GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 200,000 Max Cl/Cd: 69.96 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe629-il-200000.txt Download as CSV file: xf-goe629-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7765 0.06350 0.05918 -0.0814 1.0000 0.0692
-13.500 -0.8401 0.05265 0.04812 -0.0889 1.0000 0.0686
-13.250 -0.8835 0.04730 0.04257 -0.0895 1.0000 0.0684
-13.000 -0.9221 0.04435 0.03942 -0.0857 1.0000 0.0687
-12.750 -0.9568 0.04250 0.03741 -0.0790 1.0000 0.0689
-12.500 -0.9723 0.04072 0.03553 -0.0744 1.0000 0.0700
-12.250 -0.9386 0.04199 0.03711 -0.0739 1.0000 0.0724
-12.000 -0.9372 0.04158 0.03670 -0.0705 1.0000 0.0741
-11.750 -0.9492 0.04013 0.03508 -0.0660 1.0000 0.0758
-11.500 -0.9646 0.03829 0.03294 -0.0612 1.0000 0.0773
-11.250 -0.9764 0.03637 0.03067 -0.0566 1.0000 0.0789
-11.000 -0.9602 0.03594 0.03043 -0.0550 1.0000 0.0808
-10.750 -0.9468 0.03597 0.03051 -0.0529 1.0000 0.0829
-10.500 -0.9383 0.03543 0.02990 -0.0503 1.0000 0.0852
-10.250 -0.9376 0.03403 0.02818 -0.0470 1.0000 0.0876
-10.000 -0.9346 0.03237 0.02624 -0.0441 1.0000 0.0897
-9.750 -0.9172 0.03223 0.02626 -0.0426 1.0000 0.0918
-9.500 -0.9021 0.03214 0.02619 -0.0408 1.0000 0.0941
-9.250 -0.8898 0.03156 0.02548 -0.0387 1.0000 0.0967
-9.000 -0.8705 0.03047 0.02395 -0.0383 0.9978 0.0998
-8.750 -0.8385 0.02929 0.02282 -0.0401 0.9944 0.1027
-8.500 -0.8058 0.02895 0.02245 -0.0416 0.9904 0.1055
-8.250 -0.7738 0.02814 0.02145 -0.0431 0.9857 0.1086
-8.000 -0.7375 0.02723 0.02014 -0.0454 0.9815 0.1118
-7.750 -0.7077 0.02586 0.01874 -0.0465 0.9751 0.1144
-7.500 -0.6683 0.02541 0.01827 -0.0491 0.9707 0.1174
-7.250 -0.6358 0.02484 0.01758 -0.0503 0.9656 0.1207
-7.000 -0.6058 0.02414 0.01666 -0.0510 0.9601 0.1236
-6.750 -0.5703 0.02322 0.01558 -0.0528 0.9566 0.1268
-6.500 -0.5328 0.02271 0.01512 -0.0549 0.9536 0.1301
-6.250 -0.5089 0.02228 0.01463 -0.0543 0.9462 0.1332
-6.000 -0.4727 0.02178 0.01398 -0.0560 0.9422 0.1371
-5.750 -0.4336 0.02105 0.01315 -0.0583 0.9398 0.1413
-5.500 -0.4102 0.02063 0.01276 -0.0575 0.9324 0.1447
-5.250 -0.3755 0.02019 0.01229 -0.0589 0.9278 0.1494
-5.000 -0.3354 0.01974 0.01168 -0.0612 0.9248 0.1549
-4.750 -0.2937 0.01905 0.01110 -0.0640 0.9228 0.1614
-4.500 -0.2747 0.01878 0.01079 -0.0622 0.9133 0.1667
-4.250 -0.2364 0.01816 0.01018 -0.0642 0.9100 0.1742
-4.000 -0.1940 0.01773 0.00975 -0.0669 0.9077 0.1839
-3.750 -0.1662 0.01727 0.00934 -0.0668 0.9009 0.1920
-3.500 -0.1308 0.01691 0.00897 -0.0681 0.8957 0.2016
-3.250 -0.0898 0.01634 0.00850 -0.0706 0.8928 0.2121
-3.000 -0.0479 0.01585 0.00803 -0.0731 0.8904 0.2237
-2.750 -0.0254 0.01563 0.00786 -0.0718 0.8810 0.2326
-2.500 0.0118 0.01515 0.00744 -0.0734 0.8765 0.2439
-2.250 0.0526 0.01466 0.00700 -0.0756 0.8732 0.2576
-2.000 0.0748 0.01444 0.00684 -0.0742 0.8629 0.2703
-1.750 0.1110 0.01398 0.00646 -0.0755 0.8579 0.2895
-1.500 0.1365 0.01363 0.00627 -0.0748 0.8487 0.3116
-1.250 0.1683 0.01311 0.00594 -0.0752 0.8413 0.3493
-1.000 0.1921 0.01267 0.00574 -0.0741 0.8304 0.4016
-0.750 0.2222 0.01203 0.00542 -0.0741 0.8222 0.4816
-0.500 0.2407 0.01154 0.00531 -0.0717 0.8089 0.5730
-0.250 0.2610 0.01098 0.00526 -0.0694 0.7968 0.6992
0.000 0.3043 0.01062 0.00525 -0.0712 0.7878 0.8363
0.250 0.3601 0.01068 0.00538 -0.0760 0.7756 0.9045
0.500 0.4100 0.01078 0.00541 -0.0798 0.7640 0.9377
0.750 0.4649 0.01089 0.00540 -0.0847 0.7529 0.9575
1.000 0.5157 0.01099 0.00544 -0.0890 0.7394 0.9734
1.250 0.5671 0.01105 0.00542 -0.0937 0.7256 0.9863
1.500 0.6214 0.01105 0.00533 -0.0991 0.7117 0.9978
1.750 0.6503 0.01107 0.00526 -0.0993 0.6992 1.0000
2.000 0.6705 0.01113 0.00523 -0.0978 0.6867 1.0000
2.250 0.6895 0.01121 0.00526 -0.0960 0.6735 1.0000
2.500 0.7096 0.01130 0.00529 -0.0944 0.6611 1.0000
2.750 0.7310 0.01142 0.00532 -0.0930 0.6497 1.0000
3.000 0.7507 0.01154 0.00541 -0.0913 0.6374 1.0000
3.250 0.7703 0.01168 0.00551 -0.0896 0.6246 1.0000
3.500 0.7899 0.01183 0.00559 -0.0878 0.6106 1.0000
3.750 0.8092 0.01198 0.00568 -0.0859 0.5960 1.0000
4.000 0.8285 0.01215 0.00577 -0.0840 0.5811 1.0000
4.250 0.8478 0.01235 0.00588 -0.0822 0.5663 1.0000
4.500 0.8655 0.01253 0.00603 -0.0800 0.5504 1.0000
4.750 0.8830 0.01273 0.00618 -0.0778 0.5339 1.0000
5.000 0.9005 0.01294 0.00635 -0.0756 0.5178 1.0000
5.250 0.9183 0.01316 0.00655 -0.0735 0.5023 1.0000
5.500 0.9360 0.01339 0.00676 -0.0713 0.4869 1.0000
5.750 0.9528 0.01362 0.00695 -0.0691 0.4703 1.0000
6.000 0.9689 0.01385 0.00715 -0.0666 0.4527 1.0000
6.250 0.9840 0.01409 0.00735 -0.0640 0.4340 1.0000
6.500 0.9983 0.01436 0.00755 -0.0613 0.4150 1.0000
6.750 1.0122 0.01467 0.00778 -0.0585 0.3963 1.0000
7.000 1.0261 0.01500 0.00807 -0.0558 0.3783 1.0000
7.250 1.0396 0.01537 0.00838 -0.0531 0.3608 1.0000
7.500 1.0523 0.01579 0.00873 -0.0502 0.3434 1.0000
7.750 1.0643 0.01623 0.00911 -0.0473 0.3258 1.0000
8.000 1.0748 0.01668 0.00951 -0.0441 0.3090 1.0000
8.250 1.0838 0.01713 0.00992 -0.0407 0.2914 1.0000
8.500 1.0929 0.01762 0.01037 -0.0374 0.2730 1.0000
8.750 1.1015 0.01815 0.01085 -0.0341 0.2531 1.0000
9.000 1.1095 0.01877 0.01139 -0.0309 0.2325 1.0000
9.250 1.1180 0.01944 0.01200 -0.0279 0.2103 1.0000
9.500 1.1248 0.02025 0.01271 -0.0249 0.1909 1.0000
9.750 1.1310 0.02116 0.01352 -0.0219 0.1741 1.0000
10.000 1.1374 0.02214 0.01443 -0.0191 0.1594 1.0000
10.250 1.1443 0.02314 0.01540 -0.0165 0.1458 1.0000
10.500 1.1504 0.02424 0.01647 -0.0139 0.1319 1.0000
10.750 1.1547 0.02550 0.01766 -0.0114 0.1175 1.0000
11.250 1.1567 0.02866 0.02067 -0.0062 0.0914 1.0000
11.500 1.1593 0.03028 0.02229 -0.0040 0.0826 1.0000
11.750 1.1618 0.03198 0.02401 -0.0019 0.0769 1.0000
12.000 1.1654 0.03366 0.02569 -0.0002 0.0728 1.0000
12.250 1.1677 0.03552 0.02754 0.0016 0.0696 1.0000
12.500 1.1749 0.03705 0.02916 0.0029 0.0667 1.0000
12.750 1.1806 0.03872 0.03086 0.0042 0.0642 1.0000
13.000 1.1851 0.04056 0.03266 0.0054 0.0622 1.0000
13.250 1.1923 0.04224 0.03442 0.0066 0.0605 1.0000
13.500 1.2003 0.04387 0.03615 0.0076 0.0589 1.0000
13.750 1.2082 0.04554 0.03788 0.0085 0.0574 1.0000
14.000 1.2159 0.04726 0.03962 0.0093 0.0559 1.0000
14.250 1.2245 0.04892 0.04125 0.0102 0.0545 1.0000
14.500 1.2350 0.05054 0.04291 0.0111 0.0532 1.0000
14.750 1.2417 0.05246 0.04498 0.0118 0.0521 1.0000
15.000 1.2492 0.05438 0.04701 0.0124 0.0511 1.0000
15.250 1.2563 0.05635 0.04908 0.0130 0.0501 1.0000
15.500 1.2635 0.05831 0.05111 0.0135 0.0492 1.0000
15.750 1.2715 0.06021 0.05305 0.0140 0.0482 1.0000
16.000 1.2860 0.06170 0.05449 0.0147 0.0470 1.0000
16.250 1.2904 0.06422 0.05716 0.0151 0.0464 1.0000
16.500 1.2870 0.06737 0.06052 0.0150 0.0458 1.0000
16.750 1.2834 0.07071 0.06407 0.0148 0.0452 1.0000
17.000 1.2799 0.07413 0.06768 0.0145 0.0447 1.0000
17.250 1.2743 0.07790 0.07163 0.0139 0.0442 1.0000
17.500 1.2681 0.08179 0.07569 0.0130 0.0437 1.0000
17.750 1.2618 0.08580 0.07986 0.0119 0.0431 1.0000
18.000 1.2532 0.09023 0.08444 0.0105 0.0427 1.0000
18.250 1.2433 0.09497 0.08935 0.0088 0.0423 1.0000
18.500 1.2362 0.09931 0.09381 0.0071 0.0418 1.0000
18.750 1.2198 0.10538 0.10008 0.0044 0.0417 1.0000
19.000 1.2135 0.10988 0.10467 0.0024 0.0412 1.0000
19.250 1.1949 0.11665 0.11162 -0.0011 0.0410 1.0000
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Polar data table (+)
Polar graphs
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