GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 367 AIRFOIL (goe367-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.26 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe367-il-1000000.txt Download as CSV file: xf-goe367-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 367 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9174 0.04620 0.04328 -0.1083 1.0000 0.0290
-15.750 -0.9365 0.04050 0.03741 -0.1127 1.0000 0.0291
-15.500 -0.9502 0.03750 0.03431 -0.1128 1.0000 0.0292
-15.250 -0.9463 0.03523 0.03194 -0.1140 0.9972 0.0294
-15.000 -0.9317 0.03329 0.02990 -0.1160 0.9940 0.0296
-14.750 -0.9190 0.03158 0.02810 -0.1170 0.9878 0.0298
-14.500 -0.9052 0.02999 0.02639 -0.1176 0.9812 0.0301
-14.250 -0.8990 0.02864 0.02491 -0.1162 0.9696 0.0303
-14.000 -0.8948 0.02751 0.02365 -0.1137 0.9575 0.0305
-13.750 -0.8891 0.02652 0.02254 -0.1110 0.9468 0.0307
-13.250 -0.8687 0.02474 0.02051 -0.1068 0.9282 0.0311
-13.000 -0.8545 0.02393 0.01955 -0.1051 0.9200 0.0313
-12.750 -0.8377 0.02315 0.01866 -0.1039 0.9115 0.0316
-12.250 -0.8003 0.02188 0.01715 -0.1017 0.8951 0.0319
-12.000 -0.7863 0.02053 0.01562 -0.1001 0.8868 0.0323
-11.750 -0.7676 0.01962 0.01463 -0.0991 0.8792 0.0327
-11.500 -0.7459 0.01910 0.01405 -0.0984 0.8714 0.0331
-11.250 -0.7231 0.01863 0.01353 -0.0977 0.8642 0.0334
-11.000 -0.7000 0.01818 0.01301 -0.0972 0.8565 0.0337
-10.750 -0.6768 0.01773 0.01247 -0.0965 0.8495 0.0341
-10.500 -0.6528 0.01727 0.01195 -0.0961 0.8427 0.0344
-10.250 -0.6289 0.01684 0.01142 -0.0956 0.8354 0.0348
-10.000 -0.6046 0.01640 0.01090 -0.0951 0.8280 0.0352
-9.750 -0.5800 0.01600 0.01041 -0.0946 0.8201 0.0356
-9.500 -0.5550 0.01564 0.00995 -0.0942 0.8130 0.0359
-9.250 -0.5293 0.01530 0.00955 -0.0939 0.8069 0.0362
-9.000 -0.5048 0.01479 0.00894 -0.0935 0.8009 0.0366
-8.750 -0.4813 0.01413 0.00823 -0.0929 0.7953 0.0373
-8.500 -0.4552 0.01380 0.00789 -0.0927 0.7901 0.0379
-8.250 -0.4289 0.01353 0.00758 -0.0925 0.7847 0.0384
-8.000 -0.4026 0.01327 0.00726 -0.0923 0.7795 0.0390
-7.750 -0.3758 0.01299 0.00695 -0.0922 0.7750 0.0396
-7.500 -0.3490 0.01272 0.00664 -0.0920 0.7701 0.0402
-7.250 -0.3221 0.01249 0.00635 -0.0919 0.7653 0.0407
-7.000 -0.2950 0.01231 0.00610 -0.0917 0.7605 0.0412
-6.750 -0.2695 0.01181 0.00559 -0.0914 0.7564 0.0420
-6.500 -0.2429 0.01150 0.00527 -0.0912 0.7517 0.0429
-6.250 -0.2158 0.01130 0.00504 -0.0911 0.7472 0.0437
-6.000 -0.1885 0.01114 0.00484 -0.0910 0.7425 0.0446
-5.750 -0.1607 0.01095 0.00464 -0.0910 0.7384 0.0456
-5.500 -0.1328 0.01081 0.00446 -0.0910 0.7338 0.0464
-5.250 -0.1064 0.01051 0.00413 -0.0908 0.7292 0.0476
-5.000 -0.0795 0.01029 0.00389 -0.0906 0.7243 0.0489
-4.750 -0.0517 0.01011 0.00371 -0.0906 0.7196 0.0502
-4.500 -0.0242 0.00996 0.00354 -0.0906 0.7134 0.0515
-4.250 0.0033 0.00988 0.00339 -0.0905 0.7069 0.0526
-4.000 0.0304 0.00961 0.00314 -0.0904 0.7013 0.0549
-3.750 0.0580 0.00946 0.00299 -0.0903 0.6957 0.0570
-3.500 0.0855 0.00938 0.00286 -0.0902 0.6900 0.0589
-3.250 0.1132 0.00919 0.00269 -0.0902 0.6851 0.0620
-3.000 0.1409 0.00906 0.00257 -0.0902 0.6794 0.0655
-2.750 0.1682 0.00894 0.00245 -0.0901 0.6736 0.0711
-2.500 0.1959 0.00880 0.00237 -0.0901 0.6678 0.0829
-2.250 0.2235 0.00869 0.00233 -0.0901 0.6609 0.0993
-2.000 0.2511 0.00867 0.00230 -0.0900 0.6538 0.1091
-1.750 0.2793 0.00860 0.00227 -0.0901 0.6466 0.1168
-1.500 0.3069 0.00860 0.00223 -0.0901 0.6387 0.1223
-1.250 0.3348 0.00854 0.00220 -0.0901 0.6309 0.1289
-1.000 0.3622 0.00856 0.00217 -0.0900 0.6217 0.1331
-0.750 0.3899 0.00853 0.00214 -0.0900 0.6125 0.1387
-0.500 0.4166 0.00853 0.00212 -0.0898 0.6021 0.1451
-0.250 0.4441 0.00854 0.00210 -0.0898 0.5910 0.1498
0.000 0.4707 0.00854 0.00210 -0.0896 0.5801 0.1594
0.500 0.5233 0.00853 0.00211 -0.0891 0.5578 0.1927
0.750 0.5467 0.00823 0.00213 -0.0885 0.5473 0.3175
1.000 0.5669 0.00765 0.00217 -0.0874 0.5368 0.5421
1.250 0.5801 0.00684 0.00232 -0.0844 0.5284 0.8518
1.500 0.6029 0.00697 0.00249 -0.0831 0.5190 0.8970
1.750 0.6266 0.00710 0.00262 -0.0821 0.5104 0.9189
2.000 0.6479 0.00729 0.00277 -0.0805 0.5005 0.9342
2.250 0.6698 0.00742 0.00289 -0.0790 0.4917 0.9453
2.500 0.6915 0.00760 0.00300 -0.0777 0.4818 0.9534
2.750 0.7155 0.00770 0.00309 -0.0767 0.4735 0.9597
3.250 0.7652 0.00799 0.00330 -0.0754 0.4571 0.9718
3.750 0.8199 0.00831 0.00353 -0.0754 0.4397 0.9809
4.000 0.8582 0.00857 0.00372 -0.0779 0.4295 0.9834
4.250 0.8964 0.00876 0.00387 -0.0804 0.4199 0.9848
4.500 0.9284 0.00897 0.00402 -0.0816 0.4102 0.9862
4.750 0.9630 0.00918 0.00418 -0.0834 0.4004 0.9881
5.000 1.0024 0.00943 0.00439 -0.0861 0.3919 0.9914
5.250 1.0352 0.00965 0.00456 -0.0875 0.3837 0.9933
5.500 1.0651 0.00983 0.00471 -0.0883 0.3767 0.9941
5.750 1.0952 0.01000 0.00487 -0.0892 0.3698 0.9951
6.000 1.1240 0.01025 0.00506 -0.0898 0.3622 0.9964
6.250 1.1532 0.01042 0.00522 -0.0905 0.3556 0.9976
6.500 1.1807 0.01066 0.00543 -0.0909 0.3487 0.9989
6.750 1.2083 0.01086 0.00562 -0.0913 0.3436 1.0000
7.000 1.2079 0.01093 0.00571 -0.0857 0.3401 1.0000
7.250 1.1988 0.01097 0.00577 -0.0784 0.3368 1.0000
7.500 1.2050 0.01115 0.00594 -0.0744 0.3324 1.0000
7.750 1.2228 0.01137 0.00616 -0.0728 0.3280 1.0000
8.000 1.2434 0.01160 0.00639 -0.0718 0.3231 1.0000
8.250 1.2629 0.01191 0.00669 -0.0707 0.3174 1.0000
8.500 1.2828 0.01224 0.00701 -0.0697 0.3122 1.0000
8.750 1.3041 0.01252 0.00730 -0.0689 0.3063 1.0000
9.000 1.3221 0.01296 0.00770 -0.0677 0.2982 1.0000
9.250 1.3428 0.01330 0.00805 -0.0670 0.2910 1.0000
9.500 1.3598 0.01382 0.00852 -0.0657 0.2813 1.0000
9.750 1.3782 0.01429 0.00897 -0.0646 0.2699 1.0000
10.000 1.3908 0.01507 0.00964 -0.0628 0.2501 1.0000
10.250 1.3884 0.01668 0.01098 -0.0592 0.2012 1.0000
10.500 1.3814 0.01867 0.01272 -0.0552 0.1640 1.0000
10.750 1.3895 0.01986 0.01385 -0.0532 0.1511 1.0000
11.000 1.4007 0.02089 0.01486 -0.0518 0.1404 1.0000
11.250 1.4086 0.02216 0.01606 -0.0500 0.1251 1.0000
11.500 1.4050 0.02425 0.01796 -0.0472 0.0944 1.0000
11.750 1.4117 0.02571 0.01939 -0.0456 0.0874 1.0000
12.000 1.4200 0.02708 0.02077 -0.0442 0.0840 1.0000
12.250 1.4289 0.02845 0.02216 -0.0430 0.0806 1.0000
12.500 1.4408 0.02963 0.02340 -0.0421 0.0792 1.0000
12.750 1.4515 0.03094 0.02475 -0.0412 0.0777 1.0000
13.000 1.4604 0.03240 0.02625 -0.0402 0.0760 1.0000
13.250 1.4672 0.03408 0.02797 -0.0391 0.0742 1.0000
13.500 1.4725 0.03593 0.02986 -0.0380 0.0721 1.0000
13.750 1.4806 0.03758 0.03156 -0.0372 0.0706 1.0000
14.000 1.4914 0.03901 0.03305 -0.0366 0.0694 1.0000
14.250 1.5008 0.04057 0.03466 -0.0360 0.0679 1.0000
14.500 1.5072 0.04245 0.03659 -0.0353 0.0661 1.0000
14.750 1.5111 0.04460 0.03877 -0.0345 0.0641 1.0000
15.000 1.5147 0.04683 0.04105 -0.0338 0.0621 1.0000
15.250 1.5248 0.04846 0.04273 -0.0335 0.0603 1.0000
15.500 1.5307 0.05048 0.04479 -0.0330 0.0577 1.0000
15.750 1.5323 0.05301 0.04733 -0.0325 0.0548 1.0000
16.000 1.5375 0.05521 0.04959 -0.0321 0.0517 1.0000
16.250 1.5372 0.05803 0.05241 -0.0317 0.0478 1.0000
16.500 1.5368 0.06090 0.05530 -0.0314 0.0438 1.0000
16.750 1.5337 0.06410 0.05853 -0.0311 0.0406 1.0000
17.000 1.5290 0.06755 0.06201 -0.0309 0.0379 1.0000
17.250 1.5244 0.07105 0.06556 -0.0308 0.0358 1.0000
17.500 1.5195 0.07464 0.06920 -0.0308 0.0342 1.0000
17.750 1.5121 0.07854 0.07315 -0.0309 0.0327 1.0000
18.000 1.5077 0.08211 0.07680 -0.0311 0.0315 1.0000
18.250 1.5039 0.08564 0.08039 -0.0313 0.0305 1.0000
18.500 1.4975 0.08957 0.08438 -0.0317 0.0295 1.0000
18.750 1.4895 0.09371 0.08858 -0.0321 0.0286 1.0000
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