GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 200,000 Max Cl/Cd: 74.37 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe549-il-200000.txt Download as CSV file: xf-goe549-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2522 0.09732 0.09417 -0.0482 0.9938 0.0574
-9.000 -0.2324 0.09315 0.08999 -0.0533 0.9868 0.0595
-8.750 -0.2336 0.08521 0.08207 -0.0720 0.9727 0.0642
-8.500 -0.2187 0.07963 0.07651 -0.0748 0.9640 0.0654
-8.250 -0.1856 0.07751 0.07436 -0.0745 0.9596 0.0672
-8.000 -0.1602 0.07386 0.07069 -0.0793 0.9488 0.0705
-7.750 -0.1828 0.06029 0.05667 -0.1089 0.9179 0.0767
-7.500 -0.1430 0.05830 0.05494 -0.1058 0.9102 0.0785
-7.250 -0.1191 0.05679 0.05339 -0.1055 0.8946 0.0811
-7.000 -0.1133 0.05316 0.04959 -0.1084 0.8734 0.0854
-6.750 -0.1283 0.04717 0.04309 -0.1122 0.8525 0.0916
-6.500 -0.1093 0.04542 0.04138 -0.1109 0.8371 0.0938
-6.250 -0.0950 0.04365 0.03948 -0.1103 0.8217 0.0983
-6.000 -0.0918 0.04010 0.03548 -0.1106 0.8070 0.1074
-5.750 -0.0907 0.02938 0.02344 -0.1089 0.7956 0.0668
-5.500 -0.0719 0.02567 0.01918 -0.1074 0.7854 0.0587
-5.250 -0.0514 0.02316 0.01612 -0.1060 0.7752 0.0572
-5.000 -0.0278 0.02212 0.01488 -0.1053 0.7650 0.0593
-4.750 -0.0027 0.02081 0.01323 -0.1046 0.7573 0.0599
-4.500 0.0218 0.01984 0.01206 -0.1038 0.7476 0.0613
-4.250 0.0480 0.01892 0.01090 -0.1032 0.7404 0.0623
-4.000 0.0736 0.01804 0.00987 -0.1026 0.7320 0.0626
-3.750 0.1003 0.01731 0.00897 -0.1021 0.7256 0.0632
-3.500 0.1258 0.01673 0.00833 -0.1015 0.7177 0.0639
-3.250 0.1515 0.01603 0.00754 -0.1010 0.7117 0.0657
-3.000 0.1761 0.01551 0.00704 -0.1004 0.7046 0.0678
-2.750 0.2017 0.01512 0.00661 -0.0999 0.6982 0.0696
-2.500 0.2274 0.01483 0.00626 -0.0993 0.6922 0.0721
-2.250 0.2531 0.01459 0.00595 -0.0988 0.6855 0.0752
-2.000 0.2798 0.01434 0.00562 -0.0985 0.6802 0.0814
-1.750 0.3047 0.01410 0.00545 -0.0978 0.6733 0.0969
-1.500 0.3266 0.01317 0.00524 -0.0971 0.6675 0.2871
-1.250 0.3479 0.01265 0.00532 -0.0960 0.6619 0.4632
-1.000 0.3701 0.01245 0.00544 -0.0948 0.6555 0.5754
-0.750 0.3948 0.01236 0.00546 -0.0938 0.6503 0.6451
-0.500 0.4173 0.01224 0.00556 -0.0925 0.6444 0.7126
-0.250 0.4424 0.01201 0.00561 -0.0913 0.6385 0.8059
0.000 0.5323 0.01191 0.00555 -0.1035 0.6319 0.9821
0.250 0.5706 0.01203 0.00558 -0.1059 0.6252 1.0000
0.500 0.5951 0.01220 0.00559 -0.1053 0.6198 1.0000
0.750 0.6188 0.01240 0.00569 -0.1046 0.6143 1.0000
1.000 0.6421 0.01256 0.00578 -0.1038 0.6080 1.0000
1.250 0.6679 0.01275 0.00582 -0.1034 0.6029 1.0000
1.500 0.6910 0.01294 0.00598 -0.1025 0.5969 1.0000
1.750 0.7152 0.01310 0.00608 -0.1018 0.5907 1.0000
2.000 0.7420 0.01330 0.00614 -0.1015 0.5858 1.0000
2.250 0.7641 0.01347 0.00634 -0.1005 0.5790 1.0000
2.500 0.7893 0.01362 0.00641 -0.1000 0.5732 1.0000
2.750 0.8148 0.01381 0.00653 -0.0995 0.5677 1.0000
3.000 0.8378 0.01395 0.00669 -0.0986 0.5607 1.0000
3.250 0.8643 0.01409 0.00674 -0.0983 0.5553 1.0000
3.500 0.8874 0.01426 0.00694 -0.0974 0.5486 1.0000
3.750 0.9123 0.01438 0.00702 -0.0968 0.5420 1.0000
4.000 0.9378 0.01453 0.00713 -0.0964 0.5362 1.0000
4.250 0.9608 0.01468 0.00731 -0.0955 0.5289 1.0000
4.500 0.9876 0.01479 0.00734 -0.0952 0.5233 1.0000
4.750 1.0094 0.01496 0.00758 -0.0942 0.5153 1.0000
5.000 1.0351 0.01507 0.00762 -0.0937 0.5090 1.0000
5.250 1.0578 0.01526 0.00788 -0.0928 0.5016 1.0000
5.500 1.0826 0.01539 0.00797 -0.0923 0.4947 1.0000
5.750 1.1057 0.01559 0.00820 -0.0915 0.4873 1.0000
6.000 1.1297 0.01575 0.00834 -0.0908 0.4801 1.0000
6.250 1.1532 0.01598 0.00860 -0.0901 0.4731 1.0000
6.500 1.1763 0.01618 0.00882 -0.0893 0.4656 1.0000
6.750 1.1990 0.01640 0.00904 -0.0884 0.4577 1.0000
7.000 1.2211 0.01656 0.00919 -0.0874 0.4490 1.0000
7.250 1.2418 0.01679 0.00947 -0.0862 0.4399 1.0000
7.500 1.2651 0.01701 0.00961 -0.0855 0.4320 1.0000
7.750 1.2837 0.01728 0.00998 -0.0840 0.4230 1.0000
8.000 1.3067 0.01757 0.01022 -0.0833 0.4157 1.0000
8.250 1.3244 0.01786 0.01062 -0.0816 0.4068 1.0000
8.500 1.3463 0.01820 0.01093 -0.0808 0.3998 1.0000
8.750 1.3636 0.01853 0.01136 -0.0791 0.3916 1.0000
9.000 1.3835 0.01889 0.01171 -0.0779 0.3840 1.0000
9.250 1.3990 0.01924 0.01214 -0.0760 0.3756 1.0000
9.500 1.4150 0.01961 0.01253 -0.0742 0.3670 1.0000
9.750 1.4295 0.01999 0.01296 -0.0722 0.3588 1.0000
10.000 1.4432 0.02042 0.01344 -0.0700 0.3514 1.0000
10.250 1.4554 0.02086 0.01396 -0.0676 0.3445 1.0000
10.500 1.4687 0.02135 0.01449 -0.0655 0.3380 1.0000
10.750 1.4775 0.02187 0.01511 -0.0628 0.3305 1.0000
11.000 1.4882 0.02244 0.01570 -0.0604 0.3232 1.0000
11.250 1.4943 0.02309 0.01646 -0.0576 0.3147 1.0000
11.500 1.5005 0.02383 0.01727 -0.0550 0.3060 1.0000
11.750 1.5050 0.02470 0.01817 -0.0524 0.2966 1.0000
12.000 1.5090 0.02568 0.01928 -0.0499 0.2869 1.0000
12.250 1.5124 0.02681 0.02046 -0.0476 0.2776 1.0000
12.500 1.5138 0.02814 0.02185 -0.0454 0.2669 1.0000
12.750 1.5147 0.02964 0.02345 -0.0433 0.2553 1.0000
13.000 1.5128 0.03145 0.02533 -0.0414 0.2419 1.0000
13.250 1.5084 0.03362 0.02754 -0.0396 0.2268 1.0000
13.500 1.5009 0.03622 0.03015 -0.0380 0.2099 1.0000
13.750 1.4892 0.03942 0.03332 -0.0366 0.1886 1.0000
14.000 1.4714 0.04345 0.03726 -0.0355 0.1646 1.0000
14.500 1.4268 0.05326 0.04683 -0.0344 0.1172 1.0000
14.750 1.4052 0.05847 0.05197 -0.0344 0.1027 1.0000
15.000 1.3852 0.06371 0.05718 -0.0346 0.0922 1.0000
15.250 1.3677 0.06889 0.06238 -0.0350 0.0833 1.0000
15.500 1.3489 0.07444 0.06795 -0.0357 0.0755 1.0000
15.750 1.3337 0.07969 0.07325 -0.0366 0.0673 1.0000
16.000 1.3222 0.08461 0.07823 -0.0374 0.0609 1.0000
16.250 1.3096 0.08980 0.08341 -0.0386 0.0559 1.0000
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