GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.24 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe505-il-1000000-n5.txt Download as CSV file: xf-goe505-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5797 0.03561 0.03289 -0.1613 0.9483 0.0189
-13.750 -0.5755 0.02874 0.02571 -0.1685 0.9410 0.0191
-13.500 -0.5671 0.02674 0.02353 -0.1685 0.9319 0.0193
-13.250 -0.5618 0.02533 0.02198 -0.1667 0.9215 0.0195
-13.000 -0.5506 0.02440 0.02092 -0.1651 0.9110 0.0198
-12.750 -0.5420 0.02355 0.01993 -0.1627 0.8976 0.0200
-12.500 -0.5335 0.02258 0.01879 -0.1603 0.8833 0.0201
-12.250 -0.5199 0.02196 0.01802 -0.1584 0.8713 0.0203
-12.000 -0.5098 0.02114 0.01704 -0.1560 0.8612 0.0204
-11.750 -0.4917 0.02077 0.01656 -0.1546 0.8540 0.0206
-11.500 -0.4767 0.02018 0.01586 -0.1527 0.8478 0.0207
-11.250 -0.4665 0.01925 0.01479 -0.1502 0.8417 0.0210
-11.000 -0.4537 0.01844 0.01385 -0.1480 0.8368 0.0212
-10.750 -0.4372 0.01783 0.01317 -0.1462 0.8325 0.0215
-10.500 -0.4186 0.01735 0.01262 -0.1448 0.8286 0.0217
-10.250 -0.3996 0.01686 0.01204 -0.1434 0.8252 0.0218
-10.000 -0.3794 0.01642 0.01152 -0.1421 0.8224 0.0220
-9.750 -0.3591 0.01596 0.01100 -0.1409 0.8198 0.0222
-9.500 -0.3379 0.01555 0.01053 -0.1398 0.8170 0.0224
-9.250 -0.3163 0.01516 0.01009 -0.1387 0.8142 0.0226
-9.000 -0.2943 0.01479 0.00965 -0.1377 0.8118 0.0229
-8.750 -0.2721 0.01441 0.00919 -0.1367 0.8094 0.0231
-8.500 -0.2497 0.01403 0.00873 -0.1357 0.8063 0.0233
-8.250 -0.2279 0.01363 0.00827 -0.1346 0.8034 0.0235
-8.000 -0.2057 0.01326 0.00784 -0.1335 0.7994 0.0237
-7.750 -0.1832 0.01291 0.00742 -0.1325 0.7954 0.0239
-7.500 -0.1600 0.01261 0.00704 -0.1316 0.7918 0.0242
-7.250 -0.1367 0.01230 0.00668 -0.1307 0.7882 0.0244
-7.000 -0.1133 0.01200 0.00633 -0.1298 0.7846 0.0246
-6.750 -0.0894 0.01173 0.00601 -0.1289 0.7810 0.0248
-6.500 -0.0657 0.01148 0.00570 -0.1281 0.7768 0.0249
-6.250 -0.0415 0.01128 0.00544 -0.1272 0.7723 0.0251
-6.000 -0.0172 0.01109 0.00523 -0.1265 0.7671 0.0253
-5.750 0.0064 0.01089 0.00498 -0.1255 0.7610 0.0254
-5.500 0.0286 0.01054 0.00456 -0.1243 0.7549 0.0258
-5.250 0.0519 0.01025 0.00423 -0.1233 0.7486 0.0261
-5.000 0.0752 0.01001 0.00393 -0.1223 0.7430 0.0266
-4.750 0.0997 0.00982 0.00371 -0.1216 0.7382 0.0268
-4.500 0.1243 0.00963 0.00350 -0.1208 0.7327 0.0272
-4.250 0.1477 0.00948 0.00331 -0.1198 0.7257 0.0275
-4.000 0.1722 0.00933 0.00313 -0.1190 0.7187 0.0279
-3.750 0.1951 0.00922 0.00297 -0.1179 0.7098 0.0282
-3.500 0.2181 0.00911 0.00283 -0.1168 0.6984 0.0286
-3.250 0.2391 0.00905 0.00269 -0.1152 0.6836 0.0290
-3.000 0.2579 0.00903 0.00258 -0.1132 0.6647 0.0293
-2.750 0.2744 0.00907 0.00250 -0.1107 0.6397 0.0298
-2.500 0.2893 0.00915 0.00245 -0.1078 0.6130 0.0302
-2.250 0.3043 0.00924 0.00242 -0.1051 0.5870 0.0306
-2.000 0.3178 0.00934 0.00240 -0.1019 0.5607 0.0310
-1.750 0.3298 0.00942 0.00236 -0.0985 0.5365 0.0318
-1.500 0.3431 0.00950 0.00234 -0.0954 0.5127 0.0329
-1.250 0.3568 0.00961 0.00234 -0.0924 0.4889 0.0341
-1.000 0.3711 0.00971 0.00236 -0.0895 0.4667 0.0359
-0.750 0.3865 0.00983 0.00238 -0.0869 0.4452 0.0382
-0.500 0.4014 0.00986 0.00242 -0.0842 0.4262 0.0614
-0.250 0.4172 0.00995 0.00249 -0.0817 0.4086 0.0783
0.000 0.4343 0.01004 0.00256 -0.0795 0.3937 0.0921
0.250 0.4520 0.01015 0.00264 -0.0775 0.3806 0.1022
0.750 0.4874 0.01033 0.00281 -0.0734 0.3585 0.1353
1.000 0.5065 0.01039 0.00291 -0.0717 0.3516 0.1590
1.250 0.5260 0.01048 0.00301 -0.0700 0.3444 0.1719
1.500 0.5447 0.01060 0.00312 -0.0682 0.3368 0.1832
1.750 0.5648 0.01071 0.00322 -0.0667 0.3307 0.1923
2.000 0.5843 0.01082 0.00333 -0.0651 0.3251 0.2016
2.250 0.6047 0.01094 0.00343 -0.0637 0.3212 0.2067
2.500 0.6256 0.01104 0.00354 -0.0623 0.3179 0.2123
2.750 0.6451 0.01115 0.00366 -0.0608 0.3129 0.2222
3.000 0.6645 0.01128 0.00380 -0.0592 0.3088 0.2352
3.250 0.6839 0.01140 0.00394 -0.0577 0.3043 0.2513
3.750 0.7240 0.01159 0.00424 -0.0549 0.2981 0.2944
4.000 0.7436 0.01171 0.00440 -0.0534 0.2954 0.3154
4.250 0.7629 0.01184 0.00458 -0.0519 0.2924 0.3408
4.500 0.7822 0.01199 0.00476 -0.0504 0.2888 0.3635
4.750 0.8024 0.01209 0.00493 -0.0491 0.2865 0.3921
5.000 0.8214 0.01217 0.00511 -0.0476 0.2843 0.4344
5.500 1.0154 0.01181 0.00603 -0.0794 0.2741 0.9919
5.750 1.0441 0.01210 0.00631 -0.0800 0.2715 0.9980
6.000 1.0809 0.01239 0.00657 -0.0825 0.2640 0.9998
6.250 1.1003 0.01267 0.00681 -0.0812 0.2593 1.0000
6.500 1.1179 0.01290 0.00703 -0.0795 0.2546 1.0000
6.750 1.1346 0.01318 0.00728 -0.0777 0.2483 1.0000
7.000 1.1505 0.01351 0.00758 -0.0757 0.2423 1.0000
7.250 1.1672 0.01382 0.00786 -0.0740 0.2339 1.0000
7.500 1.1824 0.01422 0.00820 -0.0720 0.2239 1.0000
7.750 1.1964 0.01468 0.00860 -0.0700 0.2127 1.0000
8.000 1.2055 0.01540 0.00917 -0.0672 0.1891 1.0000
8.250 1.2156 0.01611 0.00977 -0.0646 0.1726 1.0000
8.500 1.2262 0.01684 0.01040 -0.0623 0.1573 1.0000
8.750 1.2369 0.01758 0.01106 -0.0600 0.1434 1.0000
9.000 1.2470 0.01839 0.01177 -0.0577 0.1266 1.0000
9.250 1.2281 0.02091 0.01388 -0.0516 0.0558 1.0000
9.500 1.2269 0.02251 0.01535 -0.0481 0.0163 1.0000
9.750 1.2413 0.02319 0.01605 -0.0467 0.0145 1.0000
10.000 1.2551 0.02393 0.01680 -0.0452 0.0129 1.0000
10.250 1.2688 0.02469 0.01759 -0.0438 0.0121 1.0000
10.500 1.2828 0.02544 0.01837 -0.0425 0.0116 1.0000
10.750 1.2960 0.02625 0.01921 -0.0412 0.0110 1.0000
11.000 1.3090 0.02710 0.02009 -0.0399 0.0105 1.0000
11.250 1.3207 0.02805 0.02108 -0.0385 0.0101 1.0000
11.500 1.3319 0.02907 0.02213 -0.0371 0.0097 1.0000
11.750 1.3425 0.03014 0.02324 -0.0357 0.0093 1.0000
12.000 1.3545 0.03114 0.02427 -0.0345 0.0088 1.0000
12.250 1.3649 0.03227 0.02544 -0.0332 0.0085 1.0000
12.500 1.3746 0.03348 0.02669 -0.0320 0.0083 1.0000
12.750 1.3838 0.03476 0.02802 -0.0307 0.0080 1.0000
13.000 1.3921 0.03615 0.02945 -0.0295 0.0078 1.0000
13.250 1.3990 0.03768 0.03103 -0.0283 0.0075 1.0000
13.500 1.4044 0.03939 0.03279 -0.0271 0.0072 1.0000
13.750 1.4096 0.04118 0.03464 -0.0259 0.0071 1.0000
14.000 1.4154 0.04296 0.03648 -0.0250 0.0070 1.0000
14.250 1.4204 0.04487 0.03845 -0.0241 0.0068 1.0000
14.500 1.4231 0.04705 0.04071 -0.0232 0.0067 1.0000
14.750 1.4270 0.04917 0.04289 -0.0225 0.0065 1.0000
15.000 1.4322 0.05121 0.04498 -0.0219 0.0062 1.0000
15.250 1.4312 0.05399 0.04784 -0.0213 0.0061 1.0000
15.500 1.4326 0.05657 0.05049 -0.0209 0.0060 1.0000
15.750 1.4307 0.05961 0.05361 -0.0206 0.0059 1.0000
16.000 1.4283 0.06276 0.05684 -0.0204 0.0058 1.0000
16.250 1.4240 0.06623 0.06041 -0.0204 0.0057 1.0000
16.500 1.4190 0.06989 0.06415 -0.0206 0.0057 1.0000
16.750 1.4103 0.07411 0.06847 -0.0209 0.0056 1.0000
17.000 1.3998 0.07866 0.07312 -0.0214 0.0054 1.0000
17.250 1.3895 0.08327 0.07783 -0.0221 0.0054 1.0000
17.500 1.3756 0.08851 0.08319 -0.0230 0.0054 1.0000
17.750 1.3581 0.09434 0.08914 -0.0241 0.0053 1.0000
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