GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 50,000 Max Cl/Cd: 32.2 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe629-il-50000-n5.txt Download as CSV file: xf-goe629-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 629 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4314 0.10282 0.09448 -0.0456 1.0000 0.1246
-10.500 -0.4424 0.09847 0.09018 -0.0469 1.0000 0.1259
-10.250 -0.4575 0.09363 0.08540 -0.0483 1.0000 0.1268
-10.000 -0.4780 0.08823 0.08009 -0.0501 1.0000 0.1274
-9.750 -0.5146 0.08109 0.07307 -0.0530 1.0000 0.1282
-9.500 -0.5745 0.07321 0.06530 -0.0548 1.0000 0.1283
-9.250 -0.6268 0.06739 0.05947 -0.0528 1.0000 0.1286
-9.000 -0.6590 0.06291 0.05489 -0.0503 1.0000 0.1294
-8.750 -0.6473 0.06234 0.05439 -0.0480 1.0000 0.1312
-8.500 -0.6526 0.06016 0.05216 -0.0456 1.0000 0.1327
-8.250 -0.6626 0.05724 0.04909 -0.0433 1.0000 0.1342
-8.000 -0.6711 0.05416 0.04582 -0.0410 1.0000 0.1359
-7.750 -0.6768 0.05114 0.04253 -0.0389 1.0000 0.1382
-7.500 -0.6817 0.04785 0.03884 -0.0368 1.0000 0.1411
-7.250 -0.6835 0.04459 0.03506 -0.0348 1.0000 0.1439
-7.000 -0.6706 0.04346 0.03391 -0.0331 1.0000 0.1460
-6.750 -0.6587 0.04215 0.03250 -0.0315 1.0000 0.1482
-6.500 -0.6465 0.04086 0.03105 -0.0299 1.0000 0.1514
-6.250 -0.6347 0.03930 0.02918 -0.0284 1.0000 0.1552
-6.000 -0.6051 0.03729 0.02662 -0.0304 0.9935 0.1601
-5.750 -0.5727 0.03632 0.02563 -0.0321 0.9867 0.1636
-5.500 -0.5400 0.03538 0.02450 -0.0339 0.9798 0.1689
-5.250 -0.5080 0.03416 0.02284 -0.0356 0.9725 0.1756
-5.000 -0.4766 0.03336 0.02204 -0.0369 0.9652 0.1803
-4.750 -0.4426 0.03262 0.02116 -0.0385 0.9582 0.1864
-4.500 -0.4128 0.03181 0.02008 -0.0394 0.9503 0.1939
-4.250 -0.3789 0.03131 0.01963 -0.0410 0.9434 0.2011
-4.000 -0.3492 0.03068 0.01874 -0.0417 0.9354 0.2096
-3.750 -0.3156 0.03020 0.01835 -0.0431 0.9281 0.2174
-3.500 -0.2854 0.02977 0.01777 -0.0438 0.9201 0.2278
-3.250 -0.2530 0.02939 0.01743 -0.0449 0.9124 0.2382
-3.000 -0.2214 0.02904 0.01706 -0.0458 0.9046 0.2494
-2.750 -0.1893 0.02872 0.01669 -0.0468 0.8963 0.2627
-2.500 -0.1560 0.02845 0.01641 -0.0479 0.8888 0.2784
-2.250 -0.1251 0.02817 0.01616 -0.0487 0.8801 0.2942
-2.000 -0.0910 0.02787 0.01591 -0.0499 0.8728 0.3132
-1.500 -0.0286 0.02724 0.01552 -0.0513 0.8566 0.3569
-1.250 -0.0024 0.02698 0.01540 -0.0511 0.8467 0.3861
-1.000 0.0304 0.02656 0.01523 -0.0519 0.8398 0.4265
-0.750 0.0541 0.02626 0.01522 -0.0511 0.8298 0.4778
-0.500 0.0850 0.02570 0.01513 -0.0512 0.8232 0.5621
-0.250 0.1091 0.02531 0.01535 -0.0497 0.8134 0.6810
0.000 0.2109 0.02507 0.01559 -0.0621 0.8119 0.9193
0.250 0.2987 0.02502 0.01539 -0.0733 0.8091 1.0000
0.500 0.3150 0.02518 0.01541 -0.0715 0.7963 1.0000
0.750 0.3407 0.02517 0.01527 -0.0710 0.7855 1.0000
1.000 0.3738 0.02497 0.01495 -0.0715 0.7758 1.0000
1.250 0.3937 0.02504 0.01492 -0.0699 0.7623 1.0000
1.500 0.4192 0.02500 0.01479 -0.0691 0.7505 1.0000
1.750 0.4528 0.02480 0.01451 -0.0696 0.7412 1.0000
2.000 0.4705 0.02501 0.01465 -0.0676 0.7282 1.0000
2.250 0.4955 0.02507 0.01467 -0.0668 0.7174 1.0000
2.500 0.5253 0.02501 0.01456 -0.0666 0.7078 1.0000
2.750 0.5435 0.02528 0.01480 -0.0648 0.6953 1.0000
3.000 0.5711 0.02531 0.01479 -0.0643 0.6851 1.0000
3.250 0.5974 0.02537 0.01484 -0.0636 0.6744 1.0000
3.500 0.6167 0.02565 0.01511 -0.0619 0.6620 1.0000
3.750 0.6444 0.02570 0.01515 -0.0614 0.6513 1.0000
4.000 0.6712 0.02578 0.01523 -0.0608 0.6401 1.0000
4.500 0.7149 0.02629 0.01576 -0.0581 0.6153 1.0000
4.750 0.7473 0.02624 0.01571 -0.0582 0.6046 1.0000
5.000 0.7651 0.02664 0.01615 -0.0563 0.5907 1.0000
5.250 0.7858 0.02697 0.01652 -0.0548 0.5772 1.0000
5.500 0.8096 0.02720 0.01676 -0.0536 0.5638 1.0000
5.750 0.8344 0.02734 0.01692 -0.0526 0.5492 1.0000
6.000 0.8579 0.02750 0.01706 -0.0513 0.5336 1.0000
6.250 0.8798 0.02770 0.01726 -0.0497 0.5174 1.0000
6.500 0.8994 0.02800 0.01758 -0.0480 0.5013 1.0000
6.750 0.9152 0.02844 0.01806 -0.0457 0.4851 1.0000
7.000 0.9303 0.02889 0.01856 -0.0434 0.4690 1.0000
7.250 0.9449 0.02935 0.01905 -0.0411 0.4527 1.0000
7.500 0.9588 0.02979 0.01954 -0.0386 0.4360 1.0000
7.750 0.9719 0.03025 0.02001 -0.0360 0.4192 1.0000
8.000 0.9842 0.03071 0.02048 -0.0334 0.4022 1.0000
8.250 0.9953 0.03122 0.02098 -0.0306 0.3855 1.0000
8.500 1.0061 0.03179 0.02155 -0.0278 0.3690 1.0000
8.750 1.0167 0.03244 0.02218 -0.0252 0.3525 1.0000
9.000 1.0269 0.03320 0.02292 -0.0226 0.3361 1.0000
9.250 1.0362 0.03406 0.02378 -0.0200 0.3197 1.0000
9.500 1.0447 0.03504 0.02476 -0.0176 0.3035 1.0000
9.750 1.0520 0.03613 0.02589 -0.0151 0.2874 1.0000
10.000 1.0572 0.03733 0.02710 -0.0126 0.2712 1.0000
10.250 1.0604 0.03864 0.02842 -0.0100 0.2551 1.0000
10.500 1.0613 0.04009 0.02987 -0.0076 0.2392 1.0000
10.750 1.0606 0.04169 0.03145 -0.0053 0.2235 1.0000
11.000 1.0588 0.04348 0.03321 -0.0032 0.2082 1.0000
11.250 1.0573 0.04541 0.03514 -0.0014 0.1940 1.0000
11.500 1.0564 0.04749 0.03720 0.0001 0.1810 1.0000
11.750 1.0571 0.04960 0.03930 0.0013 0.1700 1.0000
12.000 1.0584 0.05173 0.04133 0.0025 0.1604 1.0000
12.250 1.0590 0.05416 0.04388 0.0034 0.1504 1.0000
12.500 1.0598 0.05662 0.04636 0.0042 0.1416 1.0000
12.750 1.0607 0.05910 0.04885 0.0048 0.1335 1.0000
13.000 1.0611 0.06188 0.05175 0.0053 0.1259 1.0000
13.250 1.0634 0.06436 0.05421 0.0059 0.1193 1.0000
13.500 1.0633 0.06741 0.05742 0.0061 0.1131 1.0000
13.750 1.0646 0.07021 0.06027 0.0063 0.1077 1.0000
14.000 1.0663 0.07308 0.06318 0.0064 0.1030 1.0000
14.250 1.0625 0.07686 0.06718 0.0060 0.0987 1.0000
14.500 1.0637 0.07985 0.07022 0.0059 0.0951 1.0000
14.750 1.0690 0.08247 0.07285 0.0060 0.0921 1.0000
15.000 1.0576 0.08778 0.07848 0.0046 0.0900 1.0000
15.250 1.0435 0.09362 0.08459 0.0026 0.0880 1.0000
15.500 1.0270 0.10009 0.09128 0.0001 0.0863 1.0000
15.750 1.0072 0.10747 0.09885 -0.0032 0.0850 1.0000
16.000 0.9776 0.11729 0.10887 -0.0083 0.0841 1.0000
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