GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 500,000 Max Cl/Cd: 81.93 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe629-il-500000-n5.txt Download as CSV file: xf-goe629-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9175 0.08084 0.07718 -0.0657 1.0000 0.0238
-16.500 -0.9820 0.06817 0.06431 -0.0729 1.0000 0.0229
-16.250 -1.0519 0.05463 0.05051 -0.0809 1.0000 0.0216
-16.000 -1.1010 0.04327 0.03888 -0.0890 1.0000 0.0211
-15.750 -1.1260 0.03661 0.03200 -0.0938 1.0000 0.0210
-15.500 -1.1434 0.03273 0.02798 -0.0948 1.0000 0.0215
-15.250 -1.1558 0.03032 0.02545 -0.0934 1.0000 0.0221
-15.000 -1.1668 0.02861 0.02364 -0.0904 1.0000 0.0229
-14.500 -1.1934 0.02652 0.02141 -0.0803 1.0000 0.0243
-14.250 -1.2010 0.02564 0.02047 -0.0754 0.9997 0.0254
-14.000 -1.1791 0.02439 0.01914 -0.0762 0.9971 0.0280
-13.750 -1.1561 0.02329 0.01797 -0.0769 0.9943 0.0308
-13.500 -1.1340 0.02232 0.01694 -0.0772 0.9914 0.0338
-13.250 -1.1104 0.02152 0.01607 -0.0774 0.9884 0.0367
-13.000 -1.0851 0.02075 0.01526 -0.0779 0.9858 0.0400
-12.750 -1.0575 0.02009 0.01455 -0.0787 0.9838 0.0427
-12.500 -1.0295 0.01949 0.01391 -0.0795 0.9820 0.0455
-12.250 -1.0063 0.01900 0.01333 -0.0791 0.9781 0.0476
-12.000 -0.9795 0.01847 0.01278 -0.0795 0.9753 0.0498
-11.750 -0.9503 0.01802 0.01228 -0.0802 0.9733 0.0525
-11.500 -0.9198 0.01760 0.01178 -0.0811 0.9717 0.0545
-11.250 -0.8892 0.01712 0.01129 -0.0821 0.9704 0.0567
-11.000 -0.8661 0.01677 0.01090 -0.0815 0.9657 0.0586
-10.750 -0.8376 0.01642 0.01048 -0.0818 0.9628 0.0606
-10.500 -0.8069 0.01608 0.01006 -0.0827 0.9607 0.0623
-10.250 -0.7757 0.01565 0.00963 -0.0837 0.9589 0.0647
-10.000 -0.7434 0.01532 0.00928 -0.0849 0.9573 0.0672
-9.750 -0.7167 0.01507 0.00896 -0.0848 0.9533 0.0692
-9.500 -0.6891 0.01482 0.00864 -0.0848 0.9490 0.0707
-9.250 -0.6599 0.01436 0.00817 -0.0853 0.9453 0.0729
-9.000 -0.6274 0.01396 0.00774 -0.0864 0.9423 0.0747
-8.750 -0.6024 0.01366 0.00740 -0.0859 0.9357 0.0761
-8.500 -0.5738 0.01335 0.00704 -0.0861 0.9300 0.0776
-8.250 -0.5416 0.01305 0.00667 -0.0870 0.9255 0.0793
-8.000 -0.5173 0.01283 0.00638 -0.0863 0.9172 0.0804
-7.750 -0.4890 0.01248 0.00600 -0.0864 0.9108 0.0821
-7.500 -0.4633 0.01218 0.00568 -0.0860 0.9046 0.0840
-7.250 -0.4374 0.01193 0.00541 -0.0856 0.8982 0.0860
-7.000 -0.4091 0.01169 0.00512 -0.0856 0.8926 0.0881
-6.750 -0.3840 0.01149 0.00488 -0.0850 0.8855 0.0898
-6.500 -0.3570 0.01130 0.00464 -0.0848 0.8791 0.0913
-6.250 -0.3305 0.01107 0.00439 -0.0844 0.8731 0.0941
-6.000 -0.3050 0.01087 0.00418 -0.0839 0.8659 0.0972
-5.750 -0.2777 0.01069 0.00397 -0.0837 0.8593 0.1003
-5.500 -0.2520 0.01054 0.00380 -0.0831 0.8516 0.1031
-5.250 -0.2255 0.01036 0.00362 -0.0827 0.8440 0.1079
-5.000 -0.1993 0.01023 0.00347 -0.0823 0.8366 0.1133
-4.750 -0.1730 0.01009 0.00333 -0.0818 0.8289 0.1186
-4.500 -0.1465 0.00997 0.00320 -0.0814 0.8216 0.1245
-4.250 -0.1200 0.00989 0.00308 -0.0810 0.8133 0.1293
-4.000 -0.0938 0.00977 0.00296 -0.0805 0.8051 0.1349
-3.750 -0.0676 0.00969 0.00286 -0.0800 0.7957 0.1404
-3.500 -0.0411 0.00963 0.00275 -0.0796 0.7868 0.1446
-3.250 -0.0152 0.00952 0.00265 -0.0791 0.7774 0.1498
-3.000 0.0110 0.00945 0.00256 -0.0786 0.7682 0.1544
-2.750 0.0371 0.00941 0.00247 -0.0780 0.7575 0.1581
-2.500 0.0626 0.00936 0.00237 -0.0773 0.7443 0.1620
-2.250 0.0876 0.00930 0.00229 -0.0766 0.7294 0.1669
-2.000 0.1128 0.00927 0.00222 -0.0759 0.7146 0.1718
-1.750 0.1380 0.00926 0.00216 -0.0751 0.7000 0.1766
-1.500 0.1626 0.00922 0.00210 -0.0743 0.6847 0.1831
-1.250 0.1871 0.00922 0.00205 -0.0735 0.6681 0.1894
-1.000 0.2113 0.00923 0.00201 -0.0726 0.6499 0.1968
-0.750 0.2353 0.00922 0.00199 -0.0717 0.6331 0.2087
-0.500 0.2595 0.00920 0.00198 -0.0708 0.6192 0.2253
-0.250 0.2840 0.00917 0.00197 -0.0700 0.6064 0.2444
0.000 0.3082 0.00913 0.00198 -0.0692 0.5938 0.2697
0.500 0.3565 0.00907 0.00202 -0.0675 0.5719 0.3237
0.750 0.3812 0.00903 0.00205 -0.0667 0.5629 0.3525
1.000 0.4050 0.00898 0.00209 -0.0658 0.5540 0.3886
1.250 0.4291 0.00891 0.00214 -0.0650 0.5454 0.4296
1.500 0.4524 0.00886 0.00220 -0.0640 0.5368 0.4743
1.750 0.4757 0.00877 0.00226 -0.0630 0.5283 0.5255
2.000 0.4978 0.00867 0.00233 -0.0617 0.5207 0.5848
2.250 0.5187 0.00850 0.00241 -0.0602 0.5138 0.6607
2.500 0.5380 0.00831 0.00251 -0.0582 0.5062 0.7516
2.750 0.5594 0.00821 0.00264 -0.0565 0.4973 0.8279
3.000 0.5971 0.00828 0.00285 -0.0584 0.4834 0.9055
3.250 0.6529 0.00853 0.00308 -0.0643 0.4635 0.9449
3.500 0.6948 0.00878 0.00324 -0.0674 0.4379 0.9616
3.750 0.7290 0.00906 0.00340 -0.0688 0.4115 0.9732
4.000 0.7590 0.00938 0.00358 -0.0693 0.3830 0.9830
4.250 0.7911 0.00980 0.00381 -0.0705 0.3489 0.9902
4.750 0.8578 0.01047 0.00427 -0.0732 0.3082 1.0000
5.000 0.8752 0.01069 0.00444 -0.0711 0.2973 1.0000
5.250 0.8925 0.01092 0.00462 -0.0690 0.2856 1.0000
5.500 0.9102 0.01115 0.00480 -0.0669 0.2728 1.0000
5.750 0.9272 0.01140 0.00500 -0.0648 0.2585 1.0000
6.000 0.9441 0.01166 0.00521 -0.0626 0.2441 1.0000
6.250 0.9599 0.01197 0.00544 -0.0603 0.2259 1.0000
6.500 0.9746 0.01234 0.00570 -0.0577 0.2058 1.0000
6.750 0.9875 0.01277 0.00600 -0.0549 0.1825 1.0000
7.000 0.9979 0.01320 0.00633 -0.0516 0.1632 1.0000
7.250 1.0101 0.01357 0.00664 -0.0486 0.1502 1.0000
7.500 1.0228 0.01396 0.00697 -0.0458 0.1376 1.0000
7.750 1.0365 0.01435 0.00731 -0.0432 0.1270 1.0000
8.000 1.0501 0.01478 0.00769 -0.0407 0.1160 1.0000
8.250 1.0636 0.01524 0.00810 -0.0382 0.1046 1.0000
8.500 1.0784 0.01567 0.00850 -0.0361 0.0961 1.0000
8.750 1.0923 0.01617 0.00895 -0.0338 0.0870 1.0000
9.000 1.1066 0.01667 0.00943 -0.0317 0.0803 1.0000
9.250 1.1211 0.01717 0.00992 -0.0296 0.0734 1.0000
9.500 1.1354 0.01771 0.01044 -0.0276 0.0662 1.0000
9.750 1.1475 0.01838 0.01105 -0.0254 0.0553 1.0000
10.000 1.1581 0.01915 0.01176 -0.0231 0.0452 1.0000
10.250 1.1697 0.01990 0.01249 -0.0209 0.0405 1.0000
10.500 1.1825 0.02061 0.01321 -0.0191 0.0381 1.0000
10.750 1.1948 0.02136 0.01398 -0.0172 0.0364 1.0000
11.000 1.2064 0.02219 0.01483 -0.0153 0.0348 1.0000
11.250 1.2192 0.02296 0.01566 -0.0137 0.0340 1.0000
11.500 1.2314 0.02381 0.01655 -0.0121 0.0332 1.0000
11.750 1.2427 0.02473 0.01753 -0.0105 0.0324 1.0000
12.000 1.2534 0.02573 0.01858 -0.0089 0.0319 1.0000
12.250 1.2626 0.02687 0.01976 -0.0074 0.0312 1.0000
12.500 1.2705 0.02814 0.02107 -0.0058 0.0306 1.0000
12.750 1.2770 0.02958 0.02256 -0.0043 0.0300 1.0000
13.000 1.2861 0.03085 0.02390 -0.0031 0.0296 1.0000
13.250 1.2950 0.03218 0.02531 -0.0020 0.0292 1.0000
13.500 1.3024 0.03368 0.02688 -0.0009 0.0287 1.0000
13.750 1.3093 0.03527 0.02855 0.0000 0.0283 1.0000
14.000 1.3150 0.03702 0.03037 0.0009 0.0278 1.0000
14.250 1.3203 0.03888 0.03229 0.0017 0.0274 1.0000
14.500 1.3244 0.04091 0.03440 0.0023 0.0270 1.0000
14.750 1.3276 0.04309 0.03664 0.0028 0.0266 1.0000
15.000 1.3292 0.04553 0.03915 0.0032 0.0263 1.0000
15.250 1.3282 0.04831 0.04201 0.0034 0.0259 1.0000
15.500 1.3253 0.05140 0.04517 0.0035 0.0255 1.0000
15.750 1.3260 0.05415 0.04800 0.0035 0.0253 1.0000
16.000 1.3290 0.05670 0.05065 0.0033 0.0250 1.0000
16.250 1.3294 0.05961 0.05365 0.0031 0.0248 1.0000
16.500 1.3295 0.06262 0.05676 0.0027 0.0245 1.0000
16.750 1.3293 0.06570 0.05993 0.0022 0.0241 1.0000
17.000 1.3278 0.06898 0.06329 0.0017 0.0238 1.0000
17.250 1.3259 0.07237 0.06678 0.0010 0.0235 1.0000
17.500 1.3232 0.07593 0.07043 0.0002 0.0232 1.0000
17.750 1.3194 0.07965 0.07424 -0.0007 0.0230 1.0000
18.000 1.3153 0.08349 0.07816 -0.0017 0.0227 1.0000
18.250 1.3110 0.08742 0.08217 -0.0029 0.0224 1.0000
18.500 1.3056 0.09154 0.08638 -0.0041 0.0222 1.0000
18.750 1.2993 0.09584 0.09074 -0.0055 0.0219 1.0000
19.000 1.2933 0.10011 0.09509 -0.0070 0.0218 1.0000
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