0.05867 -0.1097 0.8162 0.0342
-6.500 0.0307 0.05843 0.05534 -0.1141 0.8056 0.0354
-6.250 0.0600 0.04911 0.04580 -0.1299 0.7953 0.0380
-6.000 0.0771 0.04729 0.04391 -0.1303 0.7866 0.0384
-5.750 0.0966 0.04543 0.04199 -0.1312 0.7773 0.0389
-5.500 0.1181 0.04336 0.03982 -0.1328 0.7691 0.0396
-5.250 0.1416 0.04079 0.03715 -0.1351 0.7605 0.0409
-5.000 0.1735 0.03302 0.02887 -0.1420 0.7538 0.0451
-4.750 0.1957 0.03171 0.02753 -0.1422 0.7454 0.0456
-4.250 0.2438 0.02917 0.02480 -0.1431 0.7305 0.0481
-4.000 0.2716 0.02481 0.01992 -0.1448 0.7240 0.0536
-3.750 0.2965 0.02389 0.01895 -0.1450 0.7170 0.0546
-3.500 0.3222 0.02294 0.01791 -0.1451 0.7100 0.0562
-3.250 0.3513 0.01633 0.01012 -0.1453 0.7050 0.0431
-3.000 0.3784 0.01504 0.00862 -0.1452 0.6982 0.0426
-2.750 0.4058 0.01405 0.00740 -0.1450 0.6917 0.0422
-2.500 0.4333 0.01327 0.00644 -0.1449 0.6852 0.0419
-2.250 0.4608 0.01270 0.00573 -0.1447 0.6783 0.0420
-2.000 0.4883 0.01228 0.00518 -0.1446 0.6722 0.0423
-1.750 0.5159 0.01189 0.00475 -0.1444 0.6659 0.0428
-1.500 0.5435 0.01160 0.00438 -0.1443 0.6602 0.0433
-1.250 0.5712 0.01140 0.00412 -0.1442 0.6548 0.0440
-1.000 0.5986 0.01101 0.00372 -0.1441 0.6491 0.0453
-0.750 0.6261 0.01076 0.00345 -0.1440 0.6436 0.0468
-0.500 0.6538 0.01062 0.00329 -0.1440 0.6386 0.0483
-0.250 0.6815 0.01048 0.00316 -0.1439 0.6331 0.0502
0.000 0.7092 0.01042 0.00305 -0.1438 0.6276 0.0522
0.250 0.7370 0.01031 0.00293 -0.1438 0.6224 0.0572
0.750 0.7922 0.01008 0.00296 -0.1437 0.6115 0.1449
1.000 0.8197 0.01010 0.00299 -0.1437 0.6062 0.1670
1.250 0.8471 0.01005 0.00302 -0.1436 0.6002 0.1907
1.500 0.8738 0.00960 0.00314 -0.1439 0.5945 0.4268
1.750 0.8960 0.00853 0.00328 -0.1425 0.5894 1.0000
2.000 0.9231 0.00860 0.00332 -0.1423 0.5833 1.0000
2.250 0.9499 0.00872 0.00336 -0.1421 0.5772 1.0000
2.500 0.9767 0.00882 0.00342 -0.1419 0.5708 1.0000
2.750 1.0033 0.00892 0.00348 -0.1416 0.5638 1.0000
3.000 1.0298 0.00906 0.00355 -0.1414 0.5575 1.0000
3.250 1.0564 0.00914 0.00364 -0.1412 0.5502 1.0000
3.500 1.0823 0.00930 0.00372 -0.1408 0.5431 1.0000
3.750 1.1085 0.00939 0.00382 -0.1405 0.5349 1.0000
4.250 1.1595 0.00967 0.00403 -0.1397 0.5166 1.0000
4.500 1.1843 0.00983 0.00415 -0.1392 0.5056 1.0000
4.750 1.2083 0.01002 0.00428 -0.1385 0.4936 1.0000
5.000 1.2325 0.01021 0.00444 -0.1378 0.4813 1.0000
5.250 1.2567 0.01042 0.00462 -0.1372 0.4695 1.0000
5.500 1.2802 0.01065 0.00481 -0.1365 0.4580 1.0000
5.750 1.3030 0.01093 0.00502 -0.1357 0.4467 1.0000
6.000 1.3263 0.01118 0.00526 -0.1349 0.4351 1.0000
6.250 1.3493 0.01144 0.00550 -0.1342 0.4245 1.0000
6.500 1.3712 0.01176 0.00577 -0.1332 0.4145 1.0000
6.750 1.3937 0.01203 0.00604 -0.1323 0.4045 1.0000
7.000 1.4155 0.01234 0.00633 -0.1314 0.3945 1.0000
7.250 1.4354 0.01271 0.00665 -0.1301 0.3833 1.0000
7.500 1.4558 0.01304 0.00697 -0.1289 0.3718 1.0000
7.750 1.4758 0.01338 0.00731 -0.1276 0.3611 1.0000
8.000 1.4929 0.01377 0.00766 -0.1258 0.3508 1.0000
8.250 1.5106 0.01415 0.00803 -0.1241 0.3406 1.0000
8.500 1.5286 0.01453 0.00842 -0.1225 0.3311 1.0000
8.750 1.5442 0.01502 0.00888 -0.1206 0.3213 1.0000
9.000 1.5621 0.01542 0.00931 -0.1190 0.3111 1.0000
9.250 1.5783 0.01590 0.00979 -0.1173 0.3011 1.0000
9.500 1.5921 0.01650 0.01036 -0.1152 0.2888 1.0000
9.750 1.6052 0.01715 0.01098 -0.1131 0.2749 1.0000
10.250 1.6288 0.01866 0.01243 -0.1087 0.2433 1.0000
10.500 1.6362 0.01971 0.01340 -0.1060 0.2215 1.0000
10.750 1.6387 0.02112 0.01468 -0.1029 0.1968 1.0000
11.000 1.6372 0.02288 0.01630 -0.0996 0.1721 1.0000
11.250 1.6343 0.02488 0.01817 -0.0965 0.1476 1.0000
11.500 1.6272 0.02735 0.02047 -0.0932 0.1163 1.0000
11.750 1.6128 0.03058 0.02348 -0.0898 0.0853 1.0000
12.250 1.5841 0.03763 0.03025 -0.0842 0.0351 1.0000
12.500 1.5790 0.04056 0.03321 -0.0825 0.0296 1.0000
12.750 1.5759 0.04340 0.03611 -0.0810 0.0269 1.0000
13.000 1.5773 0.04585 0.03866 -0.0799 0.0254 1.0000
13.250 1.5762 0.04863 0.04154 -0.0789 0.0242 1.0000
13.500 1.5721 0.05183 0.04482 -0.0778 0.0232 1.0000
13.750 1.5661 0.05534 0.04843 -0.0770 0.0223 1.0000
14.000 1.5656 0.05827 0.05147 -0.0763 0.0218 1.0000
14.250 1.5634 0.06148 0.05478 -0.0758 0.0212 1.0000
14.500 1.5602 0.06488 0.05829 -0.0754 0.0207 1.0000
14.750 1.5554 0.06855 0.06205 -0.0751 0.0202 1.0000
15.000 1.5492 0.07243 0.06604 -0.0749 0.0197 1.0000
15.250 1.5410 0.07667 0.07037 -0.0748 0.0193 1.0000
15.500 1.5299 0.08141 0.07521 -0.0749 0.0189 1.0000
15.750 1.5158 0.08663 0.08054 -0.0752 0.0185 1.0000
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Polar data table (+)
Polar graphs
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