GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 200,000 Max Cl/Cd: 75.06 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe479-il-200000.txt Download as CSV file: xf-goe479-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4028 0.08896 0.08557 -0.0380 1.0000 0.0749
-8.250 -0.3316 0.08055 0.07747 -0.0311 0.9997 0.0776
-8.000 -0.4741 0.08099 0.07765 -0.0436 0.9984 0.0755
-7.750 -0.4519 0.07959 0.07639 -0.0368 0.9980 0.0766
-7.500 -0.4249 0.07834 0.07514 -0.0348 0.9956 0.0782
-7.250 -0.3988 0.07450 0.07127 -0.0400 0.9901 0.0812
-7.000 -0.3828 0.06204 0.05848 -0.0613 0.9771 0.0885
-6.750 -0.3534 0.06006 0.05656 -0.0621 0.9732 0.0901
-6.500 -0.3241 0.05728 0.05372 -0.0655 0.9681 0.0938
-6.250 -0.3021 0.05022 0.04629 -0.0740 0.9586 0.1026
-6.000 -0.2940 0.03552 0.03036 -0.0787 0.9470 0.0737
-5.750 -0.2656 0.02968 0.02390 -0.0811 0.9425 0.0688
-5.500 -0.2403 0.02658 0.02028 -0.0813 0.9343 0.0683
-5.250 -0.2061 0.02400 0.01720 -0.0828 0.9293 0.0680
-5.000 -0.1643 0.02227 0.01522 -0.0856 0.9265 0.0692
-4.750 -0.1312 0.02112 0.01389 -0.0864 0.9184 0.0714
-4.500 -0.0921 0.01980 0.01233 -0.0882 0.9129 0.0734
-4.250 -0.0502 0.01866 0.01094 -0.0905 0.9093 0.0751
-4.000 -0.0236 0.01744 0.00968 -0.0900 0.8989 0.0772
-3.750 0.0135 0.01659 0.00886 -0.0916 0.8937 0.0813
-3.500 0.0412 0.01601 0.00822 -0.0912 0.8833 0.0850
-3.250 0.0754 0.01510 0.00728 -0.0921 0.8769 0.0894
-3.000 0.1012 0.01461 0.00684 -0.0914 0.8656 0.0951
-2.750 0.1320 0.01401 0.00622 -0.0916 0.8574 0.1034
-2.500 0.1588 0.01362 0.00583 -0.0910 0.8464 0.1140
-2.250 0.1847 0.01313 0.00544 -0.0904 0.8358 0.1322
-2.000 0.2130 0.01257 0.00504 -0.0902 0.8270 0.1745
-1.750 0.2363 0.01213 0.00487 -0.0892 0.8152 0.2381
-1.500 0.2616 0.01172 0.00469 -0.0886 0.8049 0.3108
-1.250 0.2845 0.01112 0.00455 -0.0875 0.7951 0.4370
-1.000 0.2996 0.01035 0.00462 -0.0846 0.7843 0.6693
-0.500 0.4629 0.00982 0.00444 -0.1049 0.7660 1.0000
-0.250 0.4857 0.00989 0.00436 -0.1038 0.7550 1.0000
0.000 0.5098 0.00996 0.00427 -0.1028 0.7445 1.0000
0.250 0.5315 0.01006 0.00428 -0.1015 0.7325 1.0000
0.500 0.5548 0.01018 0.00428 -0.1004 0.7216 1.0000
0.750 0.5792 0.01030 0.00426 -0.0995 0.7112 1.0000
1.000 0.6012 0.01042 0.00433 -0.0982 0.6990 1.0000
1.250 0.6243 0.01056 0.00437 -0.0971 0.6874 1.0000
1.500 0.6478 0.01069 0.00438 -0.0960 0.6749 1.0000
1.750 0.6707 0.01082 0.00440 -0.0947 0.6614 1.0000
2.000 0.6926 0.01095 0.00448 -0.0933 0.6478 1.0000
2.250 0.7155 0.01110 0.00457 -0.0922 0.6355 1.0000
2.500 0.7393 0.01127 0.00465 -0.0911 0.6243 1.0000
2.750 0.7622 0.01142 0.00474 -0.0900 0.6121 1.0000
3.000 0.7847 0.01158 0.00488 -0.0888 0.5997 1.0000
3.250 0.8079 0.01176 0.00500 -0.0877 0.5882 1.0000
3.500 0.8316 0.01194 0.00510 -0.0867 0.5771 1.0000
3.750 0.8536 0.01210 0.00527 -0.0854 0.5646 1.0000
4.000 0.8763 0.01228 0.00542 -0.0842 0.5527 1.0000
4.250 0.8995 0.01247 0.00556 -0.0832 0.5416 1.0000
4.500 0.9218 0.01264 0.00570 -0.0819 0.5289 1.0000
4.750 0.9432 0.01281 0.00585 -0.0805 0.5145 1.0000
5.000 0.9645 0.01299 0.00601 -0.0791 0.4996 1.0000
5.250 0.9853 0.01319 0.00616 -0.0776 0.4839 1.0000
5.500 1.0061 0.01342 0.00635 -0.0762 0.4685 1.0000
5.750 1.0268 0.01368 0.00658 -0.0747 0.4533 1.0000
6.000 1.0474 0.01397 0.00683 -0.0733 0.4385 1.0000
6.250 1.0671 0.01426 0.00709 -0.0717 0.4223 1.0000
6.500 1.0866 0.01457 0.00737 -0.0701 0.4060 1.0000
6.750 1.1059 0.01489 0.00769 -0.0685 0.3905 1.0000
7.000 1.1246 0.01521 0.00800 -0.0668 0.3741 1.0000
7.250 1.1422 0.01555 0.00832 -0.0649 0.3558 1.0000
7.500 1.1590 0.01591 0.00867 -0.0629 0.3370 1.0000
7.750 1.1743 0.01632 0.00903 -0.0607 0.3166 1.0000
8.000 1.1887 0.01677 0.00943 -0.0584 0.2934 1.0000
8.250 1.2004 0.01733 0.00990 -0.0556 0.2706 1.0000
8.500 1.2098 0.01795 0.01043 -0.0526 0.2450 1.0000
8.750 1.2161 0.01871 0.01107 -0.0490 0.2172 1.0000
9.000 1.2183 0.01973 0.01188 -0.0451 0.1792 1.0000
9.250 1.2143 0.02124 0.01300 -0.0407 0.1224 1.0000
9.500 1.2112 0.02286 0.01433 -0.0367 0.0908 1.0000
9.750 1.2138 0.02421 0.01561 -0.0336 0.0805 1.0000
10.000 1.2181 0.02549 0.01692 -0.0308 0.0757 1.0000
10.250 1.2234 0.02677 0.01826 -0.0284 0.0724 1.0000
10.500 1.2260 0.02828 0.01980 -0.0259 0.0698 1.0000
10.750 1.2246 0.03015 0.02168 -0.0234 0.0676 1.0000
11.000 1.2305 0.03161 0.02324 -0.0216 0.0660 1.0000
11.250 1.2355 0.03322 0.02493 -0.0199 0.0645 1.0000
11.500 1.2399 0.03493 0.02671 -0.0184 0.0629 1.0000
11.750 1.2440 0.03676 0.02858 -0.0170 0.0615 1.0000
12.000 1.2486 0.03861 0.03046 -0.0156 0.0603 1.0000
12.250 1.2545 0.04046 0.03228 -0.0142 0.0591 1.0000
12.500 1.2647 0.04207 0.03390 -0.0129 0.0579 1.0000
12.750 1.2745 0.04362 0.03557 -0.0120 0.0568 1.0000
13.000 1.2857 0.04512 0.03715 -0.0110 0.0557 1.0000
13.250 1.2977 0.04662 0.03873 -0.0101 0.0546 1.0000
13.500 1.3098 0.04816 0.04032 -0.0092 0.0534 1.0000
13.750 1.3230 0.04968 0.04185 -0.0084 0.0520 1.0000
14.000 1.3490 0.05084 0.04295 -0.0076 0.0505 1.0000
14.250 1.3678 0.05270 0.04492 -0.0068 0.0495 1.0000
14.500 1.3722 0.05481 0.04723 -0.0060 0.0489 1.0000
14.750 1.3759 0.05711 0.04972 -0.0053 0.0482 1.0000
15.000 1.3789 0.05953 0.05233 -0.0047 0.0474 1.0000
15.250 1.3811 0.06207 0.05504 -0.0042 0.0466 1.0000
15.500 1.3839 0.06467 0.05778 -0.0039 0.0457 1.0000
15.750 1.3884 0.06728 0.06052 -0.0035 0.0450 1.0000
16.000 1.3908 0.07007 0.06343 -0.0034 0.0443 1.0000
16.250 1.3958 0.07290 0.06635 -0.0032 0.0436 1.0000
16.500 1.4101 0.07698 0.07053 -0.0030 0.0424 1.0000
16.750 1.3921 0.08118 0.07496 -0.0036 0.0423 1.0000
17.000 1.3736 0.08583 0.07985 -0.0046 0.0421 1.0000
17.250 1.3541 0.09102 0.08529 -0.0063 0.0420 1.0000
17.500 1.3323 0.09679 0.09130 -0.0086 0.0419 1.0000
17.750 1.3109 0.10303 0.09776 -0.0114 0.0418 1.0000
18.000 1.2881 0.10993 0.10488 -0.0149 0.0418 1.0000
18.250 1.2643 0.11743 0.11260 -0.0190 0.0418 1.0000
18.500 1.2400 0.12553 0.12091 -0.0236 0.0420 1.0000
18.750 1.2146 0.13435 0.12991 -0.0290 0.0422 1.0000
19.000 1.1895 0.14375 0.13947 -0.0347 0.0424 1.0000
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Polar data table (+)
Polar graphs
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