GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 500,000 Max Cl/Cd: 86.12 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe676-il-500000.txt Download as CSV file: xf-goe676-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9026 0.04922 0.04621 -0.0523 1.0000 0.0235
-12.250 -0.9325 0.04417 0.04089 -0.0517 1.0000 0.0236
-12.000 -0.9451 0.04134 0.03792 -0.0494 1.0000 0.0238
-11.750 -0.9394 0.04028 0.03683 -0.0475 1.0000 0.0242
-11.500 -0.9248 0.03979 0.03633 -0.0465 1.0000 0.0245
-11.250 -0.9104 0.03916 0.03568 -0.0454 1.0000 0.0250
-11.000 -0.8996 0.03794 0.03436 -0.0441 1.0000 0.0255
-10.750 -0.8950 0.03568 0.03187 -0.0422 1.0000 0.0262
-10.500 -0.8919 0.03297 0.02882 -0.0400 1.0000 0.0271
-10.250 -0.8834 0.03105 0.02654 -0.0379 1.0000 0.0279
-10.000 -0.8795 0.02806 0.02321 -0.0353 1.0000 0.0287
-9.750 -0.8630 0.02718 0.02232 -0.0339 1.0000 0.0294
-9.500 -0.8466 0.02662 0.02172 -0.0323 1.0000 0.0300
-9.250 -0.8314 0.02600 0.02104 -0.0304 1.0000 0.0307
-9.000 -0.8180 0.02531 0.02026 -0.0281 1.0000 0.0315
-8.750 -0.8069 0.02448 0.01929 -0.0253 1.0000 0.0324
-8.500 -0.7879 0.02362 0.01823 -0.0241 0.9990 0.0333
-8.250 -0.7576 0.02173 0.01604 -0.0255 0.9961 0.0343
-8.000 -0.7249 0.02043 0.01469 -0.0272 0.9939 0.0355
-7.750 -0.6916 0.01994 0.01416 -0.0288 0.9905 0.0366
-7.500 -0.6573 0.01924 0.01338 -0.0305 0.9873 0.0379
-7.250 -0.6221 0.01835 0.01236 -0.0323 0.9849 0.0390
-7.000 -0.5857 0.01772 0.01160 -0.0343 0.9828 0.0402
-6.750 -0.5556 0.01655 0.01030 -0.0350 0.9772 0.0413
-6.500 -0.5233 0.01553 0.00926 -0.0363 0.9726 0.0426
-6.250 -0.4922 0.01500 0.00871 -0.0371 0.9666 0.0438
-6.000 -0.4632 0.01457 0.00826 -0.0373 0.9589 0.0452
-5.750 -0.4360 0.01414 0.00777 -0.0371 0.9505 0.0466
-5.500 -0.4102 0.01371 0.00727 -0.0366 0.9417 0.0477
-5.250 -0.3854 0.01339 0.00689 -0.0358 0.9313 0.0486
-5.000 -0.3631 0.01253 0.00600 -0.0347 0.9218 0.0506
-4.750 -0.3388 0.01217 0.00562 -0.0338 0.9116 0.0525
-4.500 -0.3136 0.01191 0.00533 -0.0332 0.9011 0.0547
-4.250 -0.2884 0.01164 0.00500 -0.0324 0.8912 0.0569
-4.000 -0.2633 0.01133 0.00462 -0.0317 0.8801 0.0591
-3.750 -0.2389 0.01088 0.00416 -0.0310 0.8687 0.0632
-3.500 -0.2130 0.01066 0.00390 -0.0304 0.8576 0.0673
-3.250 -0.1875 0.01040 0.00357 -0.0298 0.8462 0.0725
-3.000 -0.1616 0.01013 0.00329 -0.0293 0.8337 0.0794
-2.750 -0.1354 0.00989 0.00302 -0.0289 0.8216 0.0873
-2.500 -0.1091 0.00968 0.00281 -0.0285 0.8099 0.0982
-2.250 -0.0829 0.00944 0.00265 -0.0281 0.7983 0.1248
-2.000 -0.0567 0.00915 0.00250 -0.0279 0.7860 0.1672
-1.750 -0.0314 0.00873 0.00232 -0.0275 0.7739 0.2359
-1.500 -0.0100 0.00787 0.00214 -0.0266 0.7619 0.4326
-1.250 0.0107 0.00714 0.00200 -0.0254 0.7497 0.6003
-1.000 0.0304 0.00654 0.00200 -0.0234 0.7366 0.7637
-0.750 0.0541 0.00644 0.00210 -0.0220 0.7237 0.8421
-0.500 0.0795 0.00648 0.00216 -0.0210 0.7112 0.8781
-0.250 0.1049 0.00657 0.00222 -0.0200 0.6989 0.9026
0.000 0.1293 0.00670 0.00228 -0.0187 0.6869 0.9238
0.250 0.1550 0.00682 0.00237 -0.0178 0.6752 0.9388
0.500 0.1849 0.00697 0.00246 -0.0179 0.6638 0.9487
0.750 0.2156 0.00713 0.00253 -0.0181 0.6511 0.9581
1.000 0.2512 0.00732 0.00263 -0.0195 0.6385 0.9657
1.250 0.2877 0.00747 0.00271 -0.0212 0.6258 0.9711
1.500 0.3346 0.00765 0.00282 -0.0252 0.6123 0.9748
1.750 0.3738 0.00778 0.00289 -0.0276 0.6004 0.9797
2.000 0.4101 0.00788 0.00294 -0.0295 0.5888 0.9836
2.250 0.4497 0.00797 0.00296 -0.0321 0.5763 0.9860
2.500 0.4912 0.00806 0.00301 -0.0351 0.5617 0.9903
2.750 0.5317 0.00817 0.00306 -0.0379 0.5441 0.9946
3.000 0.5704 0.00822 0.00306 -0.0404 0.5246 0.9971
3.250 0.6056 0.00830 0.00308 -0.0421 0.5062 0.9992
3.500 0.6349 0.00839 0.00312 -0.0427 0.4871 1.0000
3.750 0.6597 0.00851 0.00316 -0.0422 0.4685 1.0000
4.000 0.6842 0.00865 0.00323 -0.0418 0.4506 1.0000
4.250 0.7086 0.00879 0.00332 -0.0413 0.4330 1.0000
4.500 0.7328 0.00894 0.00342 -0.0407 0.4172 1.0000
4.750 0.7566 0.00910 0.00353 -0.0401 0.4023 1.0000
5.000 0.7799 0.00928 0.00366 -0.0394 0.3870 1.0000
5.250 0.8026 0.00947 0.00380 -0.0386 0.3687 1.0000
5.500 0.8251 0.00967 0.00395 -0.0377 0.3523 1.0000
5.750 0.8473 0.00987 0.00412 -0.0368 0.3368 1.0000
6.000 0.8690 0.01009 0.00430 -0.0357 0.3192 1.0000
6.250 0.8903 0.01034 0.00450 -0.0346 0.3007 1.0000
6.500 0.9104 0.01066 0.00472 -0.0333 0.2736 1.0000
6.750 0.9287 0.01111 0.00499 -0.0318 0.2359 1.0000
7.250 0.9595 0.01249 0.00587 -0.0279 0.1459 1.0000
7.500 0.9778 0.01296 0.00628 -0.0263 0.1327 1.0000
7.750 0.9964 0.01341 0.00669 -0.0248 0.1231 1.0000
8.000 1.0166 0.01376 0.00706 -0.0235 0.1154 1.0000
8.250 1.0359 0.01422 0.00750 -0.0222 0.1065 1.0000
8.500 1.0567 0.01460 0.00787 -0.0212 0.0958 1.0000
8.750 1.0766 0.01509 0.00826 -0.0200 0.0727 1.0000
9.000 1.0912 0.01600 0.00896 -0.0182 0.0480 1.0000
9.250 1.1076 0.01678 0.00971 -0.0166 0.0405 1.0000
9.500 1.1243 0.01752 0.01045 -0.0150 0.0364 1.0000
9.750 1.1398 0.01831 0.01129 -0.0133 0.0333 1.0000
10.000 1.1563 0.01899 0.01203 -0.0118 0.0310 1.0000
10.250 1.1666 0.02002 0.01308 -0.0095 0.0287 1.0000
10.500 1.1781 0.02079 0.01393 -0.0072 0.0274 1.0000
10.750 1.1900 0.02157 0.01478 -0.0052 0.0261 1.0000
11.000 1.2007 0.02249 0.01575 -0.0032 0.0250 1.0000
11.250 1.2080 0.02368 0.01699 -0.0011 0.0240 1.0000
11.500 1.2080 0.02549 0.01886 0.0015 0.0231 1.0000
11.750 1.2205 0.02650 0.01996 0.0027 0.0224 1.0000
12.000 1.2307 0.02772 0.02127 0.0039 0.0216 1.0000
12.250 1.2399 0.02907 0.02269 0.0050 0.0208 1.0000
12.500 1.2477 0.03060 0.02427 0.0060 0.0201 1.0000
12.750 1.2528 0.03243 0.02617 0.0069 0.0196 1.0000
13.000 1.2523 0.03484 0.02864 0.0081 0.0191 1.0000
13.250 1.2537 0.03717 0.03106 0.0090 0.0186 1.0000
13.500 1.2603 0.03908 0.03308 0.0095 0.0183 1.0000
13.750 1.2653 0.04119 0.03530 0.0099 0.0179 1.0000
14.000 1.2693 0.04345 0.03767 0.0102 0.0175 1.0000
14.250 1.2726 0.04584 0.04015 0.0103 0.0171 1.0000
14.500 1.2755 0.04833 0.04273 0.0103 0.0168 1.0000
14.750 1.2777 0.05093 0.04542 0.0102 0.0164 1.0000
15.000 1.2789 0.05367 0.04822 0.0099 0.0161 1.0000
15.250 1.2791 0.05657 0.05118 0.0097 0.0158 1.0000
15.500 1.2769 0.05969 0.05437 0.0096 0.0154 1.0000
15.750 1.2722 0.06312 0.05790 0.0098 0.0151 1.0000
16.000 1.2706 0.06660 0.06153 0.0089 0.0150 1.0000
16.250 1.2679 0.07027 0.06534 0.0078 0.0148 1.0000
16.500 1.2642 0.07415 0.06936 0.0067 0.0146 1.0000
16.750 1.2594 0.07826 0.07361 0.0054 0.0144 1.0000
17.000 1.2538 0.08261 0.07810 0.0039 0.0143 1.0000
17.250 1.2472 0.08722 0.08284 0.0022 0.0141 1.0000
17.500 1.2395 0.09207 0.08783 0.0003 0.0140 1.0000
17.750 1.2310 0.09719 0.09310 -0.0019 0.0138 1.0000
18.000 1.2217 0.10258 0.09862 -0.0043 0.0137 1.0000
18.250 1.2113 0.10825 0.10443 -0.0070 0.0136 1.0000
18.500 1.1999 0.11424 0.11056 -0.0100 0.0135 1.0000
18.750 1.1872 0.12064 0.11711 -0.0133 0.0134 1.0000
19.000 1.1731 0.12753 0.12414 -0.0171 0.0134 1.0000
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Polar data table (+)
Polar graphs
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