GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 100,000 Max Cl/Cd: 54.41 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe380-il-100000.txt Download as CSV file: xf-goe380-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3113 0.11163 0.10690 -0.0258 1.0000 0.0425
-8.250 -0.3154 0.11072 0.10608 -0.0264 1.0000 0.0426
-8.000 -0.3195 0.10969 0.10516 -0.0273 1.0000 0.0427
-7.750 -0.3180 0.10814 0.10367 -0.0291 1.0000 0.0428
-7.500 -0.3153 0.10645 0.10203 -0.0310 1.0000 0.0429
-7.250 -0.3030 0.09598 0.09161 -0.0232 1.0000 0.0444
-7.000 -0.3000 0.09285 0.08853 -0.0219 1.0000 0.0454
-6.750 -0.2992 0.09038 0.08610 -0.0212 1.0000 0.0463
-6.500 -0.2993 0.08814 0.08393 -0.0205 1.0000 0.0473
-6.250 -0.2998 0.08602 0.08187 -0.0200 1.0000 0.0482
-6.000 -0.3004 0.08393 0.07985 -0.0195 1.0000 0.0494
-5.750 -0.3005 0.08193 0.07790 -0.0191 1.0000 0.0505
-5.500 -0.2995 0.07995 0.07596 -0.0190 1.0000 0.0516
-5.250 -0.2954 0.07816 0.07420 -0.0200 1.0000 0.0534
-5.000 -0.2822 0.07751 0.07349 -0.0240 1.0000 0.0549
-4.750 -0.2624 0.07755 0.07334 -0.0289 1.0000 0.0555
-4.500 -0.2620 0.07289 0.06879 -0.0271 1.0000 0.0560
-4.250 -0.2696 0.06842 0.06448 -0.0225 1.0000 0.0577
-4.000 -0.2651 0.06590 0.06200 -0.0214 1.0000 0.0596
-3.750 -0.2035 0.06277 0.05859 -0.0329 0.9913 0.0677
-3.500 -0.1565 0.05779 0.05346 -0.0408 0.9834 0.0700
-3.250 -0.1243 0.05337 0.04900 -0.0444 0.9740 0.0742
-3.000 -0.0576 0.05165 0.04673 -0.0540 0.9635 0.0823
-2.750 -0.0257 0.04600 0.04119 -0.0575 0.9563 0.0858
-2.500 0.0303 0.04401 0.03871 -0.0636 0.9442 0.0955
-2.250 0.0661 0.03949 0.03424 -0.0668 0.9329 0.1009
-2.000 0.1136 0.03642 0.03088 -0.0711 0.9219 0.1133
-1.750 0.1654 0.03341 0.02756 -0.0761 0.9140 0.1367
-1.500 0.2047 0.03081 0.02477 -0.0786 0.9022 0.1650
-1.000 0.2765 0.02609 0.01978 -0.0817 0.8783 0.2563
-0.750 0.3450 0.02377 0.01609 -0.0831 0.8710 0.0932
-0.500 0.3833 0.02159 0.01354 -0.0837 0.8583 0.0891
-0.250 0.4195 0.02008 0.01157 -0.0837 0.8441 0.0964
0.000 0.4508 0.01867 0.01001 -0.0834 0.8277 0.1181
0.250 0.4804 0.01740 0.00873 -0.0832 0.8104 0.1571
0.500 0.5102 0.01659 0.00789 -0.0828 0.7932 0.1802
0.750 0.5406 0.01608 0.00727 -0.0824 0.7761 0.1970
1.250 0.6323 0.01375 0.00635 -0.0888 0.7387 1.0000
1.500 0.6574 0.01391 0.00617 -0.0876 0.7208 1.0000
1.750 0.6827 0.01408 0.00607 -0.0865 0.7036 1.0000
2.000 0.7063 0.01430 0.00610 -0.0853 0.6849 1.0000
2.250 0.7303 0.01454 0.00616 -0.0842 0.6668 1.0000
2.500 0.7548 0.01479 0.00623 -0.0832 0.6497 1.0000
2.750 0.7794 0.01508 0.00632 -0.0822 0.6331 1.0000
3.000 0.8027 0.01541 0.00655 -0.0811 0.6151 1.0000
3.250 0.8263 0.01577 0.00679 -0.0801 0.5978 1.0000
3.500 0.8500 0.01611 0.00704 -0.0791 0.5804 1.0000
3.750 0.8738 0.01647 0.00724 -0.0780 0.5635 1.0000
4.000 0.8969 0.01685 0.00753 -0.0770 0.5468 1.0000
4.250 0.9201 0.01726 0.00789 -0.0760 0.5314 1.0000
4.500 0.9436 0.01769 0.00827 -0.0751 0.5175 1.0000
4.750 0.9673 0.01812 0.00873 -0.0743 0.5043 1.0000
5.000 0.9912 0.01855 0.00912 -0.0735 0.4917 1.0000
5.250 1.0139 0.01897 0.00958 -0.0725 0.4786 1.0000
5.500 1.0366 0.01938 0.01005 -0.0716 0.4656 1.0000
5.750 1.0592 0.01980 0.01054 -0.0706 0.4529 1.0000
6.000 1.0818 0.02022 0.01109 -0.0696 0.4403 1.0000
6.250 1.1043 0.02063 0.01157 -0.0686 0.4275 1.0000
6.500 1.1266 0.02104 0.01205 -0.0675 0.4142 1.0000
6.750 1.1488 0.02149 0.01258 -0.0665 0.4009 1.0000
7.000 1.1708 0.02198 0.01320 -0.0654 0.3872 1.0000
7.250 1.1925 0.02252 0.01383 -0.0643 0.3731 1.0000
7.500 1.2131 0.02296 0.01434 -0.0629 0.3569 1.0000
7.750 1.2300 0.02301 0.01435 -0.0609 0.3347 1.0000
8.000 1.2451 0.02313 0.01453 -0.0587 0.3126 1.0000
8.250 1.2599 0.02335 0.01488 -0.0565 0.2922 1.0000
8.500 1.2709 0.02337 0.01509 -0.0538 0.2648 1.0000
8.750 1.2825 0.02357 0.01543 -0.0511 0.2287 1.0000
9.000 1.2884 0.02466 0.01619 -0.0478 0.1651 1.0000
9.250 1.2821 0.02730 0.01801 -0.0438 0.0701 1.0000
9.500 1.2785 0.02967 0.02013 -0.0398 0.0515 1.0000
9.750 1.2784 0.03141 0.02200 -0.0360 0.0471 1.0000
10.000 1.2769 0.03321 0.02398 -0.0325 0.0445 1.0000
10.250 1.2713 0.03535 0.02629 -0.0290 0.0424 1.0000
10.500 1.2643 0.03773 0.02882 -0.0261 0.0412 1.0000
10.750 1.2560 0.04043 0.03166 -0.0237 0.0403 1.0000
11.000 1.2489 0.04330 0.03465 -0.0218 0.0393 1.0000
11.250 1.2474 0.04590 0.03742 -0.0204 0.0378 1.0000
11.500 1.2469 0.04856 0.04021 -0.0192 0.0363 1.0000
11.750 1.2499 0.05107 0.04287 -0.0179 0.0351 1.0000
12.000 1.2607 0.05315 0.04503 -0.0161 0.0345 1.0000
12.250 1.2802 0.05515 0.04713 -0.0141 0.0341 1.0000
12.500 1.3019 0.05776 0.04995 -0.0124 0.0340 1.0000
12.750 1.3130 0.06106 0.05356 -0.0111 0.0345 1.0000
13.000 1.3154 0.06488 0.05771 -0.0102 0.0351 1.0000
13.250 1.3103 0.06908 0.06222 -0.0097 0.0357 1.0000
13.500 1.3008 0.07352 0.06695 -0.0098 0.0361 1.0000
13.750 1.2875 0.07840 0.07210 -0.0105 0.0365 1.0000
14.000 1.2719 0.08360 0.07756 -0.0119 0.0367 1.0000
14.250 1.2543 0.08927 0.08347 -0.0140 0.0368 1.0000
14.500 1.2367 0.09539 0.08981 -0.0167 0.0373 1.0000
14.750 1.2172 0.10199 0.09661 -0.0201 0.0376 1.0000
15.000 1.1987 0.10892 0.10371 -0.0238 0.0381 1.0000
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Polar data table (+)
Polar graphs
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