GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.58 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe645-il-1000000-n5.txt Download as CSV file: xf-goe645-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8284 0.08561 0.08263 -0.0611 1.0000 0.0173
-16.750 -0.8484 0.07930 0.07626 -0.0647 1.0000 0.0175
-16.500 -0.8691 0.07311 0.06999 -0.0682 1.0000 0.0176
-16.250 -0.8966 0.06634 0.06314 -0.0722 1.0000 0.0178
-16.000 -0.9339 0.05882 0.05551 -0.0767 1.0000 0.0177
-15.750 -0.9794 0.05071 0.04729 -0.0815 1.0000 0.0176
-15.500 -1.1123 0.03007 0.02622 -0.0979 1.0000 0.0168
-15.250 -1.1356 0.02752 0.02354 -0.0947 1.0000 0.0169
-15.000 -1.1219 0.02597 0.02190 -0.0950 0.9991 0.0173
-14.750 -1.0980 0.02448 0.02032 -0.0968 0.9967 0.0176
-14.500 -1.0727 0.02328 0.01907 -0.0982 0.9939 0.0181
-14.250 -1.0491 0.02233 0.01806 -0.0988 0.9907 0.0187
-14.000 -1.0235 0.02144 0.01712 -0.0995 0.9871 0.0192
-13.750 -0.9953 0.02064 0.01626 -0.1006 0.9839 0.0197
-13.500 -0.9700 0.01991 0.01547 -0.1009 0.9791 0.0201
-13.250 -0.9435 0.01925 0.01474 -0.1012 0.9732 0.0205
-13.000 -0.9155 0.01849 0.01394 -0.1020 0.9661 0.0210
-12.750 -0.8792 0.01781 0.01323 -0.1042 0.9577 0.0217
-12.500 -0.8355 0.01714 0.01251 -0.1079 0.9460 0.0223
-12.250 -0.7891 0.01652 0.01179 -0.1120 0.9283 0.0230
-12.000 -0.7530 0.01604 0.01117 -0.1140 0.8973 0.0236
-11.750 -0.7290 0.01573 0.01068 -0.1133 0.8640 0.0239
-11.500 -0.7081 0.01541 0.01021 -0.1121 0.8365 0.0244
-11.250 -0.6873 0.01504 0.00972 -0.1109 0.8141 0.0250
-11.000 -0.6652 0.01472 0.00930 -0.1098 0.7955 0.0254
-10.750 -0.6423 0.01444 0.00893 -0.1089 0.7804 0.0260
-10.500 -0.6188 0.01415 0.00856 -0.1080 0.7668 0.0265
-10.250 -0.5946 0.01387 0.00820 -0.1073 0.7554 0.0270
-10.000 -0.5703 0.01362 0.00786 -0.1065 0.7446 0.0275
-9.750 -0.5452 0.01337 0.00754 -0.1059 0.7352 0.0279
-9.500 -0.5208 0.01307 0.00717 -0.1052 0.7260 0.0284
-9.250 -0.4962 0.01274 0.00678 -0.1045 0.7166 0.0292
-9.000 -0.4711 0.01248 0.00647 -0.1039 0.7082 0.0298
-8.750 -0.4454 0.01223 0.00617 -0.1034 0.7003 0.0304
-8.500 -0.4198 0.01202 0.00589 -0.1028 0.6917 0.0310
-8.250 -0.3935 0.01180 0.00563 -0.1023 0.6836 0.0317
-7.750 -0.3413 0.01139 0.00509 -0.1013 0.6662 0.0328
-7.500 -0.3155 0.01116 0.00481 -0.1007 0.6574 0.0337
-7.250 -0.2890 0.01095 0.00457 -0.1002 0.6487 0.0347
-7.000 -0.2628 0.01079 0.00434 -0.0997 0.6381 0.0356
-6.750 -0.2361 0.01063 0.00413 -0.0993 0.6271 0.0365
-6.500 -0.2095 0.01050 0.00394 -0.0988 0.6162 0.0373
-6.250 -0.1831 0.01034 0.00372 -0.0983 0.6047 0.0385
-6.000 -0.1565 0.01019 0.00353 -0.0978 0.5931 0.0402
-5.750 -0.1299 0.01007 0.00336 -0.0974 0.5808 0.0421
-5.500 -0.1035 0.00997 0.00319 -0.0969 0.5676 0.0444
-5.250 -0.0769 0.00984 0.00302 -0.0964 0.5549 0.0476
-5.000 -0.0502 0.00972 0.00286 -0.0960 0.5446 0.0518
-4.500 0.0020 0.00929 0.00254 -0.0950 0.5252 0.0905
-4.250 0.0288 0.00924 0.00246 -0.0946 0.5144 0.0974
-4.000 0.0559 0.00922 0.00239 -0.0942 0.5027 0.1026
-3.750 0.0832 0.00922 0.00233 -0.0939 0.4921 0.1049
-3.250 0.1374 0.00916 0.00220 -0.0931 0.4722 0.1121
-3.000 0.1643 0.00916 0.00214 -0.0927 0.4604 0.1156
-2.500 0.2180 0.00920 0.00206 -0.0919 0.4339 0.1215
-2.250 0.2448 0.00918 0.00202 -0.0915 0.4238 0.1281
-2.000 0.2717 0.00916 0.00198 -0.0911 0.4149 0.1355
-1.750 0.2981 0.00904 0.00194 -0.0907 0.4088 0.1625
-1.500 0.3249 0.00894 0.00193 -0.0903 0.4028 0.1918
-1.250 0.3519 0.00894 0.00193 -0.0899 0.3965 0.2054
-1.000 0.3792 0.00895 0.00194 -0.0896 0.3910 0.2134
-0.750 0.4065 0.00897 0.00195 -0.0893 0.3846 0.2219
-0.500 0.4334 0.00903 0.00197 -0.0889 0.3773 0.2278
-0.250 0.4606 0.00905 0.00200 -0.0886 0.3705 0.2354
0.000 0.4874 0.00912 0.00203 -0.0882 0.3621 0.2417
0.250 0.5145 0.00917 0.00206 -0.0879 0.3554 0.2467
0.500 0.5410 0.00923 0.00211 -0.0875 0.3469 0.2542
0.750 0.5678 0.00930 0.00216 -0.0871 0.3399 0.2606
1.000 0.5941 0.00939 0.00221 -0.0867 0.3302 0.2660
1.250 0.6206 0.00947 0.00228 -0.0862 0.3216 0.2718
1.500 0.6465 0.00959 0.00235 -0.0857 0.3114 0.2769
1.750 0.6722 0.00973 0.00243 -0.0852 0.2995 0.2815
2.000 0.6976 0.00986 0.00253 -0.0846 0.2877 0.2877
2.250 0.7228 0.01001 0.00264 -0.0840 0.2768 0.2949
2.500 0.7476 0.01019 0.00277 -0.0834 0.2647 0.3005
2.750 0.7727 0.01032 0.00288 -0.0828 0.2552 0.3081
3.000 0.7972 0.01050 0.00302 -0.0820 0.2442 0.3154
3.250 0.8212 0.01069 0.00318 -0.0813 0.2336 0.3243
3.500 0.8464 0.01081 0.00330 -0.0807 0.2279 0.3335
3.750 0.8709 0.01095 0.00344 -0.0800 0.2215 0.3435
4.250 0.9200 0.01121 0.00373 -0.0786 0.2121 0.3693
4.500 0.9441 0.01133 0.00388 -0.0779 0.2075 0.3885
4.750 0.9669 0.01146 0.00406 -0.0770 0.2017 0.4243
5.000 0.9902 0.01152 0.00424 -0.0761 0.1977 0.4696
5.250 1.0122 0.01157 0.00443 -0.0751 0.1922 0.5408
5.500 1.0329 0.01166 0.00465 -0.0737 0.1862 0.6088
7.000 1.1779 0.01342 0.00680 -0.0714 0.1105 1.0000
7.250 1.1961 0.01366 0.00704 -0.0696 0.1096 1.0000
7.500 1.2142 0.01390 0.00730 -0.0679 0.1089 1.0000
7.750 1.2325 0.01417 0.00757 -0.0662 0.1083 1.0000
8.000 1.2504 0.01446 0.00787 -0.0645 0.1075 1.0000
8.250 1.2687 0.01475 0.00818 -0.0630 0.1071 1.0000
8.500 1.2867 0.01507 0.00851 -0.0614 0.1066 1.0000
8.750 1.3045 0.01541 0.00887 -0.0599 0.1061 1.0000
9.000 1.3219 0.01578 0.00925 -0.0584 0.1055 1.0000
9.250 1.3393 0.01616 0.00966 -0.0569 0.1051 1.0000
9.500 1.3566 0.01657 0.01009 -0.0555 0.1048 1.0000
9.750 1.3731 0.01703 0.01057 -0.0541 0.1043 1.0000
10.000 1.3888 0.01755 0.01111 -0.0526 0.1033 1.0000
10.250 1.4044 0.01810 0.01169 -0.0512 0.1024 1.0000
10.500 1.4184 0.01877 0.01237 -0.0497 0.1007 1.0000
10.750 1.4331 0.01943 0.01308 -0.0484 0.0998 1.0000
11.000 1.4475 0.02016 0.01384 -0.0472 0.0991 1.0000
11.250 1.4613 0.02095 0.01467 -0.0460 0.0984 1.0000
11.500 1.4768 0.02168 0.01544 -0.0450 0.0982 1.0000
11.750 1.4924 0.02242 0.01623 -0.0442 0.0979 1.0000
12.000 1.5073 0.02324 0.01709 -0.0434 0.0977 1.0000
12.250 1.5221 0.02409 0.01799 -0.0426 0.0972 1.0000
12.500 1.5360 0.02505 0.01900 -0.0419 0.0969 1.0000
12.750 1.5499 0.02602 0.02002 -0.0412 0.0960 1.0000
13.000 1.5629 0.02709 0.02114 -0.0405 0.0950 1.0000
13.250 1.5746 0.02828 0.02236 -0.0399 0.0933 1.0000
13.500 1.5848 0.02964 0.02377 -0.0392 0.0923 1.0000
13.750 1.5934 0.03115 0.02531 -0.0385 0.0905 1.0000
14.000 1.6012 0.03275 0.02696 -0.0379 0.0896 1.0000
14.250 1.6072 0.03455 0.02881 -0.0373 0.0884 1.0000
14.500 1.6141 0.03632 0.03063 -0.0368 0.0869 1.0000
14.750 1.6242 0.03779 0.03215 -0.0364 0.0855 1.0000
15.000 1.6315 0.03954 0.03397 -0.0360 0.0831 1.0000
15.250 1.6322 0.04199 0.03640 -0.0356 0.0756 1.0000
15.500 1.6109 0.04680 0.04110 -0.0352 0.0571 1.0000
15.750 1.5857 0.05232 0.04663 -0.0351 0.0476 1.0000
16.000 1.5705 0.05693 0.05130 -0.0353 0.0424 1.0000
16.250 1.5571 0.06141 0.05584 -0.0356 0.0383 1.0000
16.500 1.5419 0.06621 0.06071 -0.0361 0.0339 1.0000
16.750 1.5190 0.07206 0.06661 -0.0368 0.0274 1.0000
17.000 1.4976 0.07785 0.07244 -0.0377 0.0216 1.0000
17.250 1.4789 0.08340 0.07804 -0.0387 0.0177 1.0000
17.500 1.4664 0.08815 0.08287 -0.0396 0.0161 1.0000
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Polar data table (+)
Polar graphs
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