GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 500,000 Max Cl/Cd: 81.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe647-il-500000.txt Download as CSV file: xf-goe647-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5536 0.03885 0.03560 -0.1107 0.9752 0.0347
-11.250 -0.5441 0.03450 0.03089 -0.1153 0.9683 0.0350
-11.000 -0.5331 0.03145 0.02753 -0.1169 0.9584 0.0354
-10.750 -0.5087 0.02863 0.02438 -0.1198 0.9539 0.0359
-10.500 -0.4900 0.02666 0.02214 -0.1201 0.9435 0.0362
-10.250 -0.4623 0.02498 0.02017 -0.1217 0.9368 0.0368
-10.000 -0.4405 0.02404 0.01896 -0.1214 0.9253 0.0372
-9.750 -0.4195 0.02207 0.01682 -0.1213 0.9148 0.0378
-9.500 -0.3937 0.02089 0.01555 -0.1215 0.9050 0.0382
-9.250 -0.3718 0.02014 0.01473 -0.1206 0.8931 0.0387
-9.000 -0.3481 0.01941 0.01388 -0.1200 0.8825 0.0392
-8.750 -0.3254 0.01872 0.01309 -0.1191 0.8711 0.0397
-8.500 -0.3032 0.01808 0.01234 -0.1181 0.8597 0.0402
-8.250 -0.2794 0.01752 0.01164 -0.1173 0.8491 0.0409
-8.000 -0.2572 0.01701 0.01101 -0.1161 0.8367 0.0415
-7.750 -0.2342 0.01656 0.01041 -0.1150 0.8236 0.0421
-7.500 -0.2113 0.01606 0.00977 -0.1139 0.8096 0.0425
-7.250 -0.1901 0.01520 0.00884 -0.1126 0.7956 0.0432
-7.000 -0.1677 0.01469 0.00830 -0.1115 0.7824 0.0439
-6.750 -0.1442 0.01430 0.00785 -0.1105 0.7707 0.0446
-6.500 -0.1205 0.01396 0.00742 -0.1095 0.7586 0.0455
-6.250 -0.0969 0.01362 0.00702 -0.1085 0.7458 0.0464
-6.000 -0.0726 0.01334 0.00665 -0.1075 0.7338 0.0474
-5.750 -0.0486 0.01308 0.00627 -0.1066 0.7216 0.0482
-5.500 -0.0263 0.01259 0.00576 -0.1054 0.7088 0.0496
-5.250 -0.0023 0.01232 0.00544 -0.1044 0.6968 0.0509
-5.000 0.0220 0.01211 0.00515 -0.1035 0.6854 0.0524
-4.750 0.0469 0.01191 0.00488 -0.1027 0.6740 0.0540
-4.500 0.0706 0.01162 0.00453 -0.1017 0.6632 0.0562
-4.250 0.0953 0.01144 0.00430 -0.1009 0.6521 0.0592
-4.000 0.1201 0.01123 0.00406 -0.1001 0.6416 0.0634
-3.750 0.1450 0.01110 0.00386 -0.0992 0.6316 0.0694
-3.500 0.1698 0.01084 0.00366 -0.0984 0.6218 0.0819
-3.250 0.1942 0.01065 0.00348 -0.0976 0.6120 0.1021
-3.000 0.2187 0.01040 0.00330 -0.0968 0.6018 0.1258
-2.750 0.2424 0.01014 0.00322 -0.0960 0.5923 0.1801
-2.500 0.2677 0.01005 0.00319 -0.0953 0.5823 0.2133
-2.250 0.2933 0.01002 0.00316 -0.0946 0.5726 0.2334
-2.000 0.3186 0.01001 0.00313 -0.0939 0.5617 0.2487
-1.750 0.3443 0.01000 0.00310 -0.0933 0.5511 0.2622
-1.500 0.3693 0.01003 0.00308 -0.0925 0.5401 0.2760
-1.250 0.3946 0.01000 0.00306 -0.0918 0.5287 0.2902
-1.000 0.4194 0.01000 0.00306 -0.0910 0.5173 0.3065
-0.750 0.4434 0.01002 0.00307 -0.0901 0.5049 0.3281
-0.250 0.4916 0.01003 0.00312 -0.0883 0.4778 0.3760
0.000 0.5151 0.01006 0.00316 -0.0873 0.4643 0.4017
0.250 0.5382 0.01013 0.00322 -0.0863 0.4508 0.4299
0.500 0.5611 0.01020 0.00329 -0.0852 0.4371 0.4568
0.750 0.5845 0.01027 0.00335 -0.0842 0.4242 0.4847
1.000 0.6067 0.01032 0.00343 -0.0830 0.4120 0.5148
1.250 0.6274 0.01036 0.00352 -0.0815 0.4005 0.5537
1.500 0.6468 0.01023 0.00364 -0.0797 0.3902 0.6366
1.750 0.7513 0.00998 0.00406 -0.0959 0.3733 0.9805
2.000 0.7896 0.01028 0.00424 -0.0981 0.3645 1.0000
2.250 0.8110 0.01045 0.00434 -0.0968 0.3579 1.0000
2.500 0.8310 0.01067 0.00448 -0.0952 0.3515 1.0000
2.750 0.8523 0.01085 0.00460 -0.0938 0.3463 1.0000
3.000 0.8738 0.01102 0.00473 -0.0925 0.3411 1.0000
3.250 0.8941 0.01125 0.00488 -0.0910 0.3360 1.0000
3.500 0.9141 0.01149 0.00506 -0.0895 0.3313 1.0000
3.750 0.9363 0.01164 0.00520 -0.0883 0.3271 1.0000
4.000 0.9571 0.01184 0.00536 -0.0869 0.3227 1.0000
4.250 0.9767 0.01209 0.00554 -0.0853 0.3187 1.0000
4.500 0.9961 0.01237 0.00577 -0.0837 0.3148 1.0000
4.750 1.0178 0.01253 0.00594 -0.0825 0.3118 1.0000
5.000 1.0385 0.01272 0.00613 -0.0811 0.3086 1.0000
5.250 1.0571 0.01294 0.00632 -0.0794 0.3053 1.0000
5.500 1.0745 0.01321 0.00655 -0.0774 0.3022 1.0000
5.750 1.0917 0.01357 0.00685 -0.0755 0.2986 1.0000
6.000 1.1117 0.01374 0.00705 -0.0740 0.2965 1.0000
6.250 1.1314 0.01395 0.00727 -0.0726 0.2939 1.0000
6.500 1.1509 0.01418 0.00751 -0.0711 0.2912 1.0000
6.750 1.1698 0.01445 0.00776 -0.0696 0.2883 1.0000
7.000 1.1881 0.01478 0.00806 -0.0681 0.2855 1.0000
7.250 1.2070 0.01523 0.00846 -0.0667 0.2822 1.0000
7.500 1.2270 0.01546 0.00873 -0.0654 0.2806 1.0000
7.750 1.2470 0.01572 0.00903 -0.0642 0.2785 1.0000
8.000 1.2666 0.01602 0.00935 -0.0630 0.2763 1.0000
8.250 1.2860 0.01633 0.00968 -0.0618 0.2741 1.0000
8.500 1.3050 0.01668 0.01003 -0.0606 0.2720 1.0000
8.750 1.3236 0.01708 0.01042 -0.0594 0.2699 1.0000
9.000 1.3427 0.01757 0.01088 -0.0583 0.2673 1.0000
9.250 1.3624 0.01799 0.01133 -0.0573 0.2654 1.0000
9.500 1.3809 0.01834 0.01174 -0.0562 0.2638 1.0000
9.750 1.3996 0.01873 0.01218 -0.0551 0.2620 1.0000
10.000 1.4179 0.01914 0.01263 -0.0540 0.2600 1.0000
10.250 1.4362 0.01958 0.01310 -0.0529 0.2582 1.0000
10.500 1.4542 0.02005 0.01360 -0.0519 0.2565 1.0000
10.750 1.4720 0.02055 0.01411 -0.0509 0.2548 1.0000
11.000 1.4903 0.02110 0.01466 -0.0500 0.2529 1.0000
11.250 1.5110 0.02169 0.01522 -0.0493 0.2504 1.0000
11.500 1.5259 0.02222 0.01586 -0.0481 0.2490 1.0000
11.750 1.5408 0.02279 0.01651 -0.0469 0.2471 1.0000
12.000 1.5557 0.02340 0.01718 -0.0458 0.2449 1.0000
12.250 1.5705 0.02404 0.01786 -0.0448 0.2427 1.0000
12.500 1.5848 0.02473 0.01859 -0.0437 0.2405 1.0000
12.750 1.5988 0.02548 0.01935 -0.0427 0.2381 1.0000
13.000 1.6145 0.02624 0.02010 -0.0418 0.2351 1.0000
13.250 1.6254 0.02713 0.02111 -0.0407 0.2332 1.0000
13.500 1.6368 0.02806 0.02213 -0.0397 0.2306 1.0000
13.750 1.6485 0.02901 0.02315 -0.0388 0.2281 1.0000
14.000 1.6594 0.03004 0.02422 -0.0380 0.2256 1.0000
14.250 1.6706 0.03110 0.02530 -0.0371 0.2234 1.0000
14.500 1.6819 0.03218 0.02637 -0.0362 0.2204 1.0000
14.750 1.6912 0.03344 0.02776 -0.0355 0.2186 1.0000
15.000 1.7003 0.03475 0.02919 -0.0348 0.2161 1.0000
15.250 1.7087 0.03616 0.03068 -0.0342 0.2134 1.0000
15.500 1.7155 0.03775 0.03230 -0.0337 0.2104 1.0000
15.750 1.7218 0.03938 0.03394 -0.0330 0.2076 1.0000
16.000 1.7287 0.04103 0.03569 -0.0325 0.2050 1.0000
16.250 1.7350 0.04285 0.03763 -0.0323 0.2022 1.0000
16.500 1.7403 0.04478 0.03965 -0.0320 0.1990 1.0000
16.750 1.7430 0.04697 0.04188 -0.0317 0.1958 1.0000
17.000 1.7431 0.04942 0.04435 -0.0314 0.1923 1.0000
17.250 1.7465 0.05174 0.04682 -0.0315 0.1882 1.0000
17.500 1.7474 0.05427 0.04943 -0.0315 0.1845 1.0000
17.750 1.7429 0.05743 0.05262 -0.0315 0.1805 1.0000
18.000 1.7418 0.06028 0.05557 -0.0316 0.1768 1.0000
18.250 1.7377 0.06353 0.05892 -0.0319 0.1718 1.0000
18.500 1.7254 0.06775 0.06316 -0.0323 0.1668 1.0000
18.750 1.7184 0.07145 0.06697 -0.0328 0.1609 1.0000
19.000 1.7010 0.07649 0.07205 -0.0335 0.1547 1.0000
19.250 1.6861 0.08128 0.07691 -0.0343 0.1480 1.0000
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