GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610b-il-1000000-n5.txt Download as CSV file: xf-goe610b-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2043 0.08111 0.07908 -0.0779 0.8860 0.0063
-9.250 -0.2464 0.07123 0.06900 -0.0814 0.8424 0.0071
-9.000 -0.2520 0.06862 0.06634 -0.0816 0.8280 0.0075
-8.750 -0.2541 0.06540 0.06308 -0.0833 0.8178 0.0076
-8.500 -0.2498 0.06202 0.05967 -0.0859 0.8106 0.0077
-8.000 -0.2327 0.05522 0.05280 -0.0916 0.7981 0.0085
-7.750 -0.2225 0.05102 0.04852 -0.0951 0.7921 0.0089
-7.250 -0.2163 0.03182 0.02864 -0.1065 0.7814 0.0098
-7.000 -0.1987 0.02807 0.02469 -0.1071 0.7761 0.0108
-6.500 -0.1906 0.01119 0.00599 -0.1047 0.7668 0.0134
-6.250 -0.1645 0.01082 0.00558 -0.1044 0.7609 0.0161
-6.000 -0.1382 0.01049 0.00522 -0.1040 0.7551 0.0190
-5.750 -0.1097 0.01082 0.00561 -0.1040 0.7478 0.0227
-5.500 -0.0816 0.01113 0.00594 -0.1038 0.7404 0.0254
-5.250 -0.0544 0.01118 0.00594 -0.1035 0.7308 0.0276
-5.000 -0.0274 0.01119 0.00588 -0.1033 0.7197 0.0287
-4.750 -0.0007 0.01125 0.00588 -0.1029 0.7049 0.0294
-4.500 0.0258 0.01140 0.00595 -0.1025 0.6864 0.0299
-4.250 0.0520 0.01155 0.00600 -0.1021 0.6660 0.0301
-4.000 0.0782 0.01172 0.00608 -0.1016 0.6462 0.0303
-3.750 0.1016 0.01085 0.00494 -0.1009 0.6264 0.0312
-3.500 0.1266 0.01057 0.00450 -0.1003 0.6078 0.0321
-3.250 0.1526 0.01046 0.00428 -0.0999 0.5939 0.0327
-3.000 0.1786 0.01014 0.00386 -0.0995 0.5837 0.0329
-2.750 0.2048 0.01002 0.00366 -0.0991 0.5730 0.0334
-2.500 0.2306 0.00977 0.00330 -0.0987 0.5617 0.0337
-2.250 0.2566 0.00951 0.00295 -0.0982 0.5519 0.0340
-2.000 0.2827 0.00930 0.00268 -0.0978 0.5442 0.0345
-1.750 0.3090 0.00915 0.00247 -0.0974 0.5365 0.0354
-1.500 0.3356 0.00903 0.00230 -0.0971 0.5320 0.0366
-1.250 0.3625 0.00894 0.00220 -0.0969 0.5276 0.0384
-1.000 0.3895 0.00889 0.00212 -0.0966 0.5236 0.0399
-0.750 0.4162 0.00888 0.00208 -0.0963 0.5191 0.0409
-0.500 0.4433 0.00888 0.00206 -0.0961 0.5147 0.0417
-0.250 0.4702 0.00887 0.00203 -0.0959 0.5083 0.0421
0.000 0.4966 0.00888 0.00201 -0.0956 0.5014 0.0424
0.250 0.5236 0.00887 0.00199 -0.0954 0.4954 0.0427
0.500 0.5502 0.00883 0.00194 -0.0951 0.4905 0.0428
0.750 0.5765 0.00877 0.00187 -0.0948 0.4853 0.0431
1.000 0.6026 0.00863 0.00172 -0.0944 0.4788 0.0436
1.250 0.6285 0.00857 0.00164 -0.0940 0.4710 0.0440
1.500 0.6548 0.00853 0.00159 -0.0937 0.4626 0.0444
1.750 0.6807 0.00853 0.00157 -0.0933 0.4517 0.0447
2.000 0.7058 0.00860 0.00156 -0.0928 0.4294 0.0450
2.250 0.7228 0.00932 0.00182 -0.0909 0.3284 0.0458
2.500 0.7464 0.00954 0.00195 -0.0901 0.3037 0.0465
2.750 0.7711 0.00968 0.00204 -0.0895 0.2887 0.0467
3.000 0.7960 0.00981 0.00213 -0.0890 0.2767 0.0468
3.250 0.8212 0.00992 0.00222 -0.0885 0.2671 0.0471
3.500 0.8465 0.01002 0.00230 -0.0881 0.2592 0.0475
3.750 0.8714 0.01015 0.00241 -0.0876 0.2501 0.0480
4.000 0.8965 0.01026 0.00251 -0.0871 0.2408 0.0493
4.250 0.9210 0.01043 0.00265 -0.0865 0.2293 0.0510
4.500 0.9447 0.01064 0.00280 -0.0858 0.2131 0.0544
4.750 0.9683 0.01080 0.00300 -0.0851 0.1994 0.0973
5.000 0.9857 0.01144 0.00339 -0.0834 0.1384 0.1157
5.250 1.0458 0.01052 0.00408 -0.0918 0.1196 0.9985
5.500 1.0716 0.01085 0.00438 -0.0916 0.1112 1.0000
5.750 1.0942 0.01105 0.00458 -0.0907 0.1077 1.0000
6.000 1.1166 0.01127 0.00481 -0.0897 0.1043 1.0000
6.250 1.1382 0.01153 0.00506 -0.0886 0.1000 1.0000
6.500 1.1598 0.01180 0.00533 -0.0875 0.0956 1.0000
6.750 1.1825 0.01197 0.00553 -0.0866 0.0925 1.0000
7.000 1.2026 0.01231 0.00580 -0.0853 0.0781 1.0000
7.250 1.2153 0.01310 0.00636 -0.0827 0.0425 1.0000
7.500 1.2285 0.01384 0.00697 -0.0803 0.0195 1.0000
7.750 1.2469 0.01424 0.00737 -0.0787 0.0147 1.0000
8.000 1.2657 0.01460 0.00775 -0.0771 0.0127 1.0000
8.250 1.2832 0.01501 0.00818 -0.0754 0.0112 1.0000
8.500 1.2990 0.01549 0.00868 -0.0734 0.0096 1.0000
8.750 1.3145 0.01587 0.00909 -0.0713 0.0089 1.0000
9.000 1.3286 0.01629 0.00956 -0.0690 0.0082 1.0000
9.250 1.3418 0.01678 0.01007 -0.0666 0.0076 1.0000
9.500 1.3543 0.01734 0.01066 -0.0642 0.0069 1.0000
9.750 1.3681 0.01787 0.01123 -0.0620 0.0065 1.0000
10.000 1.3815 0.01844 0.01185 -0.0600 0.0063 1.0000
10.250 1.3948 0.01904 0.01249 -0.0580 0.0058 1.0000
10.500 1.4073 0.01971 0.01321 -0.0560 0.0055 1.0000
10.750 1.4190 0.02046 0.01399 -0.0540 0.0052 1.0000
11.000 1.4293 0.02134 0.01496 -0.0519 0.0050 1.0000
11.250 1.4389 0.02230 0.01597 -0.0499 0.0047 1.0000
11.500 1.4488 0.02329 0.01704 -0.0481 0.0046 1.0000
11.750 1.4611 0.02414 0.01794 -0.0466 0.0042 1.0000
12.000 1.4697 0.02532 0.01919 -0.0449 0.0042 1.0000
12.250 1.4794 0.02643 0.02037 -0.0435 0.0040 1.0000
12.500 1.4872 0.02776 0.02176 -0.0419 0.0038 1.0000
12.750 1.4946 0.02914 0.02321 -0.0405 0.0037 1.0000
13.000 1.5019 0.03059 0.02472 -0.0392 0.0036 1.0000
13.250 1.5077 0.03218 0.02638 -0.0379 0.0034 1.0000
13.500 1.5110 0.03407 0.02834 -0.0366 0.0033 1.0000
13.750 1.5111 0.03631 0.03068 -0.0352 0.0032 1.0000
14.000 1.5129 0.03847 0.03294 -0.0341 0.0032 1.0000
14.250 1.5177 0.04036 0.03491 -0.0333 0.0031 1.0000
14.500 1.5171 0.04291 0.03756 -0.0325 0.0031 1.0000
14.750 1.5184 0.04535 0.04009 -0.0319 0.0030 1.0000
15.000 1.5160 0.04826 0.04311 -0.0314 0.0030 1.0000
15.250 1.5179 0.05078 0.04576 -0.0311 0.0029 1.0000
15.500 1.5163 0.05379 0.04887 -0.0309 0.0029 1.0000
15.750 1.5121 0.05721 0.05241 -0.0308 0.0028 1.0000
16.000 1.5101 0.06042 0.05572 -0.0310 0.0027 1.0000
16.250 1.5028 0.06442 0.05983 -0.0312 0.0027 1.0000
16.500 1.5009 0.06775 0.06326 -0.0316 0.0027 1.0000
16.750 1.4936 0.07189 0.06751 -0.0321 0.0026 1.0000
17.000 1.4892 0.07569 0.07140 -0.0328 0.0026 1.0000
17.250 1.4859 0.07941 0.07521 -0.0335 0.0025 1.0000
17.500 1.4817 0.08335 0.07924 -0.0344 0.0024 1.0000
17.750 1.4698 0.08857 0.08458 -0.0357 0.0024 1.0000
18.000 1.4593 0.09370 0.08982 -0.0372 0.0024 1.0000
18.250 1.4522 0.09846 0.09468 -0.0388 0.0023 1.0000
18.500 1.4422 0.10382 0.10015 -0.0407 0.0023 1.0000
18.750 1.4308 0.10959 0.10604 -0.0429 0.0023 1.0000
19.000 1.4160 0.11612 0.11270 -0.0456 0.0023 1.0000
19.250 1.4026 0.12257 0.11926 -0.0485 0.0023 1.0000
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