GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 200,000 Max Cl/Cd: 67.83 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe654-il-200000-n5.txt Download as CSV file: xf-goe654-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2392 0.12746 0.12379 -0.0385 1.0000 0.0382
-11.750 -0.2500 0.12366 0.12003 -0.0418 1.0000 0.0389
-11.500 -0.2519 0.12006 0.11646 -0.0435 1.0000 0.0390
-11.250 -0.2507 0.11656 0.11302 -0.0441 1.0000 0.0391
-11.000 -0.2393 0.11425 0.11074 -0.0425 1.0000 0.0395
-10.750 -0.2295 0.11227 0.10879 -0.0414 1.0000 0.0402
-10.500 -0.2222 0.10990 0.10646 -0.0416 0.9994 0.0412
-10.250 -0.2081 0.10609 0.10266 -0.0450 0.9871 0.0435
-10.000 -0.2136 0.09957 0.09616 -0.0546 0.9694 0.0456
-9.750 -0.2038 0.09400 0.09057 -0.0612 0.9517 0.0458
-9.500 -0.1801 0.08956 0.08610 -0.0650 0.9373 0.0461
-9.250 -0.1485 0.08611 0.08260 -0.0692 0.9214 0.0468
-9.000 -0.1166 0.08222 0.07862 -0.0754 0.9032 0.0480
-8.750 -0.0895 0.07793 0.07423 -0.0826 0.8815 0.0503
-8.500 -0.0977 0.06762 0.06379 -0.0922 0.8571 0.0376
-8.000 -0.1938 0.04107 0.03630 -0.1098 0.8087 0.0334
-7.500 -0.1687 0.03757 0.03250 -0.1088 0.7783 0.0340
-7.250 -0.1544 0.03603 0.03078 -0.1082 0.7640 0.0346
-7.000 -0.1449 0.03321 0.02759 -0.1073 0.7509 0.0348
-6.750 -0.1334 0.03043 0.02437 -0.1062 0.7381 0.0347
-6.500 -0.1181 0.02823 0.02177 -0.1051 0.7252 0.0348
-6.250 -0.1003 0.02645 0.01964 -0.1040 0.7121 0.0349
-6.000 -0.0805 0.02498 0.01784 -0.1030 0.6998 0.0351
-5.750 -0.0594 0.02371 0.01626 -0.1021 0.6885 0.0353
-5.500 -0.0372 0.02260 0.01488 -0.1012 0.6767 0.0356
-5.250 -0.0142 0.02168 0.01372 -0.1004 0.6653 0.0361
-5.000 0.0094 0.02090 0.01269 -0.0996 0.6536 0.0368
-4.750 0.0332 0.02014 0.01169 -0.0987 0.6414 0.0374
-4.500 0.0575 0.01942 0.01076 -0.0980 0.6294 0.0377
-4.250 0.0820 0.01878 0.00993 -0.0972 0.6178 0.0379
-3.750 0.1317 0.01772 0.00855 -0.0958 0.5964 0.0386
-3.500 0.1569 0.01729 0.00798 -0.0951 0.5882 0.0389
-3.250 0.1820 0.01678 0.00743 -0.0945 0.5809 0.0393
-3.000 0.2067 0.01634 0.00693 -0.0938 0.5742 0.0398
-2.750 0.2319 0.01597 0.00655 -0.0933 0.5677 0.0405
-2.500 0.2571 0.01569 0.00624 -0.0927 0.5616 0.0417
-2.250 0.2825 0.01548 0.00595 -0.0921 0.5561 0.0430
-2.000 0.3081 0.01525 0.00569 -0.0916 0.5500 0.0442
-1.750 0.3337 0.01507 0.00544 -0.0911 0.5440 0.0450
-1.500 0.3593 0.01493 0.00521 -0.0905 0.5386 0.0460
-1.250 0.3852 0.01473 0.00501 -0.0901 0.5330 0.0475
-1.000 0.4112 0.01462 0.00485 -0.0896 0.5276 0.0496
-0.750 0.4372 0.01457 0.00471 -0.0891 0.5226 0.0522
-0.500 0.4631 0.01445 0.00462 -0.0887 0.5168 0.0584
-0.250 0.4884 0.01425 0.00455 -0.0881 0.5108 0.0899
0.000 0.5119 0.01384 0.00451 -0.0875 0.5054 0.2180
0.250 0.5336 0.01326 0.00461 -0.0866 0.4998 0.4173
0.500 0.5556 0.01294 0.00469 -0.0854 0.4939 0.5416
0.750 0.5757 0.01259 0.00476 -0.0837 0.4887 0.6775
1.250 0.6871 0.01235 0.00491 -0.0946 0.4724 1.0000
1.500 0.7104 0.01247 0.00495 -0.0936 0.4654 1.0000
1.750 0.7335 0.01259 0.00500 -0.0926 0.4581 1.0000
2.000 0.7566 0.01273 0.00505 -0.0917 0.4512 1.0000
2.250 0.7800 0.01287 0.00512 -0.0907 0.4434 1.0000
2.500 0.8029 0.01302 0.00519 -0.0898 0.4362 1.0000
2.750 0.8262 0.01317 0.00529 -0.0889 0.4274 1.0000
3.000 0.8489 0.01334 0.00538 -0.0879 0.4191 1.0000
3.250 0.8716 0.01352 0.00549 -0.0869 0.4098 1.0000
3.500 0.8943 0.01371 0.00561 -0.0859 0.4014 1.0000
3.750 0.9166 0.01392 0.00576 -0.0849 0.3934 1.0000
4.000 0.9391 0.01414 0.00592 -0.0839 0.3861 1.0000
4.250 0.9611 0.01439 0.00610 -0.0829 0.3787 1.0000
4.500 0.9831 0.01465 0.00630 -0.0818 0.3719 1.0000
4.750 1.0051 0.01491 0.00651 -0.0808 0.3654 1.0000
5.000 1.0263 0.01522 0.00674 -0.0797 0.3599 1.0000
5.250 1.0488 0.01548 0.00700 -0.0788 0.3546 1.0000
5.500 1.0704 0.01578 0.00727 -0.0778 0.3494 1.0000
5.750 1.0912 0.01612 0.00754 -0.0766 0.3447 1.0000
6.000 1.1131 0.01642 0.00785 -0.0757 0.3402 1.0000
6.250 1.1344 0.01673 0.00817 -0.0747 0.3356 1.0000
6.500 1.1551 0.01707 0.00848 -0.0736 0.3314 1.0000
6.750 1.1751 0.01747 0.00882 -0.0724 0.3274 1.0000
7.000 1.1962 0.01777 0.00918 -0.0714 0.3233 1.0000
7.250 1.2162 0.01811 0.00955 -0.0702 0.3190 1.0000
7.500 1.2350 0.01850 0.00991 -0.0689 0.3148 1.0000
7.750 1.2530 0.01892 0.01030 -0.0674 0.3110 1.0000
8.000 1.2705 0.01924 0.01071 -0.0658 0.3065 1.0000
8.250 1.2873 0.01962 0.01112 -0.0641 0.3022 1.0000
8.500 1.3033 0.02005 0.01155 -0.0624 0.2982 1.0000
8.750 1.3198 0.02052 0.01202 -0.0609 0.2946 1.0000
9.000 1.3366 0.02092 0.01252 -0.0594 0.2910 1.0000
9.250 1.3520 0.02137 0.01304 -0.0577 0.2866 1.0000
9.500 1.3655 0.02189 0.01356 -0.0558 0.2820 1.0000
9.750 1.3793 0.02245 0.01415 -0.0541 0.2778 1.0000
10.000 1.3924 0.02298 0.01480 -0.0524 0.2722 1.0000
10.250 1.4031 0.02364 0.01548 -0.0504 0.2666 1.0000
10.500 1.4141 0.02435 0.01623 -0.0486 0.2613 1.0000
10.750 1.4254 0.02507 0.01706 -0.0470 0.2553 1.0000
11.000 1.4343 0.02596 0.01796 -0.0453 0.2500 1.0000
11.250 1.4449 0.02683 0.01892 -0.0438 0.2449 1.0000
11.500 1.4537 0.02784 0.02001 -0.0423 0.2385 1.0000
11.750 1.4596 0.02906 0.02125 -0.0408 0.2326 1.0000
12.000 1.4672 0.03028 0.02257 -0.0395 0.2247 1.0000
12.250 1.4704 0.03184 0.02416 -0.0381 0.2170 1.0000
12.500 1.4742 0.03348 0.02585 -0.0369 0.2083 1.0000
12.750 1.4766 0.03531 0.02773 -0.0358 0.2003 1.0000
13.000 1.4768 0.03742 0.02987 -0.0348 0.1925 1.0000
13.250 1.4763 0.03967 0.03218 -0.0340 0.1836 1.0000
13.500 1.4728 0.04232 0.03485 -0.0333 0.1759 1.0000
13.750 1.4684 0.04518 0.03775 -0.0328 0.1670 1.0000
14.000 1.4613 0.04844 0.04103 -0.0324 0.1575 1.0000
14.250 1.4518 0.05212 0.04472 -0.0323 0.1488 1.0000
14.500 1.4430 0.05586 0.04850 -0.0324 0.1403 1.0000
14.750 1.4346 0.05968 0.05238 -0.0326 0.1326 1.0000
15.000 1.4245 0.06384 0.05658 -0.0330 0.1260 1.0000
15.250 1.4157 0.06791 0.06072 -0.0335 0.1187 1.0000
15.500 1.4038 0.07252 0.06537 -0.0343 0.1122 1.0000
15.750 1.3898 0.07753 0.07043 -0.0353 0.1031 1.0000
16.000 1.3753 0.08274 0.07570 -0.0364 0.0933 1.0000
16.250 1.3514 0.08948 0.08242 -0.0382 0.0762 1.0000
16.500 1.3245 0.09690 0.08981 -0.0404 0.0604 1.0000
16.750 1.3024 0.10379 0.09670 -0.0426 0.0487 1.0000
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