GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 500,000 Max Cl/Cd: 98.38 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe550-il-500000-n5.txt Download as CSV file: xf-goe550-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 550 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.6592 0.13433 0.13146 -0.0379 1.0000 0.0209
-17.250 -0.6859 0.12513 0.12216 -0.0425 1.0000 0.0216
-17.000 -0.6943 0.11985 0.11686 -0.0451 1.0000 0.0222
-16.750 -0.7097 0.11332 0.11029 -0.0485 1.0000 0.0227
-16.500 -0.7258 0.10685 0.10376 -0.0518 1.0000 0.0233
-16.250 -0.7409 0.10071 0.09756 -0.0549 1.0000 0.0238
-16.000 -0.7559 0.09476 0.09154 -0.0579 1.0000 0.0242
-15.750 -0.7707 0.08900 0.08570 -0.0609 1.0000 0.0247
-15.500 -0.7825 0.08394 0.08056 -0.0634 1.0000 0.0251
-15.250 -0.7958 0.07874 0.07528 -0.0660 1.0000 0.0256
-15.000 -0.8106 0.07359 0.07009 -0.0686 1.0000 0.0259
-14.750 -0.8276 0.06842 0.06488 -0.0712 1.0000 0.0262
-14.500 -0.8505 0.06295 0.05936 -0.0739 1.0000 0.0263
-14.250 -0.8787 0.05721 0.05357 -0.0765 1.0000 0.0264
-14.000 -0.9164 0.05106 0.04736 -0.0789 1.0000 0.0262
-13.750 -0.9931 0.04327 0.03951 -0.0794 1.0000 0.0254
-13.500 -1.0218 0.03062 0.02648 -0.0936 0.9974 0.0254
-13.250 -0.9985 0.02770 0.02338 -0.0982 0.9943 0.0263
-13.000 -0.9747 0.02584 0.02142 -0.1007 0.9913 0.0274
-12.750 -0.9485 0.02450 0.01996 -0.1026 0.9882 0.0286
-12.500 -0.9199 0.02341 0.01874 -0.1044 0.9856 0.0298
-12.250 -0.8902 0.02231 0.01752 -0.1064 0.9836 0.0308
-12.000 -0.8663 0.02127 0.01641 -0.1070 0.9793 0.0320
-11.750 -0.8381 0.02043 0.01550 -0.1082 0.9759 0.0332
-11.500 -0.8076 0.01970 0.01466 -0.1096 0.9735 0.0345
-11.250 -0.7766 0.01901 0.01387 -0.1109 0.9712 0.0356
-11.000 -0.7531 0.01828 0.01307 -0.1108 0.9651 0.0367
-10.750 -0.7235 0.01755 0.01229 -0.1119 0.9617 0.0381
-10.500 -0.6916 0.01693 0.01160 -0.1132 0.9593 0.0396
-10.250 -0.6670 0.01643 0.01103 -0.1129 0.9524 0.0409
-10.000 -0.6358 0.01596 0.01046 -0.1139 0.9480 0.0422
-9.750 -0.6018 0.01526 0.00972 -0.1157 0.9449 0.0441
-9.500 -0.5743 0.01474 0.00915 -0.1159 0.9370 0.0458
-9.250 -0.5397 0.01425 0.00858 -0.1176 0.9315 0.0476
-9.000 -0.5068 0.01382 0.00807 -0.1187 0.9232 0.0491
-8.750 -0.4712 0.01331 0.00747 -0.1206 0.9148 0.0511
-8.500 -0.4393 0.01284 0.00695 -0.1216 0.9038 0.0535
-8.250 -0.4072 0.01246 0.00648 -0.1226 0.8930 0.0560
-7.750 -0.3480 0.01181 0.00567 -0.1234 0.8694 0.0614
-7.500 -0.3201 0.01153 0.00532 -0.1234 0.8578 0.0655
-7.250 -0.2926 0.01127 0.00500 -0.1233 0.8468 0.0703
-7.000 -0.2657 0.01104 0.00472 -0.1231 0.8361 0.0763
-6.750 -0.2388 0.01083 0.00447 -0.1229 0.8264 0.0823
-6.500 -0.2118 0.01067 0.00425 -0.1226 0.8167 0.0886
-6.250 -0.1851 0.01049 0.00402 -0.1223 0.8078 0.0938
-6.000 -0.1581 0.01035 0.00382 -0.1220 0.7995 0.0997
-5.750 -0.1311 0.01023 0.00364 -0.1217 0.7912 0.1041
-5.500 -0.1044 0.01006 0.00343 -0.1214 0.7829 0.1098
-5.250 -0.0774 0.00993 0.00327 -0.1211 0.7750 0.1148
-5.000 -0.0504 0.00980 0.00310 -0.1208 0.7674 0.1201
-4.750 -0.0234 0.00966 0.00295 -0.1205 0.7600 0.1268
-4.500 0.0035 0.00956 0.00281 -0.1202 0.7519 0.1335
-4.250 0.0305 0.00944 0.00269 -0.1199 0.7446 0.1429
-4.000 0.0576 0.00934 0.00260 -0.1196 0.7369 0.1529
-3.750 0.0847 0.00928 0.00252 -0.1193 0.7296 0.1630
-3.500 0.1121 0.00923 0.00246 -0.1191 0.7214 0.1744
-3.250 0.1391 0.00920 0.00242 -0.1187 0.7132 0.1842
-3.000 0.1662 0.00918 0.00236 -0.1184 0.7031 0.1908
-2.750 0.1928 0.00917 0.00231 -0.1179 0.6912 0.1964
-2.500 0.2193 0.00918 0.00226 -0.1174 0.6785 0.2016
-2.250 0.2459 0.00920 0.00220 -0.1170 0.6665 0.2059
-2.000 0.2729 0.00917 0.00217 -0.1166 0.6565 0.2103
-1.750 0.2997 0.00918 0.00214 -0.1162 0.6471 0.2143
-1.500 0.3267 0.00919 0.00210 -0.1159 0.6373 0.2181
-1.250 0.3535 0.00922 0.00207 -0.1155 0.6273 0.2210
-1.000 0.3800 0.00922 0.00205 -0.1150 0.6168 0.2245
-0.750 0.4069 0.00923 0.00205 -0.1147 0.6072 0.2281
-0.500 0.4334 0.00927 0.00204 -0.1142 0.5976 0.2317
-0.250 0.4601 0.00931 0.00205 -0.1138 0.5870 0.2358
0.000 0.4865 0.00935 0.00206 -0.1134 0.5770 0.2401
0.500 0.5395 0.00943 0.00212 -0.1125 0.5582 0.2497
0.750 0.5656 0.00950 0.00215 -0.1120 0.5493 0.2534
1.000 0.5921 0.00954 0.00219 -0.1116 0.5397 0.2580
1.250 0.6181 0.00960 0.00225 -0.1111 0.5304 0.2628
1.500 0.6443 0.00967 0.00230 -0.1107 0.5209 0.2671
1.750 0.6706 0.00974 0.00236 -0.1102 0.5127 0.2710
2.000 0.6962 0.00981 0.00243 -0.1096 0.5024 0.2762
2.250 0.7221 0.00988 0.00250 -0.1091 0.4918 0.2820
2.500 0.7473 0.01000 0.00259 -0.1085 0.4797 0.2873
2.750 0.7724 0.01009 0.00268 -0.1078 0.4682 0.2934
3.000 0.7981 0.01017 0.00277 -0.1073 0.4575 0.3005
3.250 0.8232 0.01028 0.00288 -0.1067 0.4471 0.3081
3.500 0.8480 0.01039 0.00299 -0.1060 0.4360 0.3177
3.750 0.8725 0.01050 0.00312 -0.1053 0.4225 0.3302
4.000 0.8963 0.01063 0.00327 -0.1044 0.4077 0.3498
4.250 0.9196 0.01072 0.00346 -0.1036 0.3934 0.3971
4.500 0.9426 0.01079 0.00367 -0.1026 0.3809 0.4689
4.750 0.9655 0.01089 0.00386 -0.1017 0.3703 0.5174
5.000 0.9853 0.01063 0.00411 -0.1001 0.3616 0.7128
5.500 1.0468 0.01064 0.00457 -0.1013 0.3437 1.0000
5.750 1.0696 0.01088 0.00478 -0.1003 0.3351 1.0000
6.000 1.0926 0.01111 0.00500 -0.0993 0.3268 1.0000
6.250 1.1153 0.01135 0.00523 -0.0983 0.3204 1.0000
6.500 1.1377 0.01160 0.00546 -0.0972 0.3114 1.0000
6.750 1.1588 0.01190 0.00571 -0.0959 0.2988 1.0000
7.000 1.1787 0.01224 0.00599 -0.0945 0.2838 1.0000
7.250 1.1988 0.01256 0.00628 -0.0930 0.2713 1.0000
7.500 1.2174 0.01290 0.00656 -0.0913 0.2586 1.0000
7.750 1.2358 0.01322 0.00686 -0.0896 0.2451 1.0000
8.000 1.2520 0.01364 0.00721 -0.0875 0.2280 1.0000
8.250 1.2646 0.01422 0.00766 -0.0848 0.2002 1.0000
8.500 1.2692 0.01522 0.00837 -0.0811 0.1556 1.0000
8.750 1.2767 0.01610 0.00910 -0.0778 0.1299 1.0000
9.000 1.2886 0.01679 0.00972 -0.0753 0.1172 1.0000
9.250 1.3023 0.01738 0.01030 -0.0732 0.1091 1.0000
9.500 1.3158 0.01799 0.01091 -0.0711 0.1021 1.0000
9.750 1.3300 0.01858 0.01151 -0.0691 0.0958 1.0000
10.000 1.3425 0.01927 0.01218 -0.0670 0.0875 1.0000
10.250 1.3540 0.02003 0.01292 -0.0648 0.0767 1.0000
10.500 1.3639 0.02091 0.01376 -0.0626 0.0668 1.0000
10.750 1.3728 0.02188 0.01469 -0.0604 0.0582 1.0000
11.000 1.3819 0.02288 0.01568 -0.0583 0.0522 1.0000
11.250 1.3905 0.02395 0.01675 -0.0563 0.0471 1.0000
11.500 1.3999 0.02501 0.01785 -0.0544 0.0433 1.0000
11.750 1.4073 0.02625 0.01911 -0.0526 0.0393 1.0000
12.000 1.4159 0.02746 0.02035 -0.0510 0.0363 1.0000
12.250 1.4228 0.02884 0.02176 -0.0493 0.0334 1.0000
12.500 1.4303 0.03024 0.02320 -0.0479 0.0312 1.0000
12.750 1.4368 0.03176 0.02476 -0.0465 0.0288 1.0000
13.000 1.4419 0.03346 0.02650 -0.0451 0.0268 1.0000
13.250 1.4481 0.03511 0.02822 -0.0440 0.0249 1.0000
13.500 1.4522 0.03700 0.03016 -0.0428 0.0233 1.0000
13.750 1.4561 0.03899 0.03221 -0.0418 0.0218 1.0000
14.000 1.4599 0.04105 0.03432 -0.0410 0.0204 1.0000
14.250 1.4624 0.04330 0.03664 -0.0402 0.0193 1.0000
14.500 1.4635 0.04578 0.03917 -0.0396 0.0185 1.0000
14.750 1.4659 0.04820 0.04168 -0.0391 0.0178 1.0000
15.000 1.4673 0.05080 0.04437 -0.0388 0.0171 1.0000
15.250 1.4675 0.05362 0.04726 -0.0386 0.0164 1.0000
15.500 1.4666 0.05666 0.05037 -0.0385 0.0157 1.0000
15.750 1.4647 0.05992 0.05371 -0.0386 0.0153 1.0000
16.000 1.4626 0.06327 0.05715 -0.0388 0.0148 1.0000
16.250 1.4612 0.06662 0.06061 -0.0392 0.0144 1.0000
16.500 1.4593 0.07012 0.06420 -0.0397 0.0140 1.0000
16.750 1.4567 0.07378 0.06796 -0.0403 0.0137 1.0000
17.000 1.4532 0.07763 0.07189 -0.0411 0.0133 1.0000
17.250 1.4486 0.08171 0.07607 -0.0421 0.0130 1.0000
17.500 1.4437 0.08593 0.08039 -0.0432 0.0127 1.0000
17.750 1.4373 0.09048 0.08502 -0.0445 0.0124 1.0000
18.000 1.4304 0.09515 0.08979 -0.0460 0.0122 1.0000
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