GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 746 AIRFOIL (goe746-il) Reynolds number: 50,000 Max Cl/Cd: 20.78 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe746-il-50000-n5.txt Download as CSV file: xf-goe746-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 746 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3597 0.11029 0.10451 0.0045 0.7631 0.0886
-8.250 -0.3648 0.10910 0.10335 0.0006 0.7554 0.0911
-8.000 -0.3716 0.10811 0.10242 -0.0045 0.7469 0.0918
-7.750 -0.3467 0.10103 0.09527 -0.0007 0.7398 0.0957
-7.500 -0.3384 0.09785 0.09210 -0.0021 0.7317 0.0993
-7.250 -0.3376 0.09559 0.08982 -0.0043 0.7256 0.1033
-7.000 -0.3392 0.09491 0.08911 -0.0122 0.7186 0.1064
-6.750 -0.3241 0.08924 0.08347 -0.0093 0.7124 0.1095
-6.500 -0.3126 0.08615 0.08034 -0.0101 0.7061 0.1164
-6.250 -0.3059 0.08385 0.07798 -0.0155 0.7000 0.1225
-6.000 -0.2926 0.08006 0.07414 -0.0135 0.6949 0.1300
-5.750 -0.2806 0.07728 0.07129 -0.0178 0.6886 0.1384
-5.500 -0.2662 0.07396 0.06793 -0.0174 0.6830 0.1454
-5.250 -0.2529 0.07108 0.06493 -0.0197 0.6783 0.1545
-4.750 -0.2214 0.06570 0.05936 -0.0224 0.6671 0.1837
-4.500 -0.2071 0.06273 0.05636 -0.0215 0.6626 0.2019
-4.250 -0.1910 0.06055 0.05408 -0.0224 0.6567 0.2304
-3.750 -0.1162 0.05069 0.04288 -0.0301 0.6490 0.0875
-3.500 -0.0915 0.04804 0.03998 -0.0311 0.6429 0.0850
-3.250 -0.0676 0.04564 0.03721 -0.0312 0.6382 0.0838
-3.000 -0.0397 0.04336 0.03409 -0.0306 0.6346 0.0777
-2.750 -0.0153 0.04128 0.03183 -0.0309 0.6292 0.0765
-2.500 0.0098 0.03947 0.02970 -0.0307 0.6242 0.0754
-2.250 0.0349 0.03783 0.02766 -0.0300 0.6203 0.0747
-2.000 0.0617 0.03662 0.02600 -0.0298 0.6157 0.0762
-1.750 0.0892 0.03564 0.02462 -0.0298 0.6103 0.0775
-1.500 0.1161 0.03451 0.02314 -0.0294 0.6062 0.0775
-1.250 0.1436 0.03350 0.02180 -0.0289 0.6026 0.0774
-1.000 0.1728 0.03291 0.02100 -0.0296 0.5966 0.0776
-0.750 0.2024 0.03225 0.02010 -0.0298 0.5922 0.0781
-0.500 0.2372 0.03140 0.01899 -0.0305 0.5887 0.0792
-0.250 0.2699 0.03117 0.01871 -0.0320 0.5828 0.0824
0.000 0.2995 0.03096 0.01838 -0.0325 0.5780 0.0874
0.250 0.3272 0.03069 0.01791 -0.0321 0.5744 0.0912
0.500 0.3535 0.03069 0.01788 -0.0322 0.5695 0.0942
0.750 0.3786 0.03085 0.01803 -0.0324 0.5641 0.0988
1.000 0.4033 0.03081 0.01787 -0.0316 0.5602 0.1055
1.250 0.4274 0.03071 0.01777 -0.0307 0.5569 0.1186
1.500 0.4481 0.03099 0.01867 -0.0312 0.5500 0.2074
1.750 0.5405 0.02950 0.01841 -0.0430 0.5450 1.0000
2.000 0.5635 0.02986 0.01853 -0.0420 0.5415 1.0000
2.250 0.5850 0.03111 0.01975 -0.0427 0.5340 1.0000
2.500 0.6074 0.03152 0.02001 -0.0417 0.5298 1.0000
2.750 0.6303 0.03175 0.02007 -0.0404 0.5266 1.0000
3.000 0.6488 0.03333 0.02170 -0.0411 0.5180 1.0000
3.250 0.6711 0.03366 0.02194 -0.0400 0.5139 1.0000
3.500 0.6903 0.03468 0.02295 -0.0396 0.5077 1.0000
3.750 0.7093 0.03563 0.02389 -0.0392 0.5010 1.0000
4.000 0.7325 0.03573 0.02392 -0.0377 0.4974 1.0000
4.250 0.7458 0.03753 0.02579 -0.0379 0.4883 1.0000
4.500 0.7679 0.03778 0.02601 -0.0367 0.4836 1.0000
5.000 0.8005 0.03993 0.02825 -0.0353 0.4696 1.0000
5.250 0.8257 0.03974 0.02802 -0.0337 0.4664 1.0000
5.500 0.8299 0.04227 0.03067 -0.0338 0.4554 1.0000
5.750 0.8551 0.04208 0.03048 -0.0323 0.4519 1.0000
6.000 0.8553 0.04491 0.03344 -0.0322 0.4408 1.0000
6.250 0.8810 0.04463 0.03319 -0.0307 0.4373 1.0000
6.500 0.8767 0.04782 0.03647 -0.0306 0.4257 1.0000
6.750 0.9026 0.04751 0.03621 -0.0290 0.4224 1.0000
7.000 0.8928 0.05137 0.04015 -0.0293 0.4101 1.0000
7.250 0.9202 0.05079 0.03966 -0.0276 0.4073 1.0000
7.500 0.9032 0.05523 0.04413 -0.0278 0.3947 1.0000
7.750 0.9288 0.05495 0.04394 -0.0263 0.3916 1.0000
8.000 0.9096 0.05928 0.04828 -0.0259 0.3797 1.0000
8.500 0.9150 0.06393 0.05305 -0.0247 0.3652 1.0000
9.000 0.9195 0.06896 0.05824 -0.0240 0.3509 1.0000
9.500 0.9194 0.07498 0.06440 -0.0239 0.3372 1.0000
9.750 0.9419 0.07529 0.06486 -0.0228 0.3345 1.0000
10.000 0.9177 0.08153 0.07110 -0.0243 0.3242 1.0000
10.250 0.9373 0.08218 0.07191 -0.0234 0.3209 1.0000
10.500 0.9184 0.08805 0.07780 -0.0249 0.3126 1.0000
10.750 0.9271 0.09035 0.08023 -0.0248 0.3084 1.0000
11.000 0.9472 0.09106 0.08115 -0.0239 0.3057 1.0000
12.000 0.9271 0.10815 0.09860 -0.0277 0.2825 1.0000
13.000 0.9844 0.10869 0.09991 -0.0238 0.2442 1.0000
13.500 1.0161 0.10620 0.09787 -0.0211 0.2146 1.0000
14.000 1.0307 0.10786 0.09989 -0.0211 0.1759 1.0000
14.250 1.0172 0.11399 0.10612 -0.0235 0.1604 1.0000
14.500 1.0047 0.12020 0.11244 -0.0261 0.1437 1.0000
14.750 1.0255 0.11758 0.10890 -0.0241 0.0656 1.0000
15.000 1.0194 0.12236 0.11357 -0.0257 0.0578 1.0000
15.250 1.0143 0.12701 0.11813 -0.0274 0.0525 1.0000
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Polar data table (+)
Polar graphs
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