GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 500,000 Max Cl/Cd: 94.16 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe479-il-500000-n5.txt Download as CSV file: xf-goe479-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8486 0.04061 0.03746 -0.0895 1.0000 0.0217
-13.000 -0.8892 0.03743 0.03415 -0.0858 1.0000 0.0216
-12.750 -0.9008 0.03382 0.03024 -0.0853 0.9981 0.0218
-12.500 -0.8769 0.03178 0.02808 -0.0881 0.9942 0.0222
-12.250 -0.8528 0.03044 0.02665 -0.0896 0.9902 0.0225
-12.000 -0.8270 0.02932 0.02544 -0.0910 0.9869 0.0228
-11.750 -0.8000 0.02835 0.02439 -0.0923 0.9846 0.0232
-11.500 -0.7777 0.02709 0.02297 -0.0929 0.9810 0.0236
-11.250 -0.7543 0.02588 0.02160 -0.0935 0.9772 0.0242
-11.000 -0.7291 0.02445 0.01994 -0.0945 0.9744 0.0248
-10.750 -0.7024 0.02304 0.01829 -0.0957 0.9724 0.0253
-10.500 -0.6804 0.02200 0.01705 -0.0954 0.9676 0.0258
-10.250 -0.6538 0.02109 0.01607 -0.0960 0.9642 0.0263
-10.000 -0.6238 0.02047 0.01540 -0.0970 0.9616 0.0267
-9.750 -0.5929 0.01980 0.01465 -0.0982 0.9594 0.0272
-9.500 -0.5691 0.01914 0.01389 -0.0977 0.9538 0.0276
-9.250 -0.5418 0.01847 0.01312 -0.0980 0.9496 0.0281
-9.000 -0.5118 0.01782 0.01234 -0.0988 0.9462 0.0288
-8.750 -0.4851 0.01713 0.01152 -0.0989 0.9412 0.0293
-8.500 -0.4590 0.01650 0.01074 -0.0987 0.9349 0.0298
-8.250 -0.4302 0.01581 0.00993 -0.0991 0.9301 0.0302
-8.000 -0.4050 0.01522 0.00931 -0.0988 0.9237 0.0308
-7.750 -0.3781 0.01479 0.00883 -0.0987 0.9171 0.0313
-7.500 -0.3497 0.01438 0.00835 -0.0988 0.9111 0.0319
-7.250 -0.3246 0.01395 0.00787 -0.0983 0.9025 0.0324
-7.000 -0.2970 0.01354 0.00736 -0.0982 0.8949 0.0330
-6.750 -0.2717 0.01315 0.00691 -0.0976 0.8854 0.0335
-6.500 -0.2451 0.01278 0.00645 -0.0973 0.8762 0.0341
-6.250 -0.2188 0.01246 0.00602 -0.0968 0.8642 0.0347
-6.000 -0.1935 0.01210 0.00558 -0.0962 0.8496 0.0354
-5.750 -0.1682 0.01178 0.00520 -0.0956 0.8330 0.0362
-5.500 -0.1428 0.01154 0.00486 -0.0949 0.8142 0.0369
-5.250 -0.1177 0.01134 0.00456 -0.0942 0.7945 0.0377
-5.000 -0.0925 0.01115 0.00427 -0.0935 0.7765 0.0386
-4.750 -0.0672 0.01097 0.00399 -0.0928 0.7615 0.0394
-4.500 -0.0419 0.01082 0.00374 -0.0922 0.7475 0.0403
-4.250 -0.0166 0.01062 0.00348 -0.0915 0.7340 0.0415
-4.000 0.0090 0.01047 0.00328 -0.0909 0.7216 0.0431
-3.750 0.0348 0.01035 0.00310 -0.0904 0.7111 0.0447
-3.500 0.0608 0.01024 0.00293 -0.0898 0.7009 0.0464
-3.250 0.0868 0.01011 0.00275 -0.0893 0.6915 0.0482
-3.000 0.1127 0.00999 0.00260 -0.0888 0.6818 0.0508
-2.750 0.1390 0.00989 0.00247 -0.0883 0.6733 0.0536
-2.500 0.1652 0.00980 0.00234 -0.0878 0.6652 0.0572
-2.250 0.1917 0.00970 0.00224 -0.0874 0.6578 0.0623
-2.000 0.2179 0.00961 0.00214 -0.0870 0.6497 0.0687
-1.750 0.2442 0.00952 0.00206 -0.0865 0.6421 0.0783
-1.500 0.2703 0.00941 0.00199 -0.0861 0.6343 0.0946
-1.250 0.2963 0.00931 0.00195 -0.0856 0.6275 0.1197
-1.000 0.3227 0.00921 0.00192 -0.0852 0.6202 0.1451
-0.750 0.3486 0.00914 0.00190 -0.0847 0.6127 0.1711
-0.500 0.3749 0.00904 0.00188 -0.0844 0.6049 0.1997
-0.250 0.4006 0.00896 0.00188 -0.0839 0.5970 0.2367
0.000 0.4266 0.00886 0.00189 -0.0834 0.5893 0.2775
0.250 0.4519 0.00875 0.00190 -0.0829 0.5806 0.3276
0.500 0.4754 0.00846 0.00192 -0.0820 0.5704 0.4403
0.750 0.4953 0.00803 0.00199 -0.0805 0.5582 0.6151
1.000 0.5125 0.00765 0.00206 -0.0780 0.5431 0.7748
1.250 0.5643 0.00749 0.00222 -0.0828 0.5233 0.9391
1.500 0.6149 0.00764 0.00228 -0.0877 0.5067 0.9740
1.750 0.6522 0.00780 0.00234 -0.0897 0.4917 0.9883
2.000 0.6927 0.00798 0.00242 -0.0925 0.4766 1.0000
2.500 0.7382 0.00827 0.00258 -0.0902 0.4539 1.0000
2.750 0.7609 0.00842 0.00267 -0.0891 0.4438 1.0000
3.250 0.8055 0.00880 0.00290 -0.0867 0.4174 1.0000
3.500 0.8281 0.00898 0.00302 -0.0856 0.4053 1.0000
3.750 0.8505 0.00917 0.00316 -0.0845 0.3932 1.0000
4.000 0.8727 0.00938 0.00330 -0.0833 0.3802 1.0000
4.250 0.8956 0.00956 0.00344 -0.0823 0.3687 1.0000
4.500 0.9181 0.00975 0.00359 -0.0812 0.3562 1.0000
4.750 0.9393 0.01001 0.00377 -0.0799 0.3371 1.0000
5.000 0.9605 0.01028 0.00395 -0.0786 0.3191 1.0000
5.250 0.9809 0.01059 0.00416 -0.0771 0.2971 1.0000
5.500 0.9992 0.01103 0.00443 -0.0754 0.2679 1.0000
5.750 1.0182 0.01143 0.00472 -0.0738 0.2450 1.0000
6.000 1.0377 0.01181 0.00501 -0.0723 0.2276 1.0000
6.250 1.0574 0.01217 0.00530 -0.0708 0.2126 1.0000
6.500 1.0769 0.01254 0.00561 -0.0693 0.1979 1.0000
6.750 1.0944 0.01301 0.00597 -0.0675 0.1781 1.0000
7.000 1.1119 0.01347 0.00634 -0.0657 0.1571 1.0000
7.250 1.1266 0.01407 0.00678 -0.0635 0.1306 1.0000
7.500 1.1295 0.01517 0.00755 -0.0594 0.0760 1.0000
7.750 1.1369 0.01598 0.00821 -0.0559 0.0536 1.0000
8.000 1.1507 0.01650 0.00871 -0.0536 0.0476 1.0000
8.250 1.1663 0.01695 0.00917 -0.0516 0.0448 1.0000
8.500 1.1813 0.01744 0.00968 -0.0495 0.0427 1.0000
8.750 1.1958 0.01797 0.01023 -0.0475 0.0410 1.0000
9.000 1.2114 0.01846 0.01076 -0.0457 0.0401 1.0000
9.250 1.2264 0.01898 0.01132 -0.0438 0.0391 1.0000
9.500 1.2409 0.01954 0.01194 -0.0420 0.0384 1.0000
9.750 1.2546 0.02017 0.01260 -0.0401 0.0376 1.0000
10.000 1.2674 0.02086 0.01332 -0.0382 0.0367 1.0000
10.250 1.2792 0.02162 0.01413 -0.0363 0.0359 1.0000
10.500 1.2898 0.02250 0.01505 -0.0343 0.0352 1.0000
10.750 1.2984 0.02352 0.01612 -0.0322 0.0345 1.0000
11.000 1.3093 0.02443 0.01710 -0.0305 0.0342 1.0000
11.250 1.3198 0.02541 0.01814 -0.0289 0.0338 1.0000
11.500 1.3298 0.02647 0.01926 -0.0273 0.0334 1.0000
11.750 1.3394 0.02759 0.02046 -0.0258 0.0329 1.0000
12.000 1.3481 0.02883 0.02176 -0.0244 0.0324 1.0000
12.250 1.3563 0.03016 0.02317 -0.0232 0.0320 1.0000
12.500 1.3630 0.03166 0.02474 -0.0219 0.0315 1.0000
12.750 1.3695 0.03326 0.02640 -0.0208 0.0311 1.0000
13.000 1.3754 0.03497 0.02819 -0.0199 0.0307 1.0000
13.250 1.3797 0.03687 0.03016 -0.0190 0.0303 1.0000
13.500 1.3824 0.03901 0.03236 -0.0182 0.0298 1.0000
13.750 1.3824 0.04148 0.03490 -0.0175 0.0293 1.0000
14.000 1.3813 0.04414 0.03763 -0.0169 0.0290 1.0000
14.250 1.3877 0.04610 0.03968 -0.0166 0.0286 1.0000
14.500 1.3911 0.04843 0.04211 -0.0164 0.0283 1.0000
14.750 1.3947 0.05079 0.04457 -0.0162 0.0279 1.0000
15.000 1.3966 0.05338 0.04724 -0.0162 0.0275 1.0000
15.250 1.3985 0.05604 0.04998 -0.0162 0.0271 1.0000
15.500 1.3995 0.05886 0.05290 -0.0164 0.0267 1.0000
15.750 1.4000 0.06182 0.05593 -0.0167 0.0263 1.0000
16.000 1.3999 0.06487 0.05907 -0.0171 0.0260 1.0000
16.250 1.3989 0.06814 0.06242 -0.0176 0.0257 1.0000
16.500 1.3979 0.07147 0.06582 -0.0182 0.0253 1.0000
16.750 1.3957 0.07503 0.06946 -0.0190 0.0250 1.0000
17.000 1.3915 0.07885 0.07335 -0.0199 0.0247 1.0000
17.250 1.3868 0.08281 0.07737 -0.0208 0.0243 1.0000
17.500 1.3872 0.08619 0.08087 -0.0218 0.0240 1.0000
17.750 1.3857 0.08983 0.08461 -0.0228 0.0237 1.0000
18.000 1.3849 0.09344 0.08833 -0.0240 0.0233 1.0000
18.250 1.3819 0.09735 0.09235 -0.0252 0.0230 1.0000
18.500 1.3798 0.10123 0.09632 -0.0266 0.0226 1.0000
18.750 1.3781 0.10509 0.10027 -0.0281 0.0221 1.0000
19.000 1.3751 0.10917 0.10443 -0.0296 0.0218 1.0000
19.250 1.3724 0.11327 0.10862 -0.0314 0.0214 1.0000
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Polar data table (+)
Polar graphs
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