GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.97 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe419-il-1000000.txt Download as CSV file: xf-goe419-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3824 0.08975 0.08825 -0.0188 1.0000 0.0075
-7.500 -0.3875 0.08776 0.08630 -0.0176 1.0000 0.0076
-7.250 -0.3879 0.08546 0.08403 -0.0178 1.0000 0.0077
-7.000 -0.3699 0.08159 0.08016 -0.0233 0.9988 0.0079
-4.750 -0.0895 0.03854 0.03651 -0.0807 0.9468 0.0082
-4.500 -0.0461 0.03316 0.03093 -0.0868 0.9395 0.0082
-4.250 0.0011 0.02704 0.02452 -0.0932 0.9321 0.0081
-4.000 0.0387 0.01403 0.01038 -0.0964 0.9179 0.0074
-3.750 0.0728 0.01341 0.00955 -0.0978 0.9038 0.0082
-3.500 0.0967 0.00976 0.00514 -0.0969 0.8899 0.0088
-3.000 0.1476 0.00797 0.00292 -0.0957 0.8684 0.0112
-2.750 0.1732 0.00747 0.00227 -0.0950 0.8596 0.0135
-2.500 0.1999 0.00740 0.00214 -0.0947 0.8510 0.0155
-2.250 0.2248 0.00692 0.00157 -0.0940 0.8421 0.0232
-2.000 0.2521 0.00710 0.00176 -0.0939 0.8336 0.0264
-1.500 0.3033 0.00668 0.00121 -0.0930 0.8154 0.0378
-1.250 0.3294 0.00661 0.00107 -0.0926 0.8058 0.0390
-1.000 0.3553 0.00650 0.00089 -0.0921 0.7954 0.0405
-0.750 0.3809 0.00638 0.00073 -0.0916 0.7837 0.0487
-0.500 0.4060 0.00618 0.00068 -0.0910 0.7707 0.1102
-0.250 0.4310 0.00603 0.00067 -0.0905 0.7554 0.1815
0.000 0.4556 0.00589 0.00068 -0.0899 0.7365 0.2666
0.250 0.5044 0.00432 0.00082 -0.0954 0.7143 0.9869
0.500 0.5451 0.00445 0.00082 -0.0984 0.6892 1.0000
0.750 0.5680 0.00459 0.00084 -0.0974 0.6674 1.0000
1.000 0.5911 0.00473 0.00088 -0.0964 0.6480 1.0000
1.500 0.6361 0.00510 0.00102 -0.0941 0.5939 1.0000
1.750 0.6589 0.00528 0.00109 -0.0931 0.5632 1.0000
2.000 0.6767 0.00578 0.00119 -0.0911 0.4702 1.0000
2.250 0.6919 0.00658 0.00144 -0.0887 0.3549 1.0000
2.500 0.6928 0.00880 0.00226 -0.0839 0.0272 1.0000
2.750 0.7170 0.00901 0.00250 -0.0831 0.0179 1.0000
3.000 0.7406 0.00932 0.00290 -0.0822 0.0139 1.0000
3.250 0.7619 0.00988 0.00359 -0.0807 0.0110 1.0000
3.500 0.7830 0.01047 0.00426 -0.0793 0.0102 1.0000
3.750 0.8072 0.01071 0.00451 -0.0786 0.0092 1.0000
4.000 0.8283 0.01130 0.00517 -0.0772 0.0079 1.0000
4.250 0.8463 0.01223 0.00619 -0.0751 0.0077 1.0000
4.500 0.8625 0.01347 0.00750 -0.0726 0.0080 1.0000
4.750 0.8792 0.01538 0.00946 -0.0701 0.0092 1.0000
6.250 1.0138 0.02791 0.02261 -0.0638 0.0047 1.0000
6.500 1.0311 0.03067 0.02563 -0.0617 0.0047 1.0000
6.750 1.0461 0.03351 0.02873 -0.0594 0.0046 1.0000
7.000 1.0589 0.03646 0.03195 -0.0569 0.0046 1.0000
7.250 1.0704 0.03934 0.03508 -0.0544 0.0046 1.0000
7.500 1.0794 0.04243 0.03846 -0.0516 0.0046 1.0000
7.750 1.0860 0.04558 0.04186 -0.0488 0.0046 1.0000
8.000 1.0902 0.04876 0.04528 -0.0459 0.0046 1.0000
8.250 1.0919 0.05197 0.04871 -0.0429 0.0046 1.0000
8.500 1.0908 0.05523 0.05219 -0.0398 0.0046 1.0000
8.750 1.0868 0.05841 0.05555 -0.0368 0.0046 1.0000
9.000 1.0793 0.06152 0.05883 -0.0336 0.0046 1.0000
9.250 1.0661 0.06416 0.06162 -0.0296 0.0046 1.0000
9.500 1.0490 0.06674 0.06431 -0.0258 0.0046 1.0000
9.750 1.0313 0.06974 0.06743 -0.0234 0.0046 1.0000
10.000 1.0137 0.07321 0.07102 -0.0224 0.0046 1.0000
10.250 0.9958 0.07730 0.07522 -0.0227 0.0046 1.0000
10.500 0.9783 0.08201 0.08003 -0.0243 0.0046 1.0000
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Polar data table (+)
Polar graphs
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