GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.75 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe380-il-1000000.txt Download as CSV file: xf-goe380-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2993 0.09449 0.09300 -0.0222 1.0000 0.0063
-7.750 -0.3022 0.09255 0.09109 -0.0211 1.0000 0.0063
-7.500 -0.3019 0.09017 0.08873 -0.0217 0.9992 0.0063
-7.250 -0.2798 0.08577 0.08433 -0.0282 0.9956 0.0063
-7.000 -0.2622 0.08014 0.07870 -0.0340 0.9913 0.0065
-6.750 -0.2404 0.07628 0.07483 -0.0387 0.9871 0.0066
-6.500 -0.2143 0.07260 0.07113 -0.0445 0.9835 0.0069
-6.250 -0.1912 0.06884 0.06736 -0.0497 0.9767 0.0070
-6.000 -0.1606 0.06474 0.06323 -0.0566 0.9717 0.0073
-5.750 -0.1282 0.06062 0.05908 -0.0635 0.9654 0.0076
-5.500 -0.0921 0.05639 0.05478 -0.0709 0.9561 0.0078
-5.250 -0.0599 0.05245 0.05076 -0.0766 0.9415 0.0084
-5.000 -0.0328 0.04904 0.04723 -0.0801 0.9186 0.0089
-4.750 -0.0040 0.04594 0.04395 -0.0830 0.8932 0.0095
-4.500 0.0180 0.04317 0.04101 -0.0841 0.8677 0.0096
-4.250 0.0407 0.04025 0.03792 -0.0849 0.8466 0.0096
-4.000 0.0635 0.03731 0.03480 -0.0855 0.8285 0.0097
-3.750 0.0868 0.03427 0.03159 -0.0859 0.8117 0.0097
-1.750 0.2709 0.01153 0.00638 -0.0789 0.6502 0.0125
-1.500 0.2949 0.00954 0.00386 -0.0775 0.6266 0.0115
-1.250 0.3198 0.00901 0.00312 -0.0766 0.6033 0.0123
-1.000 0.3452 0.00870 0.00266 -0.0760 0.5841 0.0136
-0.750 0.3709 0.00852 0.00235 -0.0754 0.5687 0.0144
-0.500 0.3958 0.00811 0.00179 -0.0746 0.5565 0.0161
-0.250 0.4215 0.00792 0.00152 -0.0740 0.5458 0.0189
0.000 0.4476 0.00783 0.00135 -0.0735 0.5358 0.0215
0.250 0.4736 0.00768 0.00125 -0.0730 0.5264 0.0484
0.500 0.5002 0.00773 0.00129 -0.0727 0.5166 0.0642
0.750 0.5266 0.00780 0.00130 -0.0724 0.5054 0.0706
1.000 0.5534 0.00784 0.00133 -0.0721 0.4946 0.0777
1.250 0.5801 0.00791 0.00137 -0.0719 0.4837 0.0842
1.500 0.6068 0.00797 0.00141 -0.0716 0.4738 0.0914
1.750 0.6332 0.00803 0.00141 -0.0713 0.4622 0.0955
2.000 0.6592 0.00803 0.00139 -0.0709 0.4476 0.1021
2.250 0.6854 0.00810 0.00140 -0.0706 0.4315 0.1067
2.500 0.7112 0.00817 0.00141 -0.0702 0.4138 0.1121
2.750 0.7370 0.00826 0.00145 -0.0698 0.3966 0.1171
3.000 0.7625 0.00838 0.00151 -0.0694 0.3805 0.1241
3.500 0.8635 0.00714 0.00197 -0.0806 0.3474 1.0000
3.750 0.8875 0.00732 0.00207 -0.0799 0.3379 1.0000
4.000 0.9120 0.00744 0.00218 -0.0792 0.3305 1.0000
4.250 0.9359 0.00761 0.00230 -0.0785 0.3230 1.0000
4.500 0.9604 0.00774 0.00244 -0.0778 0.3161 1.0000
4.750 0.9843 0.00792 0.00258 -0.0771 0.3088 1.0000
5.000 1.0088 0.00804 0.00271 -0.0764 0.3025 1.0000
5.250 1.0326 0.00823 0.00287 -0.0757 0.2944 1.0000
5.500 1.0563 0.00842 0.00302 -0.0750 0.2828 1.0000
5.750 1.0802 0.00859 0.00318 -0.0743 0.2713 1.0000
6.000 1.1033 0.00884 0.00337 -0.0735 0.2546 1.0000
6.250 1.1263 0.00909 0.00356 -0.0727 0.2366 1.0000
6.500 1.1470 0.00954 0.00384 -0.0715 0.2033 1.0000
6.750 1.1664 0.01010 0.00422 -0.0701 0.1719 1.0000
7.000 1.1859 0.01065 0.00464 -0.0688 0.1453 1.0000
7.250 1.1988 0.01178 0.00537 -0.0664 0.0811 1.0000
7.500 1.2072 0.01334 0.00657 -0.0632 0.0147 1.0000
7.750 1.2278 0.01379 0.00709 -0.0620 0.0120 1.0000
8.000 1.2479 0.01428 0.00763 -0.0607 0.0104 1.0000
8.250 1.2662 0.01492 0.00837 -0.0591 0.0089 1.0000
8.500 1.2798 0.01597 0.00959 -0.0567 0.0079 1.0000
8.750 1.2995 0.01642 0.01009 -0.0555 0.0076 1.0000
9.000 1.3180 0.01695 0.01068 -0.0540 0.0069 1.0000
9.250 1.3354 0.01753 0.01131 -0.0525 0.0062 1.0000
9.500 1.3505 0.01826 0.01210 -0.0505 0.0058 1.0000
9.750 1.3633 0.01909 0.01301 -0.0483 0.0055 1.0000
10.000 1.3704 0.02017 0.01421 -0.0452 0.0052 1.0000
10.250 1.3631 0.02173 0.01591 -0.0396 0.0050 1.0000
10.500 1.3534 0.02357 0.01790 -0.0343 0.0048 1.0000
10.750 1.3553 0.02489 0.01933 -0.0312 0.0047 1.0000
11.000 1.3716 0.02536 0.01986 -0.0299 0.0043 1.0000
11.250 1.3690 0.02717 0.02178 -0.0268 0.0043 1.0000
11.500 1.3703 0.02886 0.02357 -0.0245 0.0042 1.0000
11.750 1.3715 0.03071 0.02552 -0.0226 0.0040 1.0000
12.000 1.3676 0.03319 0.02812 -0.0207 0.0040 1.0000
12.250 1.3672 0.03551 0.03054 -0.0194 0.0038 1.0000
12.500 1.3628 0.03842 0.03357 -0.0180 0.0038 1.0000
12.750 1.3682 0.04034 0.03557 -0.0178 0.0036 1.0000
13.000 1.3625 0.04366 0.03902 -0.0168 0.0036 1.0000
13.250 1.3580 0.04695 0.04244 -0.0160 0.0035 1.0000
13.500 1.3570 0.04991 0.04552 -0.0160 0.0035 1.0000
13.750 1.3598 0.05256 0.04824 -0.0172 0.0033 1.0000
14.000 1.3558 0.05610 0.05189 -0.0176 0.0032 1.0000
14.250 1.3559 0.05938 0.05524 -0.0191 0.0030 1.0000
14.500 1.3452 0.06381 0.05983 -0.0189 0.0031 1.0000
14.750 1.3367 0.06822 0.06438 -0.0194 0.0031 1.0000
15.000 1.3319 0.07237 0.06862 -0.0209 0.0030 1.0000
15.250 1.3229 0.07712 0.07351 -0.0221 0.0030 1.0000
15.500 1.3145 0.08198 0.07849 -0.0238 0.0030 1.0000
15.750 1.3053 0.08718 0.08380 -0.0257 0.0030 1.0000
16.000 1.2975 0.09227 0.08899 -0.0280 0.0029 1.0000
16.250 1.2822 0.09880 0.09570 -0.0302 0.0030 1.0000
16.500 1.2739 0.10433 0.10132 -0.0331 0.0029 1.0000
16.750 1.2478 0.11362 0.11091 -0.0365 0.0031 1.0000
17.000 1.2435 0.11875 0.11609 -0.0397 0.0030 1.0000
17.250 1.2222 0.12778 0.12533 -0.0442 0.0031 1.0000
17.500 1.1784 0.14295 0.14085 -0.0522 0.0034 1.0000
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Polar data table (+)
Polar graphs
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