GOE 15K AIRFOIL (goe15k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 15K AIRFOIL (goe15k-il) Reynolds number: 200,000 Max Cl/Cd: 49.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe15k-il-200000-n5.txt Download as CSV file: xf-goe15k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15K 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5679 0.08895 0.08486 -0.1095 0.9599 0.0233
-14.500 -0.6195 0.07512 0.07090 -0.1185 0.9583 0.0226
-14.250 -0.6639 0.06322 0.05874 -0.1271 0.9556 0.0222
-14.000 -0.6958 0.05601 0.05129 -0.1306 0.9498 0.0222
-13.750 -0.7153 0.05044 0.04544 -0.1337 0.9469 0.0224
-13.500 -0.7248 0.04667 0.04141 -0.1347 0.9451 0.0226
-13.250 -0.7515 0.04413 0.03865 -0.1297 0.9375 0.0230
-13.000 -0.7577 0.04167 0.03593 -0.1278 0.9348 0.0233
-12.750 -0.7572 0.03974 0.03387 -0.1261 0.9330 0.0237
-12.500 -0.7703 0.03881 0.03287 -0.1204 0.9267 0.0241
-12.250 -0.7688 0.03773 0.03165 -0.1174 0.9234 0.0246
-12.000 -0.7604 0.03678 0.03059 -0.1154 0.9212 0.0256
-11.750 -0.7502 0.03568 0.02932 -0.1136 0.9196 0.0267
-11.500 -0.7600 0.03504 0.02853 -0.1073 0.9135 0.0277
-11.250 -0.7590 0.03389 0.02714 -0.1033 0.9100 0.0286
-11.000 -0.7509 0.03304 0.02620 -0.1004 0.9077 0.0297
-10.750 -0.7384 0.03241 0.02548 -0.0984 0.9062 0.0306
-10.500 -0.7222 0.03211 0.02510 -0.0967 0.9050 0.0322
-10.250 -0.7386 0.03198 0.02487 -0.0883 0.8979 0.0326
-10.000 -0.7308 0.03154 0.02425 -0.0848 0.8949 0.0347
-9.750 -0.7169 0.03066 0.02315 -0.0826 0.8930 0.0363
-9.500 -0.7028 0.03018 0.02261 -0.0804 0.8914 0.0377
-9.250 -0.6867 0.02990 0.02226 -0.0785 0.8902 0.0395
-9.000 -0.7020 0.03017 0.02246 -0.0700 0.8837 0.0403
-8.750 -0.6936 0.02979 0.02194 -0.0664 0.8807 0.0422
-8.500 -0.6790 0.02942 0.02134 -0.0640 0.8788 0.0447
-8.250 -0.6610 0.02873 0.02054 -0.0625 0.8774 0.0465
-8.000 -0.6423 0.02832 0.02010 -0.0611 0.8761 0.0486
-7.750 -0.6205 0.02789 0.01957 -0.0602 0.8752 0.0510
-7.500 -0.5961 0.02735 0.01888 -0.0598 0.8744 0.0535
-7.250 -0.6179 0.02781 0.01927 -0.0499 0.8667 0.0541
-7.000 -0.6035 0.02770 0.01899 -0.0473 0.8645 0.0558
-6.750 -0.5813 0.02689 0.01817 -0.0467 0.8632 0.0582
-6.500 -0.5601 0.02647 0.01771 -0.0457 0.8619 0.0604
-6.250 -0.5365 0.02608 0.01726 -0.0452 0.8608 0.0631
-6.000 -0.5104 0.02565 0.01673 -0.0451 0.8599 0.0653
-5.750 -0.4835 0.02523 0.01621 -0.0451 0.8592 0.0671
-5.500 -0.4953 0.02571 0.01663 -0.0373 0.8535 0.0679
-5.250 -0.4819 0.02542 0.01630 -0.0347 0.8506 0.0694
-5.000 -0.4612 0.02501 0.01587 -0.0335 0.8486 0.0712
-4.750 -0.4390 0.02468 0.01552 -0.0327 0.8472 0.0729
-4.500 -0.4154 0.02440 0.01520 -0.0321 0.8460 0.0754
-4.250 -0.3906 0.02417 0.01491 -0.0317 0.8449 0.0777
-4.000 -0.3638 0.02391 0.01459 -0.0317 0.8441 0.0801
-3.750 -0.3350 0.02363 0.01425 -0.0321 0.8433 0.0821
-3.500 -0.3460 0.02411 0.01471 -0.0245 0.8365 0.0830
-3.250 -0.3257 0.02397 0.01457 -0.0233 0.8338 0.0866
-3.000 -0.2998 0.02379 0.01438 -0.0232 0.8321 0.0915
-2.750 -0.2709 0.02355 0.01417 -0.0237 0.8308 0.1002
-2.500 -0.2390 0.02319 0.01397 -0.0249 0.8297 0.1267
-2.250 -0.2069 0.02278 0.01379 -0.0263 0.8288 0.1811
-2.000 -0.1759 0.02246 0.01367 -0.0274 0.8280 0.2306
-1.750 -0.1453 0.02219 0.01355 -0.0283 0.8272 0.2730
-1.500 -0.1544 0.02277 0.01419 -0.0213 0.8190 0.2892
-1.250 -0.1314 0.02268 0.01424 -0.0207 0.8168 0.3286
-0.750 0.1630 0.02252 0.01640 -0.0737 0.8301 0.8838
-0.500 0.1946 0.02294 0.01678 -0.0743 0.8291 0.9186
-0.250 0.2208 0.02335 0.01714 -0.0738 0.8281 0.9436
0.000 0.2586 0.02374 0.01748 -0.0760 0.8274 0.9565
0.250 0.3056 0.02418 0.01789 -0.0802 0.8271 0.9677
0.500 0.3509 0.02448 0.01815 -0.0842 0.8268 0.9759
0.750 0.4034 0.02440 0.01806 -0.0898 0.8264 0.9814
1.750 0.5482 0.02480 0.01849 -0.0993 0.8136 1.0000
2.000 0.5795 0.02440 0.01809 -0.1001 0.8124 1.0000
2.250 0.6098 0.02408 0.01778 -0.1007 0.8114 1.0000
2.500 0.6411 0.02372 0.01744 -0.1015 0.8105 1.0000
3.250 0.6718 0.02447 0.01828 -0.0917 0.7921 1.0000
3.750 0.7185 0.02370 0.01758 -0.0897 0.7817 1.0000
4.750 0.7941 0.02232 0.01634 -0.0816 0.7477 1.0000
5.250 0.7896 0.02368 0.01777 -0.0704 0.7117 1.0000
5.500 0.8121 0.02309 0.01718 -0.0688 0.6876 1.0000
5.750 0.8722 0.02091 0.01491 -0.0736 0.6500 1.0000
6.000 0.9386 0.01913 0.01261 -0.0801 0.5659 1.0000
6.250 0.9367 0.01993 0.01299 -0.0744 0.4896 1.0000
6.500 0.9269 0.02107 0.01379 -0.0674 0.4387 1.0000
6.750 0.9249 0.02204 0.01456 -0.0622 0.4040 1.0000
7.000 0.9281 0.02286 0.01527 -0.0580 0.3738 1.0000
7.250 0.9313 0.02373 0.01599 -0.0539 0.3370 1.0000
7.500 0.9343 0.02466 0.01675 -0.0499 0.2966 1.0000
7.750 0.9355 0.02574 0.01758 -0.0457 0.2508 1.0000
8.000 0.9406 0.02669 0.01835 -0.0423 0.2175 1.0000
8.250 0.9482 0.02756 0.01910 -0.0393 0.1915 1.0000
8.500 0.9570 0.02839 0.01983 -0.0366 0.1709 1.0000
8.750 0.9671 0.02916 0.02054 -0.0341 0.1518 1.0000
9.000 0.9772 0.02997 0.02126 -0.0317 0.1316 1.0000
9.250 0.9883 0.03071 0.02196 -0.0294 0.1179 1.0000
9.500 0.9998 0.03148 0.02270 -0.0272 0.1060 1.0000
9.750 1.0104 0.03230 0.02348 -0.0250 0.0958 1.0000
10.000 1.0228 0.03303 0.02424 -0.0230 0.0880 1.0000
10.250 1.0336 0.03387 0.02506 -0.0209 0.0811 1.0000
10.500 1.0457 0.03464 0.02586 -0.0190 0.0738 1.0000
10.750 1.0566 0.03551 0.02676 -0.0169 0.0692 1.0000
11.000 1.0679 0.03635 0.02763 -0.0150 0.0624 1.0000
11.250 1.0792 0.03721 0.02853 -0.0131 0.0575 1.0000
11.500 1.0893 0.03818 0.02952 -0.0111 0.0515 1.0000
11.750 1.1004 0.03908 0.03050 -0.0092 0.0464 1.0000
12.000 1.1104 0.04008 0.03156 -0.0073 0.0429 1.0000
12.250 1.1193 0.04119 0.03269 -0.0053 0.0388 1.0000
12.500 1.1293 0.04221 0.03376 -0.0035 0.0348 1.0000
12.750 1.1357 0.04354 0.03510 -0.0014 0.0322 1.0000
13.000 1.1432 0.04482 0.03648 0.0007 0.0301 1.0000
13.250 1.1500 0.04616 0.03791 0.0027 0.0289 1.0000
13.500 1.1565 0.04754 0.03934 0.0045 0.0268 1.0000
13.750 1.1587 0.04933 0.04118 0.0067 0.0252 1.0000
14.000 1.1649 0.05079 0.04277 0.0085 0.0243 1.0000
14.250 1.1704 0.05233 0.04443 0.0103 0.0236 1.0000
14.500 1.1738 0.05411 0.04632 0.0121 0.0224 1.0000
14.750 1.1768 0.05596 0.04827 0.0139 0.0221 1.0000
15.000 1.1774 0.05809 0.05048 0.0156 0.0210 1.0000
15.250 1.1778 0.06026 0.05272 0.0172 0.0204 1.0000
15.500 1.1776 0.06258 0.05515 0.0188 0.0200 1.0000
15.750 1.1787 0.06480 0.05752 0.0201 0.0195 1.0000
16.000 1.1799 0.06709 0.05996 0.0213 0.0185 1.0000
16.250 1.1784 0.06972 0.06272 0.0224 0.0180 1.0000
16.500 1.1782 0.07225 0.06539 0.0232 0.0177 1.0000
16.750 1.1740 0.07535 0.06861 0.0241 0.0173 1.0000
17.000 1.1700 0.07850 0.07183 0.0245 0.0166 1.0000
17.250 1.1672 0.08154 0.07501 0.0250 0.0167 1.0000
17.500 1.1610 0.08510 0.07866 0.0253 0.0164 1.0000
17.750 1.1554 0.08870 0.08239 0.0253 0.0163 1.0000
18.000 1.1497 0.09243 0.08628 0.0251 0.0161 1.0000
18.250 1.1392 0.09712 0.09123 0.0244 0.0155 1.0000
18.500 1.1344 0.10084 0.09505 0.0238 0.0158 1.0000
18.750 1.1228 0.10597 0.10040 0.0223 0.0153 1.0000
19.000 1.1128 0.11090 0.10549 0.0208 0.0152 1.0000
19.250 1.0999 0.11642 0.11119 0.0190 0.0151 1.0000
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