GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 432 AIRFOIL (goe432-il) Reynolds number: 100,000 Max Cl/Cd: 56.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe432-il-100000-n5.txt Download as CSV file: xf-goe432-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 432 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3422 0.09090 0.08634 -0.0219 1.0000 0.0428
-7.000 -0.3464 0.08868 0.08420 -0.0210 1.0000 0.0435
-6.750 -0.3479 0.08614 0.08173 -0.0210 1.0000 0.0441
-6.500 -0.3484 0.08347 0.07911 -0.0214 1.0000 0.0442
-6.250 -0.3476 0.08061 0.07631 -0.0221 1.0000 0.0444
-6.000 -0.3451 0.07760 0.07333 -0.0231 1.0000 0.0441
-5.500 -0.3259 0.06600 0.06161 -0.0333 1.0000 0.0293
-5.250 -0.3164 0.06281 0.05842 -0.0338 0.9997 0.0288
-5.000 -0.2786 0.05707 0.05253 -0.0417 0.9937 0.0283
-4.750 -0.2338 0.04979 0.04494 -0.0514 0.9875 0.0289
-4.500 -0.1942 0.04325 0.03805 -0.0584 0.9814 0.0303
-4.250 -0.1562 0.03835 0.03279 -0.0633 0.9765 0.0307
-4.000 -0.1227 0.03437 0.02841 -0.0664 0.9700 0.0316
-3.750 -0.0844 0.03116 0.02474 -0.0697 0.9652 0.0348
-3.500 -0.0503 0.02742 0.02021 -0.0713 0.9582 0.0376
-3.250 -0.0133 0.02479 0.01706 -0.0735 0.9529 0.0406
-3.000 0.0189 0.02366 0.01569 -0.0745 0.9445 0.0460
-2.750 0.0577 0.02180 0.01322 -0.0761 0.9383 0.0508
-2.500 0.0892 0.02068 0.01203 -0.0769 0.9287 0.0573
-2.250 0.1292 0.01963 0.01061 -0.0787 0.9221 0.0639
-2.000 0.1588 0.01855 0.00952 -0.0789 0.9105 0.0688
-1.750 0.1909 0.01773 0.00862 -0.0793 0.8995 0.0731
-1.500 0.2242 0.01705 0.00787 -0.0800 0.8884 0.0801
-1.250 0.2569 0.01639 0.00721 -0.0805 0.8763 0.0857
-1.000 0.2895 0.01587 0.00659 -0.0810 0.8627 0.0918
-0.750 0.3225 0.01534 0.00606 -0.0816 0.8475 0.1017
-0.500 0.3564 0.01483 0.00558 -0.0823 0.8310 0.1239
-0.250 0.3924 0.01405 0.00525 -0.0836 0.8125 0.2575
0.000 0.4236 0.01277 0.00500 -0.0840 0.7905 0.6030
0.500 0.5102 0.01213 0.00436 -0.0887 0.7274 1.0000
0.750 0.5390 0.01226 0.00421 -0.0884 0.6933 1.0000
1.000 0.5664 0.01244 0.00413 -0.0879 0.6608 1.0000
1.250 0.5929 0.01266 0.00409 -0.0872 0.6305 1.0000
1.500 0.6187 0.01290 0.00410 -0.0865 0.6037 1.0000
1.750 0.6441 0.01317 0.00415 -0.0858 0.5805 1.0000
2.000 0.6694 0.01345 0.00425 -0.0851 0.5606 1.0000
2.250 0.6947 0.01374 0.00438 -0.0844 0.5435 1.0000
2.500 0.7197 0.01404 0.00454 -0.0837 0.5267 1.0000
2.750 0.7445 0.01435 0.00473 -0.0830 0.5102 1.0000
3.000 0.7693 0.01465 0.00494 -0.0823 0.4953 1.0000
3.250 0.7940 0.01494 0.00517 -0.0816 0.4813 1.0000
3.500 0.8185 0.01523 0.00542 -0.0808 0.4667 1.0000
3.750 0.8430 0.01552 0.00567 -0.0801 0.4530 1.0000
4.000 0.8675 0.01581 0.00595 -0.0794 0.4406 1.0000
4.250 0.8918 0.01610 0.00625 -0.0787 0.4280 1.0000
4.500 0.9158 0.01641 0.00655 -0.0779 0.4147 1.0000
4.750 0.9395 0.01672 0.00685 -0.0770 0.4004 1.0000
5.000 0.9629 0.01704 0.00720 -0.0762 0.3850 1.0000
5.250 0.9860 0.01737 0.00755 -0.0752 0.3689 1.0000
5.500 1.0087 0.01773 0.00793 -0.0743 0.3516 1.0000
5.750 1.0308 0.01813 0.00832 -0.0732 0.3328 1.0000
6.000 1.0523 0.01858 0.00877 -0.0721 0.3131 1.0000
6.250 1.0737 0.01905 0.00924 -0.0710 0.2921 1.0000
6.500 1.0946 0.01956 0.00973 -0.0699 0.2713 1.0000
6.750 1.1152 0.02012 0.01027 -0.0687 0.2540 1.0000
7.250 1.1563 0.02131 0.01151 -0.0664 0.2278 1.0000
7.500 1.1767 0.02194 0.01219 -0.0652 0.2177 1.0000
7.750 1.1964 0.02263 0.01291 -0.0640 0.2094 1.0000
8.000 1.2163 0.02332 0.01368 -0.0628 0.2022 1.0000
8.250 1.2357 0.02408 0.01454 -0.0616 0.1962 1.0000
8.500 1.2555 0.02484 0.01543 -0.0604 0.1900 1.0000
8.750 1.2741 0.02574 0.01635 -0.0591 0.1847 1.0000
9.000 1.2940 0.02656 0.01738 -0.0579 0.1788 1.0000
9.250 1.3117 0.02749 0.01838 -0.0566 0.1716 1.0000
9.500 1.3269 0.02833 0.01940 -0.0549 0.1612 1.0000
9.750 1.3388 0.02911 0.02035 -0.0529 0.1486 1.0000
10.000 1.3504 0.02975 0.02118 -0.0508 0.1345 1.0000
10.250 1.3632 0.03031 0.02195 -0.0489 0.1179 1.0000
10.500 1.3743 0.03103 0.02279 -0.0468 0.1005 1.0000
10.750 1.3791 0.03226 0.02395 -0.0441 0.0815 1.0000
11.000 1.3797 0.03403 0.02568 -0.0412 0.0572 1.0000
11.250 1.3744 0.03635 0.02785 -0.0381 0.0410 1.0000
11.500 1.3672 0.03893 0.03041 -0.0352 0.0339 1.0000
11.750 1.3618 0.04149 0.03312 -0.0329 0.0302 1.0000
12.000 1.3534 0.04448 0.03624 -0.0311 0.0280 1.0000
12.250 1.3425 0.04795 0.03984 -0.0299 0.0267 1.0000
12.500 1.3346 0.05142 0.04354 -0.0294 0.0254 1.0000
12.750 1.3248 0.05546 0.04784 -0.0296 0.0242 1.0000
13.000 1.3137 0.05998 0.05257 -0.0305 0.0234 1.0000
13.250 1.3015 0.06506 0.05784 -0.0321 0.0226 1.0000
13.500 1.2883 0.07063 0.06360 -0.0342 0.0222 1.0000
13.750 1.2739 0.07666 0.06982 -0.0367 0.0217 1.0000
14.000 1.2589 0.08298 0.07631 -0.0395 0.0215 1.0000
14.250 1.2437 0.08958 0.08307 -0.0425 0.0213 1.0000
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Polar data table (+)
Polar graphs
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