GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 100,000 Max Cl/Cd: 56.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417a-il-100000-n5.txt Download as CSV file: xf-goe417a-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3462 0.10942 0.10427 -0.0178 1.0000 0.0289
-8.000 -0.3500 0.10830 0.10321 -0.0167 1.0000 0.0290
-7.750 -0.3555 0.10741 0.10237 -0.0152 1.0000 0.0291
-7.500 -0.3570 0.10633 0.10134 -0.0150 1.0000 0.0292
-7.250 -0.3555 0.10510 0.10013 -0.0155 1.0000 0.0293
-7.000 -0.3517 0.10386 0.09892 -0.0167 1.0000 0.0294
-6.500 -0.3428 0.09787 0.09300 -0.0161 1.0000 0.0297
-6.250 -0.3409 0.09380 0.08897 -0.0138 1.0000 0.0300
-6.000 -0.3369 0.09092 0.08612 -0.0130 1.0000 0.0304
-5.750 -0.3311 0.08842 0.08364 -0.0129 1.0000 0.0307
-5.500 -0.3240 0.08600 0.08124 -0.0132 1.0000 0.0311
-5.250 -0.3157 0.08359 0.07884 -0.0136 1.0000 0.0315
-5.000 -0.3019 0.08097 0.07621 -0.0153 0.9991 0.0319
-4.750 -0.2712 0.07759 0.07277 -0.0209 0.9948 0.0327
-4.500 -0.2389 0.07432 0.06943 -0.0266 0.9897 0.0337
-4.250 -0.1976 0.07136 0.06638 -0.0342 0.9846 0.0352
-4.000 -0.1381 0.07029 0.06505 -0.0457 0.9774 0.0363
-3.750 -0.0903 0.06833 0.06289 -0.0535 0.9712 0.0365
-3.500 -0.0692 0.06344 0.05804 -0.0553 0.9661 0.0368
-3.250 -0.0509 0.05931 0.05395 -0.0562 0.9610 0.0374
-3.000 -0.0254 0.05621 0.05082 -0.0585 0.9556 0.0381
-2.750 0.0063 0.05350 0.04804 -0.0619 0.9511 0.0391
-2.500 0.0351 0.05119 0.04566 -0.0644 0.9443 0.0406
-2.250 0.0744 0.04894 0.04330 -0.0687 0.9402 0.0433
-2.000 0.1150 0.04824 0.04237 -0.0721 0.9323 0.0453
-1.750 0.1638 0.04763 0.04146 -0.0767 0.9277 0.0458
-1.500 0.1800 0.04388 0.03780 -0.0766 0.9197 0.0464
-1.250 0.2056 0.04092 0.03486 -0.0780 0.9143 0.0476
-1.000 0.2315 0.03901 0.03290 -0.0787 0.9066 0.0493
-0.750 0.2642 0.03729 0.03109 -0.0804 0.9000 0.0517
-0.500 0.3020 0.03660 0.03019 -0.0820 0.8929 0.0553
-0.250 0.3348 0.03522 0.02864 -0.0829 0.8850 0.0568
0.000 0.3591 0.03268 0.02617 -0.0835 0.8783 0.0596
0.250 0.3879 0.03156 0.02495 -0.0837 0.8689 0.0649
0.750 0.4485 0.02868 0.02188 -0.0845 0.8514 0.0713
1.000 0.4759 0.02763 0.02072 -0.0840 0.8384 0.0771
1.250 0.5067 0.02653 0.01946 -0.0839 0.8247 0.0819
1.500 0.5357 0.02508 0.01797 -0.0839 0.8097 0.0882
1.750 0.5691 0.02389 0.01665 -0.0845 0.7944 0.0966
2.000 0.6052 0.02271 0.01535 -0.0857 0.7790 0.1090
2.250 0.6421 0.02149 0.01402 -0.0873 0.7630 0.1351
2.500 0.6795 0.02027 0.01272 -0.0891 0.7448 0.1684
2.750 0.7205 0.01946 0.01170 -0.0908 0.7242 0.1713
3.500 0.8278 0.01849 0.00985 -0.0910 0.6538 0.0542
3.750 0.8570 0.01815 0.00941 -0.0908 0.6280 0.0527
4.000 0.8879 0.01794 0.00910 -0.0911 0.6044 0.0529
4.250 0.9215 0.01789 0.00892 -0.0920 0.5804 0.0552
4.500 0.9573 0.01780 0.00874 -0.0934 0.5541 0.0555
4.750 0.9886 0.01779 0.00860 -0.0939 0.5222 0.0558
5.000 1.0122 0.01796 0.00858 -0.0928 0.4792 0.0565
5.250 1.0306 0.01827 0.00865 -0.0908 0.4167 0.0578
5.500 1.0451 0.01891 0.00887 -0.0882 0.3346 0.0622
5.750 1.0606 0.01965 0.00922 -0.0859 0.2817 0.0669
6.000 1.0771 0.02034 0.00967 -0.0839 0.2477 0.0704
6.250 1.0938 0.02102 0.01017 -0.0819 0.2201 0.0766
6.500 1.1112 0.02162 0.01069 -0.0799 0.1984 0.0890
6.750 1.1843 0.02284 0.01219 -0.0917 0.0772 1.0000
7.000 1.1960 0.02413 0.01325 -0.0888 0.0611 1.0000
7.250 1.2082 0.02537 0.01442 -0.0860 0.0534 1.0000
7.500 1.2225 0.02635 0.01550 -0.0835 0.0484 1.0000
7.750 1.2348 0.02749 0.01674 -0.0808 0.0453 1.0000
8.000 1.2432 0.02894 0.01825 -0.0775 0.0429 1.0000
8.250 1.2551 0.03006 0.01948 -0.0747 0.0408 1.0000
8.500 1.2666 0.03122 0.02075 -0.0720 0.0381 1.0000
8.750 1.2768 0.03249 0.02210 -0.0692 0.0360 1.0000
9.000 1.2856 0.03394 0.02361 -0.0662 0.0347 1.0000
9.250 1.2952 0.03565 0.02533 -0.0635 0.0335 1.0000
9.500 1.3105 0.03781 0.02750 -0.0618 0.0323 1.0000
9.750 1.3240 0.03917 0.02908 -0.0595 0.0310 1.0000
10.000 1.3365 0.04071 0.03080 -0.0572 0.0293 1.0000
10.250 1.3485 0.04243 0.03270 -0.0550 0.0280 1.0000
10.500 1.3612 0.04444 0.03488 -0.0531 0.0271 1.0000
10.750 1.3721 0.04657 0.03719 -0.0509 0.0264 1.0000
11.000 1.3813 0.04889 0.03966 -0.0487 0.0258 1.0000
11.250 1.3895 0.05154 0.04249 -0.0466 0.0253 1.0000
11.500 1.3958 0.05484 0.04596 -0.0445 0.0248 1.0000
11.750 1.3893 0.05728 0.04872 -0.0406 0.0245 1.0000
12.000 1.3794 0.05961 0.05138 -0.0366 0.0242 1.0000
12.250 1.3676 0.06226 0.05436 -0.0331 0.0238 1.0000
12.500 1.3532 0.06530 0.05773 -0.0301 0.0234 1.0000
12.750 1.3392 0.06875 0.06145 -0.0278 0.0232 1.0000
13.000 1.3232 0.07253 0.06550 -0.0263 0.0230 1.0000
13.250 1.3055 0.07684 0.07007 -0.0256 0.0229 1.0000
13.500 1.2873 0.08171 0.07518 -0.0257 0.0230 1.0000
13.750 1.2670 0.08712 0.08083 -0.0270 0.0228 1.0000
14.000 1.2465 0.09323 0.08715 -0.0291 0.0230 1.0000
14.250 1.2231 0.10035 0.09448 -0.0325 0.0230 1.0000
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Polar data table (+)
Polar graphs
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