GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 50,000 Max Cl/Cd: 45.48 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe494-il-50000-n5.txt Download as CSV file: xf-goe494-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3458 0.10302 0.09640 -0.0292 1.0000 0.0815
-7.250 -0.3559 0.10244 0.09596 -0.0284 1.0000 0.0836
-7.000 -0.3633 0.10204 0.09571 -0.0302 1.0000 0.0848
-6.750 -0.3570 0.09717 0.09089 -0.0266 1.0000 0.0885
-6.500 -0.3561 0.09488 0.08866 -0.0254 1.0000 0.0934
-6.250 -0.3590 0.09374 0.08762 -0.0275 1.0000 0.0977
-6.000 -0.3551 0.09298 0.08693 -0.0349 1.0000 0.0992
-5.750 -0.3554 0.08804 0.08206 -0.0265 1.0000 0.1029
-5.500 -0.3518 0.08551 0.07957 -0.0262 1.0000 0.1072
-5.250 -0.3341 0.08395 0.07802 -0.0382 1.0000 0.1136
-5.000 -0.3358 0.08002 0.07416 -0.0323 1.0000 0.1155
-4.750 -0.3298 0.07710 0.07125 -0.0310 1.0000 0.1192
-4.500 -0.3073 0.07387 0.06798 -0.0392 1.0000 0.1290
-4.250 -0.3036 0.07118 0.06532 -0.0358 1.0000 0.1369
-3.750 -0.1852 0.05511 0.04839 -0.0674 0.9981 0.0711
-3.500 -0.1531 0.05087 0.04405 -0.0712 0.9946 0.0681
-3.250 -0.0858 0.04391 0.03633 -0.0852 0.9928 0.0710
-3.000 -0.0397 0.03936 0.03130 -0.0918 0.9903 0.0700
-2.750 0.0088 0.03530 0.02653 -0.0982 0.9884 0.0697
-2.500 0.0473 0.03312 0.02396 -0.1020 0.9853 0.0771
-2.250 0.0888 0.03074 0.02092 -0.1057 0.9823 0.0780
-2.000 0.1286 0.02890 0.01845 -0.1085 0.9793 0.0773
-1.750 0.1651 0.02761 0.01666 -0.1105 0.9756 0.0771
-1.500 0.1996 0.02667 0.01530 -0.1121 0.9711 0.0774
-1.250 0.2360 0.02598 0.01427 -0.1139 0.9673 0.0781
-1.000 0.2681 0.02550 0.01349 -0.1149 0.9619 0.0798
-0.750 0.3032 0.02514 0.01287 -0.1164 0.9570 0.0822
-0.500 0.3379 0.02486 0.01238 -0.1180 0.9518 0.0864
-0.250 0.3714 0.02462 0.01206 -0.1194 0.9457 0.0946
0.000 0.4100 0.02428 0.01183 -0.1219 0.9412 0.1213
0.250 0.4416 0.02335 0.01225 -0.1234 0.9357 0.4646
0.500 0.4675 0.02250 0.01217 -0.1229 0.9287 1.0000
0.750 0.4968 0.02288 0.01229 -0.1235 0.9213 1.0000
1.000 0.5304 0.02325 0.01246 -0.1249 0.9153 1.0000
1.250 0.5586 0.02366 0.01273 -0.1253 0.9079 1.0000
1.500 0.5915 0.02403 0.01301 -0.1265 0.9016 1.0000
1.750 0.6191 0.02445 0.01339 -0.1268 0.8940 1.0000
2.000 0.6515 0.02482 0.01378 -0.1279 0.8876 1.0000
2.250 0.6781 0.02527 0.01425 -0.1280 0.8795 1.0000
2.500 0.7112 0.02562 0.01467 -0.1292 0.8732 1.0000
2.750 0.7360 0.02611 0.01529 -0.1290 0.8642 1.0000
3.000 0.7716 0.02640 0.01573 -0.1304 0.8584 1.0000
3.500 0.8229 0.02734 0.01706 -0.1300 0.8395 1.0000
3.750 0.8611 0.02738 0.01738 -0.1314 0.8310 1.0000
4.000 0.8919 0.02719 0.01746 -0.1309 0.8134 1.0000
4.250 0.9283 0.02653 0.01716 -0.1306 0.7935 1.0000
4.500 0.9692 0.02562 0.01671 -0.1305 0.7749 1.0000
4.750 1.0066 0.02323 0.01461 -0.1267 0.7155 1.0000
5.000 1.0224 0.02248 0.01398 -0.1213 0.6248 1.0000
5.250 1.0240 0.02458 0.01336 -0.1140 0.2376 1.0000
5.500 1.0265 0.02790 0.01541 -0.1109 0.0836 1.0000
5.750 1.0400 0.03001 0.01740 -0.1086 0.0633 1.0000
6.000 1.0539 0.03208 0.01953 -0.1065 0.0533 1.0000
6.250 1.0714 0.03386 0.02160 -0.1045 0.0488 1.0000
6.500 1.0911 0.03609 0.02393 -0.1030 0.0430 1.0000
6.750 1.1201 0.03828 0.02637 -0.1022 0.0389 1.0000
7.000 1.1547 0.04092 0.02925 -0.1021 0.0366 1.0000
7.250 1.1845 0.04391 0.03252 -0.1019 0.0338 1.0000
7.500 1.2100 0.04766 0.03652 -0.1014 0.0314 1.0000
7.750 1.2309 0.05086 0.04030 -0.0998 0.0305 1.0000
8.000 1.2480 0.05456 0.04453 -0.0980 0.0302 1.0000
8.250 1.2604 0.05845 0.04895 -0.0959 0.0301 1.0000
8.500 1.2684 0.06250 0.05350 -0.0936 0.0301 1.0000
8.750 1.2724 0.06665 0.05812 -0.0911 0.0302 1.0000
9.000 1.2718 0.07080 0.06271 -0.0885 0.0302 1.0000
9.250 1.2666 0.07495 0.06726 -0.0859 0.0302 1.0000
9.500 1.2574 0.07904 0.07171 -0.0833 0.0301 1.0000
9.750 1.2437 0.08295 0.07590 -0.0806 0.0302 1.0000
10.000 1.2272 0.08688 0.08006 -0.0783 0.0303 1.0000
10.250 1.2098 0.09119 0.08457 -0.0770 0.0304 1.0000
10.500 1.1922 0.09595 0.08951 -0.0767 0.0306 1.0000
10.750 1.1752 0.10119 0.09491 -0.0776 0.0308 1.0000
11.000 1.1591 0.10689 0.10073 -0.0794 0.0311 1.0000
11.250 1.1441 0.11305 0.10699 -0.0820 0.0313 1.0000
11.500 1.1328 0.11938 0.11339 -0.0850 0.0316 1.0000
11.750 1.1237 0.12590 0.11995 -0.0882 0.0318 1.0000
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Polar data table (+)
Polar graphs
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