GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 100,000 Max Cl/Cd: 65.55 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417a-il-100000.txt Download as CSV file: xf-goe417a-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3465 0.10608 0.10109 -0.0151 1.0000 0.0332
-7.500 -0.3505 0.10449 0.09955 -0.0135 1.0000 0.0336
-7.250 -0.3525 0.10278 0.09788 -0.0123 1.0000 0.0340
-7.000 -0.3517 0.10083 0.09597 -0.0118 1.0000 0.0345
-6.750 -0.3497 0.09887 0.09405 -0.0116 1.0000 0.0350
-6.500 -0.3462 0.09699 0.09220 -0.0117 1.0000 0.0355
-6.250 -0.3392 0.09589 0.09112 -0.0133 1.0000 0.0362
-6.000 -0.3246 0.09628 0.09149 -0.0182 1.0000 0.0366
-5.750 -0.3070 0.09572 0.09090 -0.0231 1.0000 0.0368
-5.500 -0.3101 0.09005 0.08531 -0.0186 1.0000 0.0371
-5.250 -0.3079 0.08612 0.08142 -0.0164 1.0000 0.0375
-5.000 -0.3017 0.08311 0.07844 -0.0158 1.0000 0.0379
-4.750 -0.2933 0.08042 0.07575 -0.0159 1.0000 0.0386
-4.500 -0.2826 0.07793 0.07326 -0.0165 1.0000 0.0393
-4.250 -0.2700 0.07553 0.07086 -0.0175 1.0000 0.0401
-4.000 -0.2557 0.07322 0.06854 -0.0188 1.0000 0.0410
-3.750 -0.2392 0.07101 0.06630 -0.0205 1.0000 0.0421
-3.500 -0.2165 0.06932 0.06456 -0.0234 1.0000 0.0435
-3.250 -0.1627 0.07115 0.06608 -0.0330 1.0000 0.0447
-3.000 -0.1634 0.06620 0.06125 -0.0304 1.0000 0.0451
-2.750 -0.1574 0.06275 0.05785 -0.0290 1.0000 0.0458
-2.500 -0.1449 0.06017 0.05527 -0.0289 1.0000 0.0467
-2.250 -0.1282 0.05806 0.05313 -0.0296 1.0000 0.0479
-2.000 -0.1022 0.05601 0.05103 -0.0321 0.9983 0.0495
-1.750 -0.0511 0.05397 0.04883 -0.0393 0.9908 0.0526
-1.500 0.0242 0.05483 0.04926 -0.0497 0.9820 0.0548
-1.250 0.0431 0.04977 0.04433 -0.0512 0.9747 0.0561
-1.000 0.0780 0.04710 0.04162 -0.0548 0.9672 0.0591
-0.750 0.1268 0.04617 0.04049 -0.0598 0.9581 0.0650
-0.500 0.1700 0.04478 0.03890 -0.0637 0.9485 0.0671
-0.250 0.2035 0.04178 0.03593 -0.0667 0.9419 0.0703
0.000 0.2393 0.04048 0.03451 -0.0690 0.9311 0.0757
0.250 0.2862 0.03927 0.03309 -0.0729 0.9235 0.0800
0.500 0.3176 0.03730 0.03111 -0.0746 0.9135 0.0852
0.750 0.3565 0.03644 0.03005 -0.0766 0.9032 0.0922
1.000 0.4031 0.03543 0.02885 -0.0800 0.8961 0.1034
1.250 0.4346 0.03418 0.02750 -0.0809 0.8840 0.1158
1.500 0.4671 0.03174 0.02514 -0.0824 0.8738 0.1340
1.750 0.5115 0.02976 0.02312 -0.0855 0.8659 0.1779
2.000 0.5420 0.02821 0.02158 -0.0860 0.8529 0.2493
2.250 0.5742 0.02639 0.01982 -0.0866 0.8416 0.3120
2.500 0.6210 0.02416 0.01763 -0.0892 0.8356 0.3563
2.750 0.6593 0.02286 0.01631 -0.0902 0.8237 0.3661
3.000 0.7090 0.02183 0.01512 -0.0927 0.8135 0.3455
3.250 0.7673 0.02081 0.01389 -0.0962 0.8046 0.2945
3.500 0.8140 0.02011 0.01294 -0.0975 0.7902 0.2221
3.750 0.8617 0.01938 0.01201 -0.0994 0.7749 0.1690
4.000 0.9137 0.01869 0.01122 -0.1026 0.7588 0.1359
4.250 0.9595 0.01823 0.01068 -0.1050 0.7386 0.1192
4.500 1.0021 0.01785 0.01023 -0.1070 0.7153 0.1134
4.750 1.0365 0.01750 0.00985 -0.1073 0.6839 0.1164
5.000 1.0619 0.01734 0.00955 -0.1057 0.6455 0.1167
5.250 1.0813 0.01734 0.00944 -0.1031 0.6038 0.1190
5.500 1.0993 0.01751 0.00939 -0.1003 0.5588 0.1251
5.750 1.1159 0.01781 0.00951 -0.0974 0.5129 0.1411
6.000 1.1825 0.01804 0.01021 -0.1061 0.3922 1.0000
6.250 1.1913 0.01903 0.01062 -0.1023 0.3170 1.0000
6.500 1.1993 0.02031 0.01134 -0.0987 0.2509 1.0000
6.750 1.2073 0.02177 0.01232 -0.0951 0.1818 1.0000
7.000 1.2166 0.02323 0.01325 -0.0917 0.1082 1.0000
7.250 1.2260 0.02463 0.01436 -0.0883 0.0876 1.0000
7.500 1.2345 0.02608 0.01568 -0.0847 0.0796 1.0000
7.750 1.2457 0.02735 0.01702 -0.0815 0.0748 1.0000
8.000 1.2564 0.02881 0.01847 -0.0784 0.0707 1.0000
8.250 1.2695 0.03075 0.02032 -0.0759 0.0669 1.0000
8.500 1.2888 0.03228 0.02195 -0.0742 0.0640 1.0000
8.750 1.3128 0.03423 0.02401 -0.0733 0.0619 1.0000
9.000 1.3394 0.03648 0.02635 -0.0729 0.0603 1.0000
9.250 1.3653 0.03915 0.02907 -0.0727 0.0578 1.0000
9.500 1.3944 0.04397 0.03399 -0.0735 0.0558 1.0000
9.750 1.4104 0.04697 0.03735 -0.0715 0.0557 1.0000
10.000 1.4237 0.05013 0.04092 -0.0691 0.0560 1.0000
10.250 1.4324 0.05232 0.04349 -0.0659 0.0565 1.0000
10.500 1.4353 0.05446 0.04616 -0.0616 0.0577 1.0000
10.750 1.4221 0.05786 0.05030 -0.0556 0.0598 1.0000
11.000 1.4068 0.06213 0.05511 -0.0503 0.0618 1.0000
11.250 1.3915 0.06610 0.05944 -0.0455 0.0630 1.0000
11.500 1.3733 0.06976 0.06336 -0.0407 0.0642 1.0000
11.750 1.3535 0.07352 0.06734 -0.0366 0.0650 1.0000
12.000 1.3380 0.07793 0.07191 -0.0338 0.0662 1.0000
12.250 1.1979 0.07549 0.06992 -0.0210 0.0652 1.0000
12.500 1.1690 0.08096 0.07557 -0.0201 0.0658 1.0000
12.750 1.1377 0.08697 0.08170 -0.0203 0.0661 1.0000
13.000 1.1049 0.09355 0.08843 -0.0217 0.0665 1.0000
13.250 1.0971 0.09905 0.09402 -0.0221 0.0685 1.0000
13.500 1.0527 0.10687 0.10200 -0.0262 0.0686 1.0000
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Polar data table (+)
Polar graphs
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