GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 200,000 Max Cl/Cd: 66.25 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe629-il-200000-n5.txt Download as CSV file: xf-goe629-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8358 0.06990 0.06542 -0.0724 1.0000 0.0503
-14.750 -0.9228 0.05311 0.04829 -0.0836 1.0000 0.0491
-14.500 -0.9515 0.04594 0.04094 -0.0886 1.0000 0.0494
-14.250 -0.9698 0.04134 0.03618 -0.0911 1.0000 0.0501
-14.000 -0.9832 0.03833 0.03305 -0.0912 1.0000 0.0511
-13.750 -0.9956 0.03615 0.03073 -0.0895 1.0000 0.0521
-13.500 -1.0079 0.03450 0.02894 -0.0864 1.0000 0.0532
-13.250 -1.0218 0.03325 0.02753 -0.0818 1.0000 0.0543
-13.000 -1.0333 0.03246 0.02670 -0.0766 1.0000 0.0551
-12.750 -1.0354 0.03176 0.02597 -0.0727 1.0000 0.0562
-12.500 -1.0346 0.03111 0.02525 -0.0692 1.0000 0.0575
-12.250 -1.0325 0.03039 0.02441 -0.0657 1.0000 0.0591
-12.000 -1.0291 0.02962 0.02348 -0.0625 1.0000 0.0608
-11.750 -1.0075 0.02871 0.02240 -0.0626 0.9975 0.0630
-11.500 -0.9799 0.02811 0.02176 -0.0637 0.9943 0.0649
-11.250 -0.9535 0.02748 0.02099 -0.0644 0.9908 0.0673
-11.000 -0.9275 0.02673 0.02002 -0.0651 0.9871 0.0700
-10.750 -0.8997 0.02605 0.01926 -0.0660 0.9841 0.0724
-10.500 -0.8718 0.02567 0.01884 -0.0668 0.9808 0.0750
-10.250 -0.8465 0.02512 0.01817 -0.0669 0.9764 0.0776
-10.000 -0.8186 0.02439 0.01723 -0.0676 0.9731 0.0798
-9.750 -0.7887 0.02358 0.01629 -0.0687 0.9707 0.0816
-9.500 -0.7656 0.02297 0.01567 -0.0683 0.9657 0.0834
-9.250 -0.7382 0.02241 0.01505 -0.0687 0.9618 0.0852
-9.000 -0.7078 0.02183 0.01437 -0.0696 0.9590 0.0873
-8.750 -0.6755 0.02125 0.01365 -0.0709 0.9569 0.0896
-8.500 -0.6534 0.02076 0.01302 -0.0699 0.9510 0.0913
-8.250 -0.6255 0.02013 0.01239 -0.0703 0.9471 0.0933
-8.000 -0.5937 0.01964 0.01189 -0.0714 0.9443 0.0956
-7.750 -0.5587 0.01916 0.01134 -0.0730 0.9421 0.0982
-7.500 -0.5344 0.01873 0.01083 -0.0723 0.9349 0.1005
-7.250 -0.5005 0.01821 0.01019 -0.0736 0.9302 0.1029
-7.000 -0.4643 0.01766 0.00966 -0.0753 0.9269 0.1058
-6.750 -0.4376 0.01731 0.00930 -0.0752 0.9210 0.1087
-6.500 -0.4101 0.01697 0.00890 -0.0751 0.9155 0.1119
-6.250 -0.3779 0.01659 0.00843 -0.0759 0.9118 0.1152
-6.000 -0.3444 0.01618 0.00805 -0.0771 0.9090 0.1189
-5.750 -0.3229 0.01596 0.00782 -0.0758 0.9012 0.1226
-5.500 -0.2924 0.01566 0.00746 -0.0762 0.8964 0.1274
-5.250 -0.2596 0.01529 0.00709 -0.0772 0.8928 0.1319
-5.000 -0.2360 0.01507 0.00687 -0.0763 0.8851 0.1365
-4.750 -0.2060 0.01483 0.00657 -0.0766 0.8795 0.1425
-4.250 -0.1504 0.01433 0.00608 -0.0764 0.8670 0.1540
-4.000 -0.1196 0.01411 0.00579 -0.0768 0.8613 0.1599
-3.750 -0.0929 0.01383 0.00556 -0.0765 0.8540 0.1655
-3.500 -0.0651 0.01363 0.00534 -0.0763 0.8464 0.1718
-3.250 -0.0352 0.01342 0.00511 -0.0766 0.8402 0.1783
-3.000 -0.0102 0.01323 0.00495 -0.0759 0.8314 0.1849
-2.750 0.0208 0.01304 0.00472 -0.0763 0.8249 0.1921
-2.500 0.0449 0.01287 0.00459 -0.0754 0.8148 0.1986
-2.250 0.0741 0.01269 0.00440 -0.0755 0.8070 0.2070
-2.000 0.0992 0.01254 0.00429 -0.0748 0.7969 0.2162
-1.750 0.1269 0.01239 0.00416 -0.0746 0.7883 0.2279
-1.250 0.1783 0.01208 0.00396 -0.0734 0.7664 0.2639
-1.000 0.2044 0.01191 0.00386 -0.0729 0.7541 0.2888
-0.750 0.2301 0.01177 0.00375 -0.0722 0.7406 0.3145
-0.500 0.2542 0.01162 0.00368 -0.0713 0.7258 0.3437
-0.250 0.2782 0.01148 0.00362 -0.0703 0.7104 0.3791
0.000 0.3017 0.01133 0.00358 -0.0693 0.6956 0.4223
0.250 0.3249 0.01117 0.00357 -0.0681 0.6824 0.4719
0.500 0.3476 0.01101 0.00356 -0.0669 0.6699 0.5285
0.750 0.3691 0.01082 0.00359 -0.0654 0.6573 0.5972
1.000 0.3900 0.01059 0.00367 -0.0636 0.6454 0.6868
1.250 0.4177 0.01044 0.00382 -0.0630 0.6339 0.7925
1.500 0.4675 0.01052 0.00401 -0.0670 0.6209 0.8754
1.750 0.5157 0.01068 0.00416 -0.0710 0.6078 0.9175
2.000 0.5545 0.01084 0.00428 -0.0730 0.5963 0.9409
2.250 0.5945 0.01102 0.00439 -0.0754 0.5850 0.9590
2.500 0.6358 0.01122 0.00453 -0.0781 0.5726 0.9773
2.750 0.6814 0.01140 0.00466 -0.0818 0.5603 0.9917
3.000 0.7233 0.01156 0.00477 -0.0848 0.5492 1.0000
3.250 0.7426 0.01172 0.00487 -0.0830 0.5380 1.0000
3.500 0.7617 0.01187 0.00499 -0.0812 0.5257 1.0000
3.750 0.7803 0.01205 0.00512 -0.0793 0.5123 1.0000
4.000 0.7984 0.01225 0.00525 -0.0773 0.4978 1.0000
4.250 0.8160 0.01245 0.00539 -0.0752 0.4816 1.0000
4.500 0.8336 0.01265 0.00554 -0.0731 0.4651 1.0000
4.750 0.8506 0.01286 0.00570 -0.0709 0.4464 1.0000
5.000 0.8672 0.01309 0.00587 -0.0686 0.4260 1.0000
5.250 0.8834 0.01335 0.00606 -0.0663 0.4061 1.0000
5.500 0.8995 0.01362 0.00626 -0.0640 0.3883 1.0000
5.750 0.9147 0.01394 0.00649 -0.0615 0.3705 1.0000
6.000 0.9289 0.01429 0.00675 -0.0589 0.3525 1.0000
6.250 0.9428 0.01467 0.00704 -0.0562 0.3354 1.0000
6.500 0.9564 0.01507 0.00735 -0.0535 0.3185 1.0000
6.750 0.9703 0.01546 0.00768 -0.0509 0.3023 1.0000
7.000 0.9845 0.01585 0.00803 -0.0484 0.2871 1.0000
7.250 0.9982 0.01621 0.00837 -0.0458 0.2731 1.0000
7.500 1.0112 0.01659 0.00872 -0.0431 0.2585 1.0000
7.750 1.0234 0.01702 0.00910 -0.0403 0.2415 1.0000
8.000 1.0344 0.01752 0.00954 -0.0374 0.2220 1.0000
8.250 1.0454 0.01808 0.01001 -0.0346 0.2015 1.0000
8.500 1.0551 0.01874 0.01056 -0.0318 0.1812 1.0000
8.750 1.0645 0.01946 0.01119 -0.0290 0.1637 1.0000
9.000 1.0752 0.02017 0.01184 -0.0265 0.1502 1.0000
9.250 1.0866 0.02087 0.01252 -0.0242 0.1387 1.0000
9.500 1.0979 0.02160 0.01323 -0.0220 0.1291 1.0000
9.750 1.1088 0.02237 0.01399 -0.0198 0.1192 1.0000
10.000 1.1205 0.02314 0.01477 -0.0178 0.1103 1.0000
10.250 1.1306 0.02401 0.01564 -0.0157 0.1017 1.0000
10.750 1.1494 0.02595 0.01756 -0.0117 0.0851 1.0000
11.000 1.1579 0.02703 0.01865 -0.0098 0.0776 1.0000
11.250 1.1650 0.02824 0.01985 -0.0079 0.0708 1.0000
11.500 1.1736 0.02939 0.02105 -0.0062 0.0641 1.0000
11.750 1.1806 0.03070 0.02239 -0.0045 0.0588 1.0000
12.000 1.1867 0.03213 0.02383 -0.0029 0.0547 1.0000
12.250 1.1927 0.03361 0.02536 -0.0014 0.0516 1.0000
12.500 1.1981 0.03520 0.02699 -0.0001 0.0491 1.0000
12.750 1.2018 0.03698 0.02881 0.0012 0.0472 1.0000
13.000 1.2060 0.03879 0.03069 0.0023 0.0458 1.0000
13.250 1.2100 0.04067 0.03266 0.0033 0.0445 1.0000
13.500 1.2129 0.04273 0.03479 0.0042 0.0432 1.0000
13.750 1.2149 0.04495 0.03708 0.0048 0.0423 1.0000
14.000 1.2155 0.04738 0.03958 0.0054 0.0415 1.0000
14.250 1.2148 0.05004 0.04230 0.0058 0.0408 1.0000
14.500 1.2154 0.05264 0.04499 0.0060 0.0401 1.0000
14.750 1.2170 0.05520 0.04766 0.0062 0.0394 1.0000
15.000 1.2180 0.05791 0.05047 0.0062 0.0388 1.0000
15.250 1.2184 0.06074 0.05339 0.0061 0.0380 1.0000
15.500 1.2182 0.06369 0.05643 0.0059 0.0372 1.0000
15.750 1.2179 0.06671 0.05953 0.0055 0.0367 1.0000
16.000 1.2168 0.06989 0.06278 0.0051 0.0362 1.0000
16.250 1.2154 0.07313 0.06609 0.0045 0.0356 1.0000
16.500 1.2141 0.07635 0.06935 0.0041 0.0351 1.0000
16.750 1.2139 0.07952 0.07261 0.0035 0.0346 1.0000
17.000 1.2140 0.08274 0.07594 0.0028 0.0342 1.0000
17.250 1.2136 0.08610 0.07943 0.0019 0.0336 1.0000
17.500 1.2128 0.08953 0.08297 0.0010 0.0331 1.0000
17.750 1.2114 0.09310 0.08665 -0.0001 0.0325 1.0000
18.000 1.2104 0.09665 0.09029 -0.0012 0.0321 1.0000
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