GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 50,000 Max Cl/Cd: 32.99 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe677-il-50000-n5.txt Download as CSV file: xf-goe677-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5392 0.11358 0.10631 -0.0157 1.0000 0.0853
-10.250 -0.5379 0.10894 0.10167 -0.0177 1.0000 0.0851
-10.000 -0.5389 0.10406 0.09682 -0.0202 1.0000 0.0850
-9.750 -0.5392 0.09923 0.09201 -0.0225 1.0000 0.0847
-9.500 -0.5394 0.09444 0.08725 -0.0248 1.0000 0.0841
-9.250 -0.5421 0.08954 0.08238 -0.0273 1.0000 0.0832
-9.000 -0.5494 0.08466 0.07751 -0.0294 1.0000 0.0823
-8.750 -0.5603 0.08007 0.07291 -0.0304 1.0000 0.0815
-8.500 -0.5701 0.07540 0.06818 -0.0312 1.0000 0.0808
-8.250 -0.5781 0.07083 0.06350 -0.0314 1.0000 0.0802
-8.000 -0.5837 0.06650 0.05901 -0.0311 1.0000 0.0800
-7.750 -0.5869 0.06249 0.05480 -0.0303 1.0000 0.0807
-7.500 -0.5879 0.05872 0.05077 -0.0290 1.0000 0.0818
-7.250 -0.5870 0.05513 0.04686 -0.0273 1.0000 0.0828
-7.000 -0.5835 0.05181 0.04319 -0.0254 1.0000 0.0834
-6.750 -0.5775 0.04880 0.03986 -0.0232 1.0000 0.0836
-6.500 -0.5704 0.04609 0.03682 -0.0209 1.0000 0.0840
-6.250 -0.5627 0.04365 0.03405 -0.0184 1.0000 0.0844
-6.000 -0.5548 0.04151 0.03156 -0.0158 1.0000 0.0850
-5.750 -0.5469 0.03971 0.02955 -0.0132 1.0000 0.0861
-5.500 -0.5384 0.03846 0.02825 -0.0109 1.0000 0.0880
-5.250 -0.5116 0.03693 0.02657 -0.0119 0.9926 0.0911
-5.000 -0.4760 0.03495 0.02420 -0.0142 0.9816 0.0940
-4.750 -0.4387 0.03302 0.02183 -0.0164 0.9716 0.0963
-4.500 -0.4011 0.03135 0.01971 -0.0185 0.9614 0.0989
-4.250 -0.3643 0.03008 0.01841 -0.0208 0.9517 0.1035
-4.000 -0.3232 0.02898 0.01711 -0.0236 0.9442 0.1102
-3.750 -0.2854 0.02789 0.01586 -0.0255 0.9345 0.1153
-3.500 -0.2442 0.02696 0.01489 -0.0281 0.9269 0.1227
-3.250 -0.2056 0.02619 0.01404 -0.0303 0.9177 0.1335
-3.000 -0.1672 0.02542 0.01317 -0.0323 0.9091 0.1449
-2.750 -0.1312 0.02461 0.01240 -0.0339 0.8993 0.1620
-2.500 -0.1006 0.02382 0.01171 -0.0345 0.8869 0.1858
-2.250 -0.0738 0.02290 0.01115 -0.0344 0.8742 0.2323
-2.000 0.0011 0.02079 0.01169 -0.0399 0.8699 0.8642
-1.750 0.1351 0.02106 0.01140 -0.0582 0.8677 1.0000
-1.500 0.1593 0.02105 0.01116 -0.0578 0.8536 1.0000
-1.250 0.1828 0.02107 0.01096 -0.0572 0.8403 1.0000
-1.000 0.2061 0.02111 0.01082 -0.0566 0.8277 1.0000
-0.750 0.2293 0.02115 0.01069 -0.0558 0.8160 1.0000
-0.500 0.2525 0.02120 0.01058 -0.0550 0.8051 1.0000
-0.250 0.2751 0.02130 0.01057 -0.0542 0.7931 1.0000
0.000 0.2978 0.02141 0.01055 -0.0534 0.7820 1.0000
0.250 0.3208 0.02148 0.01050 -0.0524 0.7720 1.0000
0.500 0.3431 0.02165 0.01059 -0.0515 0.7606 1.0000
0.750 0.3654 0.02181 0.01069 -0.0506 0.7497 1.0000
1.000 0.3883 0.02193 0.01071 -0.0495 0.7401 1.0000
1.250 0.4103 0.02215 0.01089 -0.0486 0.7287 1.0000
1.500 0.4324 0.02237 0.01108 -0.0476 0.7178 1.0000
1.750 0.4559 0.02251 0.01116 -0.0466 0.7084 1.0000
2.000 0.4779 0.02280 0.01145 -0.0457 0.6968 1.0000
2.250 0.5001 0.02309 0.01174 -0.0448 0.6859 1.0000
2.500 0.5234 0.02325 0.01186 -0.0437 0.6768 1.0000
2.750 0.5446 0.02363 0.01227 -0.0427 0.6649 1.0000
3.000 0.5662 0.02397 0.01264 -0.0417 0.6541 1.0000
3.250 0.5893 0.02416 0.01282 -0.0405 0.6452 1.0000
3.500 0.6097 0.02461 0.01334 -0.0395 0.6334 1.0000
3.750 0.6307 0.02500 0.01379 -0.0384 0.6228 1.0000
4.000 0.6535 0.02523 0.01403 -0.0372 0.6138 1.0000
4.250 0.6729 0.02574 0.01463 -0.0360 0.6021 1.0000
4.500 0.6935 0.02613 0.01509 -0.0348 0.5916 1.0000
4.750 0.7158 0.02635 0.01538 -0.0335 0.5822 1.0000
5.000 0.7342 0.02685 0.01599 -0.0321 0.5701 1.0000
5.250 0.7538 0.02721 0.01644 -0.0306 0.5584 1.0000
5.500 0.7745 0.02737 0.01668 -0.0291 0.5466 1.0000
5.750 0.7955 0.02740 0.01677 -0.0274 0.5338 1.0000
6.000 0.8155 0.02743 0.01687 -0.0256 0.5196 1.0000
6.250 0.8341 0.02751 0.01703 -0.0237 0.5037 1.0000
6.500 0.8525 0.02759 0.01720 -0.0217 0.4872 1.0000
6.750 0.8709 0.02766 0.01733 -0.0197 0.4700 1.0000
7.000 0.8890 0.02775 0.01747 -0.0177 0.4519 1.0000
7.250 0.9070 0.02791 0.01764 -0.0156 0.4335 1.0000
7.500 0.9245 0.02816 0.01794 -0.0136 0.4151 1.0000
7.750 0.9412 0.02853 0.01833 -0.0115 0.3967 1.0000
8.000 0.9538 0.02915 0.01908 -0.0092 0.3762 1.0000
8.250 0.9660 0.02977 0.01982 -0.0069 0.3547 1.0000
8.500 0.9778 0.03040 0.02051 -0.0045 0.3326 1.0000
8.750 0.9868 0.03120 0.02143 -0.0019 0.3079 1.0000
9.000 0.9945 0.03207 0.02228 0.0008 0.2827 1.0000
9.250 1.0004 0.03307 0.02316 0.0036 0.2594 1.0000
9.500 1.0047 0.03433 0.02434 0.0064 0.2378 1.0000
9.750 1.0080 0.03570 0.02561 0.0091 0.2205 1.0000
10.000 1.0113 0.03714 0.02700 0.0117 0.2067 1.0000
10.250 1.0173 0.03864 0.02847 0.0139 0.1955 1.0000
10.500 1.0250 0.04012 0.02990 0.0158 0.1856 1.0000
10.750 1.0329 0.04175 0.03167 0.0174 0.1755 1.0000
11.000 1.0410 0.04340 0.03337 0.0189 0.1664 1.0000
11.250 1.0466 0.04510 0.03506 0.0203 0.1569 1.0000
11.500 1.0447 0.04734 0.03746 0.0215 0.1464 1.0000
11.750 1.0410 0.04977 0.03993 0.0223 0.1361 1.0000
12.000 1.0368 0.05232 0.04246 0.0227 0.1264 1.0000
12.250 1.0319 0.05524 0.04550 0.0228 0.1169 1.0000
12.500 1.0298 0.05814 0.04852 0.0229 0.1089 1.0000
12.750 1.0282 0.06089 0.05126 0.0231 0.1017 1.0000
13.000 1.0250 0.06425 0.05484 0.0230 0.0942 1.0000
13.250 1.0236 0.06718 0.05767 0.0231 0.0875 1.0000
13.500 1.0180 0.07111 0.06188 0.0227 0.0807 1.0000
13.750 1.0174 0.07404 0.06466 0.0227 0.0749 1.0000
14.000 1.0084 0.07885 0.06986 0.0217 0.0701 1.0000
14.250 1.0025 0.08307 0.07425 0.0209 0.0661 1.0000
14.500 1.0034 0.08604 0.07713 0.0207 0.0627 1.0000
14.750 0.9890 0.09221 0.08366 0.0185 0.0607 1.0000
15.000 0.9727 0.09893 0.09066 0.0157 0.0591 1.0000
15.250 0.9535 0.10659 0.09857 0.0121 0.0581 1.0000
15.500 0.9280 0.11612 0.10832 0.0072 0.0578 1.0000
15.750 0.8932 0.12884 0.12121 0.0004 0.0584 1.0000
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Polar data table (+)
Polar graphs
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