GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 627 AIRFOIL (goe627-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.39 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe627-il-1000000.txt Download as CSV file: xf-goe627-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 627 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 -0.7881 0.07200 0.06952 -0.0744 1.0000 0.0181
-15.750 -0.8391 0.06090 0.05819 -0.0813 1.0000 0.0181
-15.500 -0.8697 0.05409 0.05121 -0.0850 1.0000 0.0181
-15.250 -0.8903 0.04744 0.04435 -0.0903 0.9992 0.0181
-15.000 -0.9020 0.04192 0.03859 -0.0953 0.9974 0.0183
-14.750 -0.9112 0.03746 0.03392 -0.0982 0.9954 0.0185
-14.500 -0.9040 0.03513 0.03151 -0.0997 0.9940 0.0186
-14.250 -0.8841 0.03443 0.03082 -0.1006 0.9929 0.0189
-14.000 -0.8793 0.03263 0.02892 -0.1002 0.9901 0.0190
-13.750 -0.8617 0.03194 0.02820 -0.1004 0.9881 0.0192
-13.500 -0.8478 0.03062 0.02679 -0.1005 0.9861 0.0194
-13.250 -0.8264 0.03005 0.02619 -0.1010 0.9847 0.0196
-13.000 -0.8098 0.02869 0.02471 -0.1012 0.9834 0.0199
-12.750 -0.7877 0.02787 0.02381 -0.1017 0.9824 0.0202
-12.500 -0.7843 0.02712 0.02296 -0.0982 0.9770 0.0205
-12.250 -0.7692 0.02604 0.02174 -0.0971 0.9741 0.0208
-12.000 -0.7469 0.02506 0.02062 -0.0972 0.9723 0.0211
-11.750 -0.7181 0.02425 0.01968 -0.0982 0.9710 0.0214
-11.500 -0.6921 0.02226 0.01755 -0.0994 0.9701 0.0220
-11.250 -0.6724 0.02154 0.01681 -0.0984 0.9667 0.0222
-11.000 -0.6530 0.02102 0.01625 -0.0971 0.9629 0.0225
-10.750 -0.6261 0.02054 0.01574 -0.0973 0.9612 0.0229
-10.500 -0.5969 0.02004 0.01521 -0.0980 0.9599 0.0233
-10.250 -0.5667 0.01939 0.01450 -0.0989 0.9588 0.0238
-10.000 -0.5345 0.01877 0.01380 -0.1001 0.9580 0.0244
-9.750 -0.5028 0.01816 0.01309 -0.1012 0.9570 0.0248
-9.500 -0.4705 0.01767 0.01251 -0.1023 0.9559 0.0251
-9.250 -0.4530 0.01656 0.01133 -0.1006 0.9519 0.0255
-9.000 -0.4319 0.01585 0.01062 -0.0994 0.9478 0.0259
-8.750 -0.4032 0.01535 0.01012 -0.0998 0.9453 0.0264
-8.500 -0.3726 0.01488 0.00963 -0.1004 0.9431 0.0270
-8.250 -0.3411 0.01443 0.00915 -0.1013 0.9408 0.0275
-8.000 -0.3210 0.01404 0.00873 -0.0996 0.9354 0.0280
-7.750 -0.2966 0.01360 0.00824 -0.0988 0.9297 0.0284
-7.500 -0.2663 0.01315 0.00774 -0.0992 0.9252 0.0288
-7.250 -0.2447 0.01286 0.00740 -0.0978 0.9189 0.0291
-7.000 -0.2243 0.01222 0.00674 -0.0963 0.9123 0.0296
-6.750 -0.1976 0.01163 0.00614 -0.0961 0.9068 0.0304
-6.500 -0.1806 0.01133 0.00582 -0.0937 0.8982 0.0308
-6.250 -0.1535 0.01099 0.00546 -0.0934 0.8917 0.0314
-6.000 -0.1338 0.01073 0.00517 -0.0916 0.8824 0.0318
-5.750 -0.1083 0.01043 0.00482 -0.0909 0.8737 0.0324
-5.500 -0.0868 0.01020 0.00455 -0.0894 0.8623 0.0328
-5.250 -0.0635 0.01000 0.00430 -0.0883 0.8504 0.0333
-5.000 -0.0404 0.00984 0.00407 -0.0871 0.8354 0.0339
-4.750 -0.0211 0.00952 0.00366 -0.0852 0.8173 0.0347
-4.500 -0.0005 0.00935 0.00342 -0.0834 0.7982 0.0354
-4.250 0.0203 0.00923 0.00323 -0.0818 0.7795 0.0362
-4.000 0.0407 0.00916 0.00306 -0.0800 0.7598 0.0370
-3.750 0.0606 0.00910 0.00291 -0.0781 0.7399 0.0378
-3.500 0.0810 0.00907 0.00278 -0.0763 0.7209 0.0386
-3.250 0.1005 0.00898 0.00262 -0.0744 0.7016 0.0400
-3.000 0.1201 0.00894 0.00251 -0.0725 0.6816 0.0418
-2.750 0.1401 0.00892 0.00242 -0.0706 0.6623 0.0439
-2.500 0.1601 0.00889 0.00233 -0.0688 0.6445 0.0476
-2.250 0.1795 0.00879 0.00224 -0.0669 0.6279 0.0628
-2.000 0.1942 0.00842 0.00212 -0.0641 0.6125 0.1451
-1.750 0.2099 0.00816 0.00204 -0.0616 0.5968 0.2155
-1.500 0.2263 0.00796 0.00201 -0.0592 0.5807 0.2855
-1.250 0.2443 0.00784 0.00198 -0.0571 0.5641 0.3348
-1.000 0.2598 0.00764 0.00195 -0.0545 0.5471 0.4058
-0.750 0.2730 0.00740 0.00193 -0.0514 0.5294 0.4956
-0.500 0.2827 0.00718 0.00193 -0.0475 0.5100 0.5869
-0.250 0.2922 0.00700 0.00194 -0.0435 0.4925 0.6660
0.000 0.3026 0.00690 0.00198 -0.0396 0.4740 0.7332
0.250 0.3157 0.00687 0.00205 -0.0362 0.4567 0.7865
0.500 0.3314 0.00691 0.00214 -0.0334 0.4403 0.8307
0.750 0.3505 0.00698 0.00225 -0.0314 0.4243 0.8681
1.000 0.3755 0.00709 0.00237 -0.0306 0.4091 0.8988
1.250 0.4106 0.00727 0.00252 -0.0321 0.3934 0.9237
1.500 0.4553 0.00753 0.00272 -0.0357 0.3772 0.9417
1.750 0.4910 0.00776 0.00287 -0.0375 0.3628 0.9518
2.000 0.5294 0.00800 0.00301 -0.0398 0.3491 0.9560
2.250 0.5698 0.00828 0.00320 -0.0427 0.3354 0.9607
2.500 0.6004 0.00851 0.00337 -0.0432 0.3253 0.9687
2.750 0.6394 0.00878 0.00357 -0.0457 0.3147 0.9713
3.000 0.6758 0.00907 0.00377 -0.0476 0.3041 0.9742
3.250 0.7100 0.00929 0.00394 -0.0490 0.2960 0.9782
3.500 0.7406 0.00955 0.00413 -0.0497 0.2871 0.9823
3.750 0.7793 0.00975 0.00428 -0.0522 0.2795 0.9838
4.000 0.8167 0.01001 0.00447 -0.0544 0.2714 0.9859
4.250 0.8516 0.01019 0.00462 -0.0561 0.2660 0.9881
4.500 0.8840 0.01038 0.00477 -0.0573 0.2607 0.9907
4.750 0.9138 0.01063 0.00497 -0.0580 0.2546 0.9933
5.000 0.9487 0.01077 0.00509 -0.0597 0.2507 0.9947
5.250 0.9828 0.01092 0.00521 -0.0613 0.2464 0.9964
5.500 1.0157 0.01113 0.00537 -0.0627 0.2411 0.9982
5.750 1.0487 0.01133 0.00555 -0.0641 0.2367 0.9996
6.000 1.0656 0.01141 0.00565 -0.0621 0.2346 1.0000
6.250 1.0740 0.01151 0.00575 -0.0584 0.2321 1.0000
6.500 1.0833 0.01163 0.00587 -0.0548 0.2296 1.0000
6.750 1.0942 0.01180 0.00603 -0.0516 0.2269 1.0000
7.000 1.1050 0.01202 0.00623 -0.0484 0.2238 1.0000
7.250 1.1184 0.01221 0.00642 -0.0457 0.2215 1.0000
7.500 1.1351 0.01235 0.00659 -0.0437 0.2200 1.0000
7.750 1.1513 0.01252 0.00678 -0.0416 0.2180 1.0000
8.000 1.1676 0.01271 0.00698 -0.0396 0.2160 1.0000
8.250 1.1839 0.01294 0.00721 -0.0376 0.2133 1.0000
8.500 1.1995 0.01322 0.00747 -0.0356 0.2106 1.0000
8.750 1.2134 0.01356 0.00781 -0.0333 0.2075 1.0000
9.000 1.2317 0.01378 0.00806 -0.0317 0.2061 1.0000
9.250 1.2508 0.01399 0.00830 -0.0304 0.2045 1.0000
9.500 1.2694 0.01423 0.00857 -0.0290 0.2027 1.0000
9.750 1.2875 0.01450 0.00885 -0.0276 0.2005 1.0000
10.000 1.3051 0.01480 0.00917 -0.0261 0.1983 1.0000
10.250 1.3218 0.01517 0.00954 -0.0246 0.1958 1.0000
10.500 1.3363 0.01564 0.01001 -0.0227 0.1927 1.0000
10.750 1.3564 0.01588 0.01029 -0.0218 0.1907 1.0000
11.000 1.3758 0.01616 0.01062 -0.0208 0.1888 1.0000
11.250 1.3940 0.01651 0.01098 -0.0196 0.1858 1.0000
11.500 1.4107 0.01693 0.01140 -0.0183 0.1822 1.0000
11.750 1.4250 0.01748 0.01194 -0.0167 0.1782 1.0000
12.000 1.4440 0.01782 0.01234 -0.0157 0.1764 1.0000
12.250 1.4624 0.01820 0.01275 -0.0148 0.1728 1.0000
12.500 1.4784 0.01871 0.01326 -0.0135 0.1688 1.0000
12.750 1.4918 0.01936 0.01391 -0.0120 0.1644 1.0000
13.000 1.5094 0.01981 0.01440 -0.0111 0.1603 1.0000
13.250 1.5231 0.02048 0.01506 -0.0098 0.1550 1.0000
13.500 1.5362 0.02121 0.01579 -0.0084 0.1495 1.0000
13.750 1.5482 0.02201 0.01660 -0.0070 0.1429 1.0000
14.000 1.5590 0.02291 0.01750 -0.0056 0.1371 1.0000
14.250 1.5674 0.02400 0.01856 -0.0040 0.1292 1.0000
14.500 1.5742 0.02522 0.01977 -0.0024 0.1211 1.0000
14.750 1.5794 0.02660 0.02113 -0.0008 0.1144 1.0000
15.000 1.5859 0.02793 0.02248 0.0006 0.1088 1.0000
15.250 1.5897 0.02953 0.02408 0.0020 0.1035 1.0000
15.500 1.5952 0.03106 0.02564 0.0031 0.0994 1.0000
15.750 1.5963 0.03299 0.02758 0.0044 0.0947 1.0000
16.000 1.6015 0.03467 0.02931 0.0053 0.0920 1.0000
16.250 1.6052 0.03653 0.03121 0.0061 0.0893 1.0000
16.500 1.6064 0.03867 0.03340 0.0068 0.0867 1.0000
16.750 1.6055 0.04109 0.03586 0.0075 0.0838 1.0000
17.000 1.6098 0.04307 0.03791 0.0078 0.0821 1.0000
17.250 1.6092 0.04560 0.04050 0.0082 0.0793 1.0000
17.500 1.6053 0.04854 0.04349 0.0084 0.0768 1.0000
17.750 1.6004 0.05165 0.04667 0.0084 0.0739 1.0000
18.000 1.5984 0.05454 0.04963 0.0083 0.0713 1.0000
18.250 1.5891 0.05834 0.05348 0.0081 0.0682 1.0000
18.500 1.5782 0.06241 0.05762 0.0076 0.0650 1.0000
18.750 1.5658 0.06676 0.06203 0.0069 0.0607 1.0000
19.000 1.5445 0.07237 0.06769 0.0058 0.0557 1.0000
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