GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.87 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417a-il-1000000-n5.txt Download as CSV file: xf-goe417a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417A (GEW. PLATTE) 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3186 0.10804 0.10629 -0.0360 0.9927 0.0083
-9.750 -0.3094 0.10481 0.10307 -0.0381 0.9913 0.0085
-9.500 -0.3024 0.10034 0.09859 -0.0410 0.9896 0.0093
-9.250 -0.2897 0.09736 0.09561 -0.0437 0.9881 0.0095
-9.000 -0.2744 0.09480 0.09305 -0.0465 0.9867 0.0096
-8.750 -0.2577 0.09208 0.09033 -0.0497 0.9853 0.0098
-8.500 -0.2430 0.08984 0.08808 -0.0521 0.9830 0.0103
-8.250 -0.2321 0.08694 0.08519 -0.0545 0.9794 0.0106
-8.000 -0.2199 0.08257 0.08081 -0.0590 0.9764 0.0119
-7.750 -0.1995 0.08009 0.07831 -0.0626 0.9751 0.0121
-7.500 -0.1821 0.07785 0.07606 -0.0653 0.9724 0.0123
-7.250 -0.1642 0.07554 0.07375 -0.0680 0.9693 0.0128
-7.000 -0.1408 0.07162 0.06980 -0.0736 0.9666 0.0146
-6.750 -0.1164 0.06918 0.06735 -0.0776 0.9651 0.0149
-6.500 -0.0891 0.06690 0.06506 -0.0820 0.9640 0.0156
-6.250 -0.0663 0.06434 0.06247 -0.0856 0.9603 0.0171
-6.000 -0.0274 0.06086 0.05890 -0.0948 0.9558 0.0175
-5.750 -0.0074 0.05768 0.05571 -0.0968 0.9535 0.0177
-5.500 0.0156 0.05536 0.05338 -0.0995 0.9501 0.0179
-5.250 0.0373 0.05319 0.05118 -0.1017 0.9453 0.0180
-5.000 0.0642 0.05092 0.04887 -0.1050 0.9414 0.0183
-4.750 0.0885 0.04883 0.04674 -0.1074 0.9362 0.0188
-4.500 0.1134 0.04668 0.04454 -0.1097 0.9295 0.0192
-4.250 0.1386 0.04456 0.04236 -0.1118 0.9220 0.0197
-4.000 0.1644 0.04247 0.04021 -0.1138 0.9140 0.0199
-3.750 0.1891 0.04049 0.03816 -0.1153 0.9069 0.0200
-3.500 0.2162 0.03854 0.03612 -0.1170 0.8986 0.0202
-3.250 0.2415 0.03678 0.03429 -0.1180 0.8903 0.0202
-3.000 0.2671 0.03506 0.03248 -0.1189 0.8813 0.0202
-2.750 0.2917 0.03346 0.03081 -0.1194 0.8699 0.0203
-2.500 0.3156 0.03193 0.02915 -0.1196 0.8500 0.0203
-2.250 0.3364 0.03073 0.02769 -0.1187 0.7988 0.0203
-2.000 0.3527 0.02972 0.02636 -0.1168 0.7431 0.0203
-1.500 0.3938 0.02732 0.02361 -0.1149 0.6909 0.0203
-1.250 0.4158 0.02607 0.02221 -0.1140 0.6704 0.0203
-1.000 0.4375 0.02491 0.02090 -0.1130 0.6472 0.0203
-0.750 0.4590 0.02378 0.01960 -0.1119 0.6209 0.0203
-0.500 0.4797 0.02275 0.01837 -0.1105 0.5878 0.0203
-0.250 0.5015 0.02171 0.01712 -0.1091 0.5611 0.0203
0.000 0.5059 0.00684 0.00223 -0.1027 0.5281 0.0206
0.250 0.5272 0.00635 0.00167 -0.1020 0.5153 0.0207
0.500 0.5490 0.00600 0.00122 -0.1013 0.5014 0.0210
0.750 0.5719 0.00571 0.00083 -0.1006 0.4880 0.0216
1.000 0.5957 0.00547 0.00047 -0.0997 0.4743 0.0228
1.250 0.6206 0.00531 0.00018 -0.0987 0.4610 0.0233
1.500 0.6578 0.01628 0.01083 -0.1011 0.4547 0.0233
1.750 0.6811 0.01587 0.01025 -0.0998 0.4341 0.0234
2.000 0.7014 0.01556 0.00967 -0.0980 0.3862 0.0235
2.250 0.7167 0.01572 0.00931 -0.0955 0.2828 0.0235
2.500 0.7350 0.01569 0.00892 -0.0934 0.2165 0.0235
2.750 0.7571 0.01535 0.00841 -0.0921 0.1958 0.0235
3.000 0.7801 0.01494 0.00790 -0.0909 0.1856 0.0235
3.250 0.8033 0.01456 0.00741 -0.0898 0.1774 0.0235
3.500 0.8268 0.01415 0.00691 -0.0887 0.1709 0.0235
3.750 0.8498 0.01378 0.00643 -0.0875 0.1618 0.0235
4.000 0.8727 0.01324 0.00581 -0.0865 0.1533 0.0227
4.250 0.8966 0.01296 0.00541 -0.0855 0.1452 0.0227
5.250 0.9806 0.01382 0.00565 -0.0799 0.0360 0.0279
5.500 1.0031 0.01390 0.00568 -0.0788 0.0315 0.0279
5.750 1.0265 0.01366 0.00544 -0.0778 0.0283 0.0285
6.000 1.0493 0.01361 0.00541 -0.0768 0.0276 0.0288
6.250 1.0714 0.01368 0.00552 -0.0756 0.0267 0.0286
6.500 1.0926 0.01371 0.00560 -0.0743 0.0256 0.0264
6.750 1.1132 0.01382 0.00571 -0.0728 0.0243 0.0255
7.000 1.1336 0.01399 0.00588 -0.0713 0.0232 0.0249
7.250 1.1533 0.01422 0.00612 -0.0697 0.0217 0.0246
7.500 1.1722 0.01453 0.00647 -0.0679 0.0203 0.0245
7.750 1.1924 0.01471 0.00669 -0.0664 0.0199 0.0248
8.000 1.2121 0.01494 0.00695 -0.0648 0.0195 0.0252
8.250 1.2307 0.01519 0.00724 -0.0631 0.0190 0.0266
8.500 1.2484 0.01546 0.00755 -0.0611 0.0183 0.0275
8.750 1.2656 0.01573 0.00787 -0.0591 0.0177 0.0294
9.000 1.2827 0.01606 0.00821 -0.0570 0.0171 0.0304
9.250 1.2997 0.01638 0.00852 -0.0551 0.0161 0.0304
9.500 1.3149 0.01685 0.00902 -0.0527 0.0153 0.0311
9.750 1.3323 0.01715 0.00934 -0.0509 0.0146 0.0327
10.000 1.3485 0.01752 0.00980 -0.0489 0.0142 0.0719
10.250 1.5418 0.01859 0.01208 -0.0881 0.0114 1.0000
10.500 1.5554 0.01915 0.01269 -0.0855 0.0107 1.0000
10.750 1.5688 0.01959 0.01318 -0.0829 0.0105 1.0000
11.000 1.5801 0.01997 0.01361 -0.0798 0.0101 1.0000
11.250 1.5901 0.02039 0.01409 -0.0766 0.0097 1.0000
11.500 1.6006 0.02083 0.01458 -0.0735 0.0091 1.0000
11.750 1.6110 0.02131 0.01508 -0.0705 0.0085 1.0000
12.000 1.6214 0.02184 0.01564 -0.0676 0.0077 1.0000
12.250 1.6302 0.02249 0.01634 -0.0645 0.0072 1.0000
12.500 1.6398 0.02311 0.01704 -0.0616 0.0069 1.0000
12.750 1.6486 0.02381 0.01779 -0.0587 0.0064 1.0000
13.000 1.6570 0.02456 0.01860 -0.0558 0.0058 1.0000
13.250 1.6645 0.02539 0.01949 -0.0529 0.0055 1.0000
13.500 1.6705 0.02636 0.02052 -0.0499 0.0049 1.0000
13.750 1.6760 0.02739 0.02163 -0.0470 0.0047 1.0000
14.000 1.6815 0.02845 0.02277 -0.0443 0.0045 1.0000
14.250 1.6860 0.02962 0.02404 -0.0415 0.0044 1.0000
14.500 1.6900 0.03088 0.02539 -0.0389 0.0043 1.0000
14.750 1.6931 0.03226 0.02686 -0.0364 0.0041 1.0000
15.000 1.6952 0.03380 0.02851 -0.0340 0.0040 1.0000
15.250 1.6962 0.03549 0.03030 -0.0317 0.0039 1.0000
15.500 1.6961 0.03738 0.03229 -0.0296 0.0038 1.0000
15.750 1.6947 0.03951 0.03453 -0.0277 0.0037 1.0000
16.000 1.6927 0.04182 0.03694 -0.0261 0.0036 1.0000
16.250 1.6911 0.04423 0.03946 -0.0249 0.0035 1.0000
16.500 1.6867 0.04710 0.04243 -0.0239 0.0034 1.0000
16.750 1.6809 0.05029 0.04574 -0.0233 0.0033 1.0000
17.000 1.6728 0.05396 0.04954 -0.0230 0.0032 1.0000
17.250 1.6631 0.05806 0.05378 -0.0232 0.0031 1.0000
17.500 1.6549 0.06215 0.05799 -0.0237 0.0032 1.0000
17.750 1.6412 0.06727 0.06325 -0.0247 0.0031 1.0000
18.000 1.6250 0.07302 0.06915 -0.0263 0.0030 1.0000
18.250 1.6078 0.07910 0.07537 -0.0282 0.0030 1.0000
18.500 1.5919 0.08512 0.08153 -0.0303 0.0029 1.0000
18.750 1.5748 0.09159 0.08814 -0.0328 0.0030 1.0000
19.000 1.5489 0.09988 0.09658 -0.0363 0.0029 1.0000
19.250 1.5277 0.10760 0.10445 -0.0397 0.0030 1.0000
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