GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 500,000 Max Cl/Cd: 94.65 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe629-il-500000.txt Download as CSV file: xf-goe629-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9368 0.08033 0.07672 -0.0667 1.0000 0.0311
-16.750 -0.9689 0.07254 0.06883 -0.0710 1.0000 0.0312
-16.500 -1.0072 0.06394 0.06010 -0.0758 1.0000 0.0312
-16.250 -1.0448 0.05535 0.05138 -0.0808 1.0000 0.0311
-16.000 -1.0802 0.04668 0.04254 -0.0865 1.0000 0.0309
-15.750 -1.1050 0.03949 0.03515 -0.0917 1.0000 0.0312
-15.500 -1.1220 0.03471 0.03020 -0.0944 1.0000 0.0316
-15.250 -1.1413 0.03121 0.02660 -0.0943 1.0000 0.0323
-15.000 -1.1542 0.02912 0.02442 -0.0920 1.0000 0.0330
-14.750 -1.1647 0.02770 0.02293 -0.0884 1.0000 0.0339
-14.500 -1.1760 0.02671 0.02187 -0.0835 1.0000 0.0350
-14.250 -1.1893 0.02604 0.02111 -0.0775 1.0000 0.0359
-14.000 -1.1992 0.02512 0.02015 -0.0722 1.0000 0.0372
-13.750 -1.2003 0.02434 0.01934 -0.0680 1.0000 0.0388
-13.500 -1.1958 0.02373 0.01864 -0.0646 1.0000 0.0411
-13.250 -1.1927 0.02300 0.01789 -0.0611 1.0000 0.0431
-13.000 -1.1836 0.02254 0.01739 -0.0583 1.0000 0.0456
-12.750 -1.1636 0.02196 0.01673 -0.0576 0.9990 0.0483
-12.500 -1.1317 0.02155 0.01631 -0.0591 0.9969 0.0514
-12.250 -1.0993 0.02115 0.01578 -0.0605 0.9948 0.0542
-12.000 -1.0678 0.02072 0.01536 -0.0620 0.9929 0.0568
-11.750 -1.0379 0.02047 0.01504 -0.0627 0.9902 0.0593
-11.500 -1.0066 0.02014 0.01459 -0.0638 0.9875 0.0615
-11.250 -0.9759 0.01963 0.01410 -0.0650 0.9852 0.0638
-11.000 -0.9420 0.01940 0.01383 -0.0666 0.9835 0.0662
-10.750 -0.9069 0.01917 0.01349 -0.0684 0.9821 0.0684
-10.500 -0.8825 0.01867 0.01290 -0.0681 0.9778 0.0702
-10.250 -0.8535 0.01815 0.01240 -0.0688 0.9747 0.0725
-10.000 -0.8206 0.01784 0.01206 -0.0701 0.9725 0.0746
-9.750 -0.7862 0.01755 0.01169 -0.0717 0.9709 0.0768
-9.500 -0.7503 0.01736 0.01138 -0.0734 0.9696 0.0786
-9.250 -0.7263 0.01660 0.01067 -0.0731 0.9653 0.0817
-9.000 -0.6954 0.01632 0.01038 -0.0739 0.9615 0.0843
-8.750 -0.6598 0.01598 0.00998 -0.0756 0.9591 0.0868
-8.500 -0.6219 0.01562 0.00953 -0.0776 0.9574 0.0885
-8.250 -0.5854 0.01479 0.00869 -0.0797 0.9561 0.0914
-8.000 -0.5465 0.01429 0.00820 -0.0821 0.9550 0.0937
-7.750 -0.5214 0.01399 0.00787 -0.0815 0.9491 0.0959
-7.500 -0.4898 0.01368 0.00750 -0.0823 0.9458 0.0982
-7.250 -0.4562 0.01338 0.00714 -0.0834 0.9433 0.0999
-7.000 -0.4233 0.01277 0.00656 -0.0846 0.9410 0.1033
-6.750 -0.3883 0.01244 0.00623 -0.0861 0.9389 0.1064
-6.500 -0.3673 0.01224 0.00601 -0.0845 0.9315 0.1089
-6.250 -0.3362 0.01199 0.00571 -0.0851 0.9275 0.1115
-6.000 -0.3050 0.01159 0.00532 -0.0857 0.9241 0.1157
-5.750 -0.2796 0.01139 0.00514 -0.0851 0.9182 0.1195
-5.500 -0.2520 0.01121 0.00492 -0.0849 0.9122 0.1235
-5.250 -0.2222 0.01090 0.00461 -0.0852 0.9076 0.1286
-5.000 -0.1966 0.01073 0.00446 -0.0845 0.9009 0.1342
-4.750 -0.1687 0.01062 0.00430 -0.0843 0.8945 0.1395
-4.500 -0.1394 0.01033 0.00405 -0.0845 0.8895 0.1471
-4.250 -0.1150 0.01025 0.00394 -0.0836 0.8816 0.1529
-4.000 -0.0876 0.01002 0.00371 -0.0833 0.8752 0.1595
-3.750 -0.0609 0.00989 0.00359 -0.0829 0.8680 0.1657
-3.500 -0.0340 0.00980 0.00345 -0.0825 0.8601 0.1708
-3.250 -0.0074 0.00959 0.00326 -0.0821 0.8527 0.1779
-3.000 0.0183 0.00948 0.00314 -0.0815 0.8441 0.1835
-2.750 0.0459 0.00936 0.00299 -0.0812 0.8364 0.1890
-2.500 0.0708 0.00921 0.00287 -0.0804 0.8263 0.1958
-2.250 0.0970 0.00912 0.00275 -0.0798 0.8158 0.2025
-2.000 0.1232 0.00899 0.00261 -0.0793 0.8050 0.2114
-1.500 0.1733 0.00877 0.00244 -0.0777 0.7815 0.2342
-1.250 0.1986 0.00867 0.00235 -0.0770 0.7694 0.2526
-1.000 0.2227 0.00854 0.00229 -0.0761 0.7553 0.2786
-0.750 0.2465 0.00840 0.00224 -0.0751 0.7413 0.3132
-0.500 0.2702 0.00825 0.00221 -0.0741 0.7280 0.3547
-0.250 0.2935 0.00810 0.00219 -0.0731 0.7148 0.4038
0.000 0.3161 0.00796 0.00218 -0.0719 0.7009 0.4600
0.250 0.3374 0.00777 0.00218 -0.0704 0.6865 0.5298
0.500 0.3573 0.00755 0.00220 -0.0686 0.6721 0.6116
0.750 0.3750 0.00727 0.00226 -0.0662 0.6585 0.7153
1.000 0.3951 0.00710 0.00235 -0.0642 0.6459 0.8099
1.250 0.4259 0.00710 0.00249 -0.0643 0.6333 0.8833
1.500 0.4719 0.00726 0.00265 -0.0679 0.6197 0.9257
1.750 0.5145 0.00743 0.00279 -0.0708 0.6071 0.9463
2.000 0.5547 0.00762 0.00292 -0.0732 0.5955 0.9593
2.250 0.5918 0.00783 0.00305 -0.0750 0.5846 0.9701
2.500 0.6325 0.00800 0.00319 -0.0776 0.5724 0.9779
2.750 0.6717 0.00818 0.00330 -0.0799 0.5588 0.9842
3.000 0.7141 0.00837 0.00341 -0.0830 0.5437 0.9906
3.250 0.7579 0.00854 0.00351 -0.0863 0.5270 0.9963
3.500 0.7974 0.00869 0.00359 -0.0889 0.5119 1.0000
3.750 0.8161 0.00880 0.00366 -0.0870 0.4994 1.0000
4.000 0.8349 0.00891 0.00374 -0.0851 0.4857 1.0000
4.250 0.8532 0.00904 0.00382 -0.0832 0.4704 1.0000
4.500 0.8708 0.00920 0.00392 -0.0811 0.4529 1.0000
4.750 0.8878 0.00938 0.00403 -0.0788 0.4331 1.0000
5.000 0.9040 0.00960 0.00416 -0.0764 0.4122 1.0000
5.250 0.9205 0.00982 0.00431 -0.0741 0.3911 1.0000
5.500 0.9354 0.01012 0.00449 -0.0715 0.3686 1.0000
5.750 0.9508 0.01042 0.00470 -0.0690 0.3505 1.0000
6.000 0.9670 0.01070 0.00492 -0.0667 0.3352 1.0000
6.250 0.9833 0.01098 0.00514 -0.0644 0.3210 1.0000
6.500 0.9998 0.01126 0.00538 -0.0621 0.3080 1.0000
6.750 1.0157 0.01156 0.00562 -0.0598 0.2938 1.0000
7.000 1.0314 0.01188 0.00588 -0.0574 0.2776 1.0000
7.250 1.0467 0.01220 0.00614 -0.0549 0.2616 1.0000
7.500 1.0599 0.01252 0.00640 -0.0521 0.2441 1.0000
7.750 1.0714 0.01290 0.00669 -0.0490 0.2226 1.0000
8.000 1.0813 0.01338 0.00704 -0.0457 0.1981 1.0000
8.250 1.0911 0.01393 0.00746 -0.0425 0.1753 1.0000
8.750 1.1138 0.01504 0.00840 -0.0368 0.1436 1.0000
9.000 1.1266 0.01558 0.00888 -0.0344 0.1303 1.0000
9.250 1.1393 0.01615 0.00940 -0.0320 0.1173 1.0000
9.500 1.1520 0.01674 0.00993 -0.0296 0.1051 1.0000
9.750 1.1634 0.01742 0.01055 -0.0272 0.0922 1.0000
10.000 1.1741 0.01817 0.01124 -0.0248 0.0794 1.0000
10.250 1.1838 0.01900 0.01201 -0.0223 0.0655 1.0000
10.500 1.1922 0.01994 0.01286 -0.0198 0.0546 1.0000
10.750 1.2025 0.02080 0.01370 -0.0176 0.0493 1.0000
11.000 1.2119 0.02174 0.01464 -0.0154 0.0461 1.0000
11.250 1.2227 0.02263 0.01557 -0.0135 0.0440 1.0000
11.500 1.2321 0.02365 0.01661 -0.0116 0.0425 1.0000
11.750 1.2388 0.02487 0.01786 -0.0095 0.0411 1.0000
12.000 1.2464 0.02609 0.01914 -0.0077 0.0401 1.0000
12.250 1.2556 0.02724 0.02036 -0.0061 0.0391 1.0000
12.500 1.2633 0.02855 0.02173 -0.0046 0.0383 1.0000
12.750 1.2702 0.02997 0.02321 -0.0031 0.0374 1.0000
13.000 1.2755 0.03156 0.02485 -0.0017 0.0367 1.0000
13.250 1.2780 0.03344 0.02678 -0.0003 0.0360 1.0000
13.500 1.2774 0.03567 0.02906 0.0010 0.0354 1.0000
13.750 1.2794 0.03775 0.03121 0.0021 0.0348 1.0000
14.000 1.2849 0.03960 0.03316 0.0029 0.0344 1.0000
14.250 1.2900 0.04155 0.03519 0.0035 0.0338 1.0000
14.500 1.2938 0.04367 0.03739 0.0041 0.0333 1.0000
14.750 1.2966 0.04594 0.03973 0.0046 0.0328 1.0000
15.000 1.2990 0.04832 0.04218 0.0050 0.0323 1.0000
15.250 1.3011 0.05078 0.04470 0.0052 0.0318 1.0000
15.500 1.3020 0.05339 0.04737 0.0054 0.0315 1.0000
15.750 1.3014 0.05617 0.05019 0.0056 0.0309 1.0000
16.000 1.3001 0.05897 0.05303 0.0059 0.0305 1.0000
16.250 1.3009 0.06163 0.05575 0.0061 0.0300 1.0000
16.500 1.3036 0.06421 0.05843 0.0060 0.0298 1.0000
16.750 1.3053 0.06709 0.06141 0.0055 0.0292 1.0000
17.000 1.3070 0.06985 0.06426 0.0052 0.0289 1.0000
17.250 1.3076 0.07283 0.06733 0.0048 0.0285 1.0000
17.500 1.3084 0.07575 0.07033 0.0044 0.0281 1.0000
17.750 1.3086 0.07879 0.07345 0.0039 0.0278 1.0000
18.000 1.3085 0.08196 0.07667 0.0031 0.0273 1.0000
18.250 1.3092 0.08494 0.07970 0.0026 0.0269 1.0000
18.500 1.3105 0.08777 0.08257 0.0022 0.0266 1.0000
18.750 1.3143 0.08984 0.08463 0.0026 0.0261 1.0000
19.000 1.3130 0.09302 0.08791 0.0021 0.0257 1.0000
19.250 1.3075 0.09738 0.09241 0.0003 0.0254 1.0000
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