GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 50,000 Max Cl/Cd: 30.68 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe676-il-50000.txt Download as CSV file: xf-goe676-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4418 0.10367 0.09649 -0.0015 1.0000 0.3423
-8.500 -0.4395 0.10088 0.09374 -0.0010 1.0000 0.3602
-8.250 -0.4532 0.09919 0.09216 -0.0004 1.0000 0.3792
-8.000 -0.4178 0.09452 0.08742 0.0014 1.0000 0.4040
-7.000 -0.3777 0.08280 0.07580 0.0066 1.0000 0.5012
-6.750 -0.3641 0.07990 0.07291 0.0082 1.0000 0.5312
-6.500 -0.3545 0.07722 0.07027 0.0099 1.0000 0.5604
-6.250 -0.5661 0.05637 0.04874 -0.0227 1.0000 0.2038
-6.000 -0.5608 0.05173 0.04381 -0.0214 1.0000 0.1897
-5.750 -0.5505 0.04843 0.04031 -0.0197 1.0000 0.1824
-5.500 -0.5462 0.04510 0.03606 -0.0175 1.0000 0.1719
-5.250 -0.5332 0.04237 0.03310 -0.0158 1.0000 0.1709
-5.000 -0.5201 0.04014 0.03044 -0.0140 1.0000 0.1716
-4.750 -0.5046 0.03787 0.02786 -0.0125 1.0000 0.1728
-4.500 -0.4869 0.03575 0.02548 -0.0112 1.0000 0.1737
-4.250 -0.4677 0.03389 0.02340 -0.0101 1.0000 0.1755
-4.000 -0.4481 0.03241 0.02177 -0.0090 1.0000 0.1806
-3.750 -0.4276 0.03117 0.02014 -0.0080 1.0000 0.1867
-3.500 -0.4056 0.02973 0.01860 -0.0073 1.0000 0.1924
-3.250 -0.3829 0.02867 0.01739 -0.0066 1.0000 0.2008
-3.000 -0.3596 0.02764 0.01637 -0.0061 1.0000 0.2133
-2.750 -0.3348 0.02671 0.01545 -0.0057 1.0000 0.2278
-2.500 -0.1175 0.02242 0.01434 -0.0292 1.0000 1.0000
-2.250 -0.1235 0.02250 0.01422 -0.0251 1.0000 1.0000
-2.000 -0.1277 0.02263 0.01416 -0.0213 1.0000 1.0000
-1.750 -0.1299 0.02280 0.01415 -0.0177 1.0000 1.0000
-1.500 -0.1298 0.02301 0.01418 -0.0145 1.0000 1.0000
-1.250 -0.1274 0.02327 0.01426 -0.0117 1.0000 1.0000
-1.000 -0.1230 0.02356 0.01436 -0.0091 1.0000 1.0000
-0.750 -0.1167 0.02390 0.01453 -0.0070 1.0000 1.0000
-0.500 -0.1085 0.02429 0.01476 -0.0051 1.0000 1.0000
-0.250 -0.0740 0.02501 0.01527 -0.0082 0.9928 1.0000
0.000 -0.0213 0.02590 0.01595 -0.0145 0.9776 1.0000
0.250 0.0286 0.02673 0.01661 -0.0201 0.9619 1.0000
0.500 0.0766 0.02750 0.01724 -0.0251 0.9460 1.0000
0.750 0.1227 0.02820 0.01785 -0.0296 0.9298 1.0000
1.000 0.1676 0.02885 0.01842 -0.0337 0.9135 1.0000
1.250 0.2111 0.02945 0.01896 -0.0373 0.8971 1.0000
1.500 0.2539 0.02999 0.01948 -0.0406 0.8807 1.0000
1.750 0.2962 0.03050 0.01998 -0.0437 0.8644 1.0000
2.000 0.3388 0.03095 0.02044 -0.0467 0.8481 1.0000
2.250 0.3798 0.03138 0.02089 -0.0492 0.8319 1.0000
2.500 0.4160 0.03178 0.02133 -0.0507 0.8158 1.0000
2.750 0.4485 0.03220 0.02179 -0.0514 0.7998 1.0000
3.000 0.4770 0.03269 0.02232 -0.0515 0.7839 1.0000
3.250 0.5035 0.03321 0.02287 -0.0512 0.7682 1.0000
3.500 0.5271 0.03382 0.02353 -0.0504 0.7529 1.0000
3.750 0.5487 0.03450 0.02426 -0.0495 0.7378 1.0000
4.000 0.5692 0.03526 0.02507 -0.0484 0.7231 1.0000
4.250 0.5885 0.03611 0.02598 -0.0472 0.7090 1.0000
4.500 0.6088 0.03696 0.02690 -0.0461 0.6956 1.0000
4.750 0.6346 0.03756 0.02759 -0.0455 0.6834 1.0000
5.000 0.6683 0.03765 0.02778 -0.0453 0.6719 1.0000
5.250 0.6849 0.03857 0.02880 -0.0437 0.6572 1.0000
5.500 0.7070 0.03904 0.02936 -0.0421 0.6420 1.0000
5.750 0.7418 0.03827 0.02872 -0.0407 0.6254 1.0000
6.000 0.7812 0.03682 0.02738 -0.0390 0.6071 1.0000
6.250 0.7991 0.03710 0.02777 -0.0366 0.5878 1.0000
6.500 0.8229 0.03713 0.02791 -0.0347 0.5707 1.0000
6.750 0.8464 0.03731 0.02825 -0.0329 0.5542 1.0000
7.000 0.8711 0.03728 0.02836 -0.0311 0.5361 1.0000
7.250 0.9050 0.03629 0.02748 -0.0294 0.5159 1.0000
7.500 0.9308 0.03586 0.02718 -0.0272 0.4928 1.0000
7.750 0.9669 0.03457 0.02588 -0.0253 0.4658 1.0000
8.000 0.9897 0.03428 0.02560 -0.0226 0.4329 1.0000
8.250 1.0096 0.03435 0.02563 -0.0198 0.3963 1.0000
8.500 1.0341 0.03371 0.02463 -0.0172 0.3572 1.0000
8.750 1.0441 0.03418 0.02503 -0.0139 0.3221 1.0000
9.000 1.0554 0.03483 0.02557 -0.0110 0.2897 1.0000
9.250 1.0651 0.03573 0.02635 -0.0080 0.2586 1.0000
9.500 1.0729 0.03695 0.02743 -0.0050 0.2279 1.0000
9.750 1.0807 0.03862 0.02889 -0.0021 0.1994 1.0000
10.000 1.0947 0.04075 0.03074 -0.0002 0.1756 1.0000
10.250 1.1077 0.04335 0.03337 0.0016 0.1586 1.0000
10.500 1.1231 0.04614 0.03620 0.0030 0.1456 1.0000
10.750 1.1450 0.04933 0.03932 0.0034 0.1350 1.0000
11.000 1.1418 0.05247 0.04302 0.0064 0.1303 1.0000
11.250 1.1589 0.05556 0.04609 0.0072 0.1228 1.0000
11.500 1.1566 0.05943 0.05030 0.0094 0.1200 1.0000
11.750 1.1423 0.06315 0.05445 0.0124 0.1190 1.0000
12.000 1.1225 0.06688 0.05851 0.0154 0.1185 1.0000
12.250 1.0986 0.07099 0.06289 0.0177 0.1184 1.0000
12.500 1.0719 0.07579 0.06793 0.0187 0.1189 1.0000
12.750 1.0435 0.08144 0.07377 0.0182 0.1196 1.0000
13.000 1.0153 0.08796 0.08043 0.0165 0.1204 1.0000
13.250 0.9894 0.09525 0.08781 0.0140 0.1213 1.0000
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Polar data table (+)
Polar graphs
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