GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 438 AIRFOIL (goe438-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.82 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe438-il-1000000.txt Download as CSV file: xf-goe438-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 438 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
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0991 0.03432 0.03155 -0.0862 1.0000 0.0151
-14.500 -1.1164 0.03076 0.02777 -0.0831 1.0000 0.0154
-14.250 -1.1227 0.02820 0.02503 -0.0800 1.0000 0.0158
-14.000 -1.1231 0.02615 0.02282 -0.0771 1.0000 0.0163
-13.750 -1.1189 0.02449 0.02102 -0.0744 1.0000 0.0168
-13.500 -1.1112 0.02314 0.01953 -0.0718 1.0000 0.0175
-13.250 -1.1011 0.02197 0.01823 -0.0695 1.0000 0.0181
-13.000 -1.0913 0.02072 0.01690 -0.0671 1.0000 0.0193
-12.750 -1.0698 0.01965 0.01574 -0.0668 0.9993 0.0207
-12.500 -1.0393 0.01875 0.01477 -0.0681 0.9978 0.0226
-12.250 -1.0074 0.01821 0.01420 -0.0693 0.9963 0.0247
-12.000 -0.9737 0.01795 0.01395 -0.0707 0.9950 0.0265
-11.750 -0.9383 0.01805 0.01408 -0.0721 0.9940 0.0282
-11.500 -0.9061 0.01794 0.01390 -0.0730 0.9923 0.0295
-11.250 -0.8736 0.01786 0.01385 -0.0740 0.9902 0.0306
-11.000 -0.8386 0.01824 0.01430 -0.0752 0.9885 0.0314
-10.750 -0.8033 0.01863 0.01475 -0.0764 0.9871 0.0321
-10.500 -0.7683 0.01885 0.01498 -0.0776 0.9858 0.0329
-10.250 -0.7334 0.01883 0.01492 -0.0791 0.9846 0.0339
-10.000 -0.6975 0.01887 0.01491 -0.0807 0.9835 0.0345
-9.750 -0.6689 0.01803 0.01395 -0.0814 0.9809 0.0354
-9.500 -0.6373 0.01825 0.01424 -0.0820 0.9779 0.0360
-9.250 -0.6032 0.01847 0.01450 -0.0832 0.9757 0.0364
-9.000 -0.5683 0.01858 0.01463 -0.0845 0.9740 0.0370
-8.750 -0.5324 0.01867 0.01471 -0.0861 0.9725 0.0377
-8.500 -0.4976 0.01854 0.01456 -0.0876 0.9710 0.0385
-8.250 -0.4684 0.01804 0.01397 -0.0881 0.9671 0.0393
-8.000 -0.4396 0.01770 0.01353 -0.0883 0.9618 0.0400
-7.750 -0.4064 0.01781 0.01359 -0.0893 0.9581 0.0405
-7.500 -0.3834 0.01590 0.01150 -0.0893 0.9512 0.0417
-7.250 -0.3537 0.01608 0.01171 -0.0895 0.9444 0.0424
-7.000 -0.3242 0.01605 0.01168 -0.0898 0.9375 0.0431
-6.750 -0.2978 0.01558 0.01114 -0.0895 0.9280 0.0436
-6.500 -0.2717 0.01516 0.01064 -0.0892 0.9173 0.0443
-6.250 -0.2460 0.01455 0.00989 -0.0887 0.9050 0.0449
-6.000 -0.2208 0.01394 0.00913 -0.0881 0.8913 0.0455
-5.500 -0.1702 0.01299 0.00792 -0.0868 0.8648 0.0465
-5.250 -0.1445 0.01267 0.00750 -0.0862 0.8528 0.0469
-5.000 -0.1183 0.01256 0.00729 -0.0857 0.8418 0.0472
-4.750 -0.0931 0.01200 0.00660 -0.0851 0.8311 0.0476
-4.500 -0.0691 0.01086 0.00536 -0.0844 0.8212 0.0484
-4.250 -0.0436 0.01043 0.00486 -0.0838 0.8112 0.0490
-4.000 -0.0178 0.01012 0.00452 -0.0833 0.8004 0.0496
-3.750 0.0083 0.00989 0.00425 -0.0828 0.7896 0.0502
-3.500 0.0342 0.00968 0.00399 -0.0822 0.7775 0.0508
-3.250 0.0600 0.00948 0.00374 -0.0816 0.7638 0.0514
-3.000 0.0858 0.00931 0.00351 -0.0810 0.7482 0.0522
-2.750 0.1115 0.00917 0.00331 -0.0804 0.7290 0.0530
-2.500 0.1365 0.00906 0.00311 -0.0796 0.7048 0.0537
-2.250 0.1613 0.00896 0.00290 -0.0788 0.6814 0.0543
-2.000 0.1864 0.00889 0.00273 -0.0781 0.6614 0.0548
-1.750 0.2119 0.00884 0.00261 -0.0775 0.6446 0.0554
-1.500 0.2380 0.00881 0.00252 -0.0769 0.6313 0.0557
-1.250 0.2623 0.00851 0.00214 -0.0761 0.6196 0.0572
-1.000 0.2881 0.00837 0.00197 -0.0756 0.6085 0.0586
-0.750 0.3145 0.00830 0.00188 -0.0751 0.5984 0.0599
-0.250 0.3675 0.00823 0.00175 -0.0743 0.5776 0.0629
0.000 0.3939 0.00821 0.00169 -0.0739 0.5667 0.0642
0.500 0.4469 0.00816 0.00158 -0.0730 0.5434 0.0671
0.750 0.4730 0.00812 0.00151 -0.0726 0.5299 0.0709
1.000 0.4991 0.00814 0.00149 -0.0721 0.5143 0.0746
1.250 0.5250 0.00819 0.00148 -0.0716 0.4966 0.0780
1.500 0.5502 0.00818 0.00149 -0.0710 0.4786 0.1031
1.750 0.5700 0.00753 0.00157 -0.0697 0.4623 0.4068
2.000 0.5818 0.00662 0.00169 -0.0665 0.4481 0.7840
2.250 0.6634 0.00661 0.00197 -0.0781 0.4177 0.9912
2.500 0.7188 0.00686 0.00206 -0.0842 0.3952 0.9999
2.750 0.7422 0.00700 0.00213 -0.0832 0.3833 1.0000
3.000 0.7651 0.00712 0.00221 -0.0821 0.3728 1.0000
3.250 0.7876 0.00728 0.00230 -0.0810 0.3614 1.0000
3.500 0.8099 0.00746 0.00240 -0.0798 0.3479 1.0000
3.750 0.8329 0.00760 0.00250 -0.0787 0.3373 1.0000
4.000 0.8560 0.00775 0.00260 -0.0777 0.3284 1.0000
4.250 0.8790 0.00791 0.00271 -0.0767 0.3195 1.0000
4.500 0.9025 0.00805 0.00283 -0.0757 0.3116 1.0000
4.750 0.9253 0.00823 0.00295 -0.0747 0.3031 1.0000
5.000 0.9491 0.00836 0.00307 -0.0738 0.2963 1.0000
5.250 0.9722 0.00853 0.00321 -0.0728 0.2887 1.0000
5.500 0.9958 0.00868 0.00335 -0.0719 0.2813 1.0000
5.750 1.0189 0.00887 0.00350 -0.0709 0.2732 1.0000
6.000 1.0424 0.00903 0.00364 -0.0701 0.2657 1.0000
6.250 1.0653 0.00923 0.00381 -0.0691 0.2575 1.0000
6.500 1.0887 0.00940 0.00397 -0.0682 0.2500 1.0000
6.750 1.1109 0.00964 0.00416 -0.0671 0.2396 1.0000
7.000 1.1335 0.00985 0.00435 -0.0661 0.2296 1.0000
7.250 1.1559 0.01009 0.00456 -0.0651 0.2192 1.0000
7.500 1.1774 0.01037 0.00479 -0.0639 0.2065 1.0000
7.750 1.1971 0.01076 0.00508 -0.0625 0.1865 1.0000
8.000 1.2131 0.01138 0.00550 -0.0605 0.1537 1.0000
8.250 1.2271 0.01212 0.00603 -0.0582 0.1209 1.0000
8.500 1.2425 0.01276 0.00653 -0.0561 0.0974 1.0000
8.750 1.2529 0.01368 0.00721 -0.0532 0.0647 1.0000
9.000 1.2704 0.01414 0.00765 -0.0515 0.0586 1.0000
9.250 1.2889 0.01451 0.00805 -0.0499 0.0564 1.0000
9.500 1.3045 0.01494 0.00849 -0.0478 0.0542 1.0000
9.750 1.3186 0.01540 0.00896 -0.0454 0.0517 1.0000
10.000 1.3327 0.01586 0.00946 -0.0431 0.0496 1.0000
10.250 1.3497 0.01620 0.00984 -0.0414 0.0489 1.0000
10.500 1.3663 0.01657 0.01025 -0.0396 0.0477 1.0000
10.750 1.3820 0.01700 0.01072 -0.0378 0.0463 1.0000
11.000 1.3964 0.01751 0.01126 -0.0359 0.0449 1.0000
11.250 1.4094 0.01811 0.01188 -0.0338 0.0432 1.0000
11.500 1.4208 0.01881 0.01263 -0.0316 0.0414 1.0000
11.750 1.4386 0.01917 0.01303 -0.0303 0.0404 1.0000
12.000 1.4547 0.01964 0.01355 -0.0289 0.0388 1.0000
12.250 1.4684 0.02027 0.01417 -0.0273 0.0364 1.0000
12.500 1.4806 0.02100 0.01492 -0.0256 0.0341 1.0000
12.750 1.4953 0.02161 0.01556 -0.0242 0.0314 1.0000
13.000 1.5057 0.02252 0.01644 -0.0225 0.0266 1.0000
13.250 1.5137 0.02362 0.01753 -0.0207 0.0226 1.0000
13.500 1.5191 0.02497 0.01888 -0.0189 0.0195 1.0000
13.750 1.5257 0.02631 0.02027 -0.0173 0.0180 1.0000
14.000 1.5286 0.02802 0.02201 -0.0157 0.0165 1.0000
14.250 1.5343 0.02959 0.02365 -0.0145 0.0156 1.0000
14.500 1.5376 0.03142 0.02557 -0.0133 0.0150 1.0000
14.750 1.5403 0.03341 0.02762 -0.0124 0.0144 1.0000
15.000 1.5387 0.03592 0.03020 -0.0116 0.0137 1.0000
15.250 1.5350 0.03879 0.03317 -0.0110 0.0132 1.0000
15.500 1.5360 0.04131 0.03578 -0.0108 0.0130 1.0000
15.750 1.5356 0.04409 0.03866 -0.0107 0.0128 1.0000
16.000 1.5329 0.04722 0.04188 -0.0109 0.0124 1.0000
16.250 1.5291 0.05058 0.04534 -0.0112 0.0122 1.0000
16.500 1.5237 0.05421 0.04907 -0.0117 0.0120 1.0000
16.750 1.5156 0.05825 0.05321 -0.0123 0.0117 1.0000
17.000 1.5070 0.06246 0.05752 -0.0132 0.0116 1.0000
17.250 1.4953 0.06721 0.06237 -0.0143 0.0114 1.0000
17.500 1.4804 0.07248 0.06775 -0.0157 0.0112 1.0000
17.750 1.4652 0.07796 0.07335 -0.0172 0.0111 1.0000
18.000 1.4525 0.08312 0.07862 -0.0188 0.0110 1.0000
18.250 1.4348 0.08915 0.08476 -0.0207 0.0109 1.0000
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Polar data table (+)
Polar graphs
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