GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 500,000 Max Cl/Cd: 84.38 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe645-il-500000-n5.txt Download as CSV file: xf-goe645-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.6664 0.11843 0.11529 -0.0428 1.0000 0.0205
-17.250 -0.6827 0.11164 0.10843 -0.0464 1.0000 0.0207
-17.000 -0.6890 0.10677 0.10355 -0.0490 1.0000 0.0211
-16.750 -0.7030 0.10063 0.09734 -0.0523 1.0000 0.0213
-16.500 -0.7155 0.09484 0.09148 -0.0554 1.0000 0.0216
-16.250 -0.7284 0.08914 0.08571 -0.0585 1.0000 0.0218
-16.000 -0.7405 0.08371 0.08022 -0.0615 1.0000 0.0221
-15.750 -0.7516 0.07863 0.07506 -0.0643 1.0000 0.0222
-15.500 -0.7640 0.07346 0.06982 -0.0671 1.0000 0.0226
-15.250 -0.7779 0.06843 0.06471 -0.0699 1.0000 0.0228
-15.000 -0.7932 0.06353 0.05974 -0.0726 1.0000 0.0230
-14.750 -0.8096 0.05867 0.05481 -0.0751 1.0000 0.0232
-14.500 -0.8278 0.05379 0.04985 -0.0776 1.0000 0.0233
-14.250 -0.8488 0.04879 0.04477 -0.0800 1.0000 0.0234
-14.000 -0.8739 0.04354 0.03944 -0.0824 1.0000 0.0235
-13.750 -0.9074 0.03735 0.03316 -0.0855 1.0000 0.0235
-13.500 -0.9434 0.03136 0.02697 -0.0881 1.0000 0.0234
-13.250 -0.9274 0.02919 0.02464 -0.0902 0.9975 0.0238
-13.000 -0.9027 0.02734 0.02267 -0.0929 0.9924 0.0243
-12.750 -0.8790 0.02580 0.02105 -0.0947 0.9865 0.0247
-12.500 -0.8506 0.02465 0.01984 -0.0966 0.9816 0.0253
-12.250 -0.8255 0.02363 0.01874 -0.0974 0.9732 0.0259
-12.000 -0.7990 0.02271 0.01774 -0.0982 0.9638 0.0266
-11.750 -0.7673 0.02178 0.01670 -0.1000 0.9548 0.0272
-11.500 -0.7323 0.02093 0.01572 -0.1022 0.9444 0.0279
-11.250 -0.6958 0.01990 0.01461 -0.1050 0.9322 0.0286
-11.000 -0.6561 0.01904 0.01368 -0.1081 0.9171 0.0294
-10.750 -0.6189 0.01836 0.01287 -0.1105 0.8961 0.0302
-10.500 -0.5897 0.01781 0.01217 -0.1111 0.8724 0.0309
-10.250 -0.5653 0.01738 0.01158 -0.1107 0.8492 0.0316
-10.000 -0.5423 0.01699 0.01103 -0.1098 0.8293 0.0322
-9.750 -0.5207 0.01651 0.01042 -0.1089 0.8122 0.0328
-9.500 -0.4990 0.01603 0.00984 -0.1079 0.7972 0.0335
-9.000 -0.4528 0.01529 0.00892 -0.1062 0.7711 0.0350
-8.750 -0.4289 0.01496 0.00849 -0.1054 0.7603 0.0358
-8.500 -0.4048 0.01464 0.00807 -0.1046 0.7496 0.0366
-8.250 -0.3802 0.01434 0.00767 -0.1039 0.7395 0.0372
-8.000 -0.3565 0.01397 0.00721 -0.1031 0.7296 0.0382
-7.750 -0.3317 0.01362 0.00681 -0.1025 0.7206 0.0393
-7.500 -0.3068 0.01334 0.00646 -0.1018 0.7116 0.0404
-7.250 -0.2812 0.01308 0.00612 -0.1012 0.7023 0.0414
-7.000 -0.2557 0.01285 0.00581 -0.1006 0.6930 0.0426
-6.750 -0.2300 0.01257 0.00547 -0.1001 0.6839 0.0439
-6.500 -0.2046 0.01231 0.00515 -0.0995 0.6750 0.0459
-6.250 -0.1784 0.01209 0.00487 -0.0990 0.6656 0.0481
-6.000 -0.1527 0.01188 0.00459 -0.0983 0.6556 0.0507
-5.750 -0.1267 0.01164 0.00431 -0.0978 0.6446 0.0545
-5.500 -0.1011 0.01138 0.00403 -0.0972 0.6344 0.0617
-5.250 -0.0759 0.01107 0.00383 -0.0967 0.6235 0.0865
-5.000 -0.0493 0.01095 0.00369 -0.0962 0.6125 0.0987
-4.750 -0.0227 0.01091 0.00356 -0.0957 0.6007 0.1050
-4.500 0.0035 0.01079 0.00341 -0.0952 0.5881 0.1113
-4.250 0.0300 0.01072 0.00328 -0.0947 0.5760 0.1162
-4.000 0.0567 0.01069 0.00317 -0.0942 0.5653 0.1193
-3.750 0.0831 0.01060 0.00305 -0.0937 0.5545 0.1241
-3.500 0.1097 0.01054 0.00294 -0.0933 0.5444 0.1293
-3.250 0.1358 0.01051 0.00285 -0.0927 0.5331 0.1358
-3.000 0.1622 0.01043 0.00277 -0.0923 0.5219 0.1454
-2.750 0.1884 0.01037 0.00270 -0.0918 0.5121 0.1585
-2.500 0.2145 0.01029 0.00267 -0.0913 0.5021 0.1816
-2.250 0.2409 0.01025 0.00266 -0.0908 0.4923 0.2043
-1.750 0.2938 0.01032 0.00264 -0.0899 0.4696 0.2264
-1.500 0.3199 0.01036 0.00264 -0.0893 0.4568 0.2342
-1.250 0.3460 0.01043 0.00264 -0.0888 0.4457 0.2413
-1.000 0.3730 0.01046 0.00264 -0.0884 0.4369 0.2473
-0.750 0.3994 0.01051 0.00266 -0.0879 0.4296 0.2538
-0.500 0.4265 0.01055 0.00267 -0.0876 0.4232 0.2598
-0.250 0.4532 0.01059 0.00269 -0.0872 0.4166 0.2657
0.000 0.4795 0.01065 0.00272 -0.0867 0.4105 0.2718
0.250 0.5066 0.01069 0.00275 -0.0864 0.4047 0.2782
0.500 0.5329 0.01074 0.00280 -0.0859 0.3981 0.2853
0.750 0.5592 0.01080 0.00285 -0.0854 0.3924 0.2910
1.000 0.5859 0.01086 0.00289 -0.0851 0.3858 0.2964
1.250 0.6118 0.01094 0.00295 -0.0845 0.3790 0.3019
1.500 0.6379 0.01100 0.00301 -0.0841 0.3724 0.3086
2.000 0.6893 0.01117 0.00317 -0.0830 0.3573 0.3267
2.500 0.7401 0.01135 0.00335 -0.0819 0.3420 0.3443
3.000 0.7901 0.01157 0.00356 -0.0806 0.3254 0.3644
3.250 0.8145 0.01168 0.00368 -0.0799 0.3158 0.3794
3.500 0.8382 0.01181 0.00383 -0.0791 0.3046 0.4002
3.750 0.8612 0.01194 0.00399 -0.0782 0.2939 0.4281
4.000 0.8840 0.01201 0.00417 -0.0773 0.2850 0.4752
4.250 0.9055 0.01205 0.00437 -0.0761 0.2762 0.5523
4.500 0.9249 0.01199 0.00456 -0.0745 0.2681 0.6538
5.000 1.0103 0.01206 0.00519 -0.0811 0.2497 1.0000
5.250 1.0325 0.01228 0.00538 -0.0800 0.2446 1.0000
5.500 1.0544 0.01251 0.00559 -0.0788 0.2393 1.0000
5.750 1.0754 0.01277 0.00581 -0.0776 0.2341 1.0000
6.000 1.0967 0.01302 0.00603 -0.0764 0.2297 1.0000
6.250 1.1181 0.01325 0.00626 -0.0752 0.2255 1.0000
6.500 1.1386 0.01351 0.00650 -0.0739 0.2213 1.0000
6.750 1.1576 0.01380 0.00677 -0.0723 0.2170 1.0000
7.000 1.1764 0.01406 0.00702 -0.0707 0.2135 1.0000
7.250 1.1947 0.01432 0.00728 -0.0690 0.2092 1.0000
7.500 1.2114 0.01465 0.00759 -0.0671 0.2036 1.0000
7.750 1.2281 0.01500 0.00792 -0.0652 0.1995 1.0000
8.000 1.2466 0.01528 0.00823 -0.0637 0.1953 1.0000
8.250 1.2642 0.01562 0.00856 -0.0620 0.1907 1.0000
8.750 1.2971 0.01642 0.00936 -0.0586 0.1792 1.0000
9.000 1.3106 0.01697 0.00986 -0.0566 0.1671 1.0000
9.250 1.3116 0.01816 0.01084 -0.0531 0.1348 1.0000
9.500 1.3224 0.01892 0.01157 -0.0510 0.1286 1.0000
9.750 1.3334 0.01971 0.01235 -0.0491 0.1239 1.0000
10.000 1.3467 0.02040 0.01308 -0.0475 0.1221 1.0000
10.250 1.3602 0.02112 0.01383 -0.0461 0.1208 1.0000
10.500 1.3729 0.02192 0.01467 -0.0447 0.1196 1.0000
10.750 1.3852 0.02279 0.01558 -0.0433 0.1186 1.0000
11.000 1.3973 0.02372 0.01656 -0.0420 0.1178 1.0000
11.250 1.4077 0.02479 0.01767 -0.0408 0.1166 1.0000
11.500 1.4163 0.02606 0.01899 -0.0395 0.1149 1.0000
11.750 1.4245 0.02742 0.02039 -0.0384 0.1132 1.0000
12.000 1.4309 0.02898 0.02199 -0.0373 0.1114 1.0000
12.250 1.4401 0.03036 0.02344 -0.0365 0.1105 1.0000
12.500 1.4500 0.03173 0.02488 -0.0358 0.1100 1.0000
12.750 1.4587 0.03324 0.02645 -0.0351 0.1093 1.0000
13.000 1.4666 0.03484 0.02813 -0.0344 0.1088 1.0000
13.250 1.4736 0.03656 0.02993 -0.0339 0.1082 1.0000
13.500 1.4794 0.03844 0.03188 -0.0333 0.1074 1.0000
13.750 1.4845 0.04041 0.03393 -0.0329 0.1065 1.0000
14.000 1.4880 0.04259 0.03619 -0.0325 0.1056 1.0000
14.250 1.4896 0.04503 0.03868 -0.0322 0.1043 1.0000
14.500 1.4905 0.04759 0.04132 -0.0319 0.1033 1.0000
14.750 1.4919 0.05015 0.04396 -0.0318 0.1028 1.0000
15.000 1.4878 0.05339 0.04727 -0.0318 0.1011 1.0000
15.250 1.4850 0.05655 0.05049 -0.0319 0.0999 1.0000
15.500 1.4823 0.05971 0.05373 -0.0320 0.0987 1.0000
15.750 1.4850 0.06231 0.05641 -0.0322 0.0979 1.0000
16.000 1.4888 0.06483 0.05903 -0.0324 0.0971 1.0000
16.250 1.4926 0.06734 0.06163 -0.0326 0.0958 1.0000
16.500 1.4945 0.07010 0.06448 -0.0329 0.0941 1.0000
16.750 1.4939 0.07317 0.06764 -0.0333 0.0928 1.0000
17.000 1.4922 0.07645 0.07098 -0.0338 0.0909 1.0000
17.250 1.4883 0.08002 0.07462 -0.0344 0.0894 1.0000
17.750 1.4846 0.08672 0.08147 -0.0357 0.0846 1.0000
18.000 1.4842 0.08993 0.08477 -0.0363 0.0802 1.0000
18.250 1.4701 0.09513 0.08993 -0.0377 0.0652 1.0000
18.500 1.4410 0.10253 0.09726 -0.0399 0.0533 1.0000
18.750 1.4230 0.10846 0.10322 -0.0417 0.0481 1.0000
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