GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.08 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe670-il-1000000.txt Download as CSV file: xf-goe670-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4313 0.13577 0.13397 -0.0283 1.0000 0.0176
-12.750 -0.4300 0.13168 0.12988 -0.0293 1.0000 0.0177
-12.500 -0.9432 0.03482 0.03257 -0.0762 0.9972 0.0173
-12.250 -0.9219 0.03154 0.02904 -0.0791 0.9952 0.0176
-12.000 -0.9123 0.02678 0.02388 -0.0812 0.9918 0.0183
-11.750 -0.8832 0.02637 0.02347 -0.0821 0.9899 0.0188
-11.500 -0.8534 0.02600 0.02308 -0.0832 0.9882 0.0192
-11.250 -0.8218 0.02591 0.02299 -0.0843 0.9870 0.0197
-11.000 -0.7915 0.02535 0.02236 -0.0855 0.9857 0.0203
-10.750 -0.7619 0.02446 0.02135 -0.0869 0.9846 0.0210
-10.500 -0.7316 0.02360 0.02036 -0.0883 0.9837 0.0215
-10.250 -0.7038 0.02322 0.01989 -0.0887 0.9814 0.0218
-10.000 -0.6899 0.02003 0.01632 -0.0885 0.9769 0.0227
-9.750 -0.6603 0.01952 0.01577 -0.0894 0.9753 0.0233
-9.500 -0.6288 0.01926 0.01551 -0.0905 0.9742 0.0238
-9.250 -0.5965 0.01901 0.01522 -0.0918 0.9732 0.0245
-9.000 -0.5649 0.01835 0.01446 -0.0931 0.9723 0.0252
-8.750 -0.5339 0.01764 0.01363 -0.0942 0.9712 0.0259
-8.500 -0.5058 0.01717 0.01306 -0.0945 0.9688 0.0264
-8.250 -0.4790 0.01700 0.01283 -0.0944 0.9650 0.0268
-8.000 -0.4558 0.01512 0.01065 -0.0943 0.9614 0.0275
-7.750 -0.4285 0.01405 0.00948 -0.0947 0.9588 0.0284
-7.500 -0.3980 0.01360 0.00898 -0.0955 0.9567 0.0291
-7.250 -0.3738 0.01329 0.00863 -0.0948 0.9522 0.0297
-7.000 -0.3478 0.01284 0.00811 -0.0945 0.9483 0.0303
-6.750 -0.3205 0.01236 0.00754 -0.0944 0.9449 0.0309
-6.500 -0.2913 0.01193 0.00704 -0.0948 0.9418 0.0316
-6.250 -0.2675 0.01157 0.00661 -0.0939 0.9368 0.0321
-6.000 -0.2416 0.01120 0.00618 -0.0934 0.9325 0.0326
-5.750 -0.2140 0.01084 0.00574 -0.0933 0.9285 0.0329
-5.500 -0.1883 0.01042 0.00525 -0.0928 0.9239 0.0333
-5.250 -0.1655 0.00963 0.00437 -0.0918 0.9189 0.0345
-5.000 -0.1393 0.00927 0.00397 -0.0915 0.9149 0.0355
-4.750 -0.1117 0.00903 0.00370 -0.0914 0.9112 0.0365
-4.500 -0.0864 0.00882 0.00348 -0.0907 0.9067 0.0375
-4.250 -0.0603 0.00859 0.00322 -0.0903 0.9022 0.0384
-4.000 -0.0329 0.00839 0.00298 -0.0900 0.8981 0.0394
-3.750 -0.0065 0.00823 0.00279 -0.0896 0.8934 0.0402
-3.500 0.0186 0.00795 0.00247 -0.0889 0.8872 0.0418
-3.250 0.0456 0.00772 0.00221 -0.0886 0.8814 0.0445
-3.000 0.0709 0.00757 0.00206 -0.0879 0.8746 0.0471
-2.750 0.0979 0.00746 0.00191 -0.0875 0.8684 0.0493
-2.500 0.1236 0.00726 0.00174 -0.0870 0.8619 0.0563
-2.250 0.1497 0.00712 0.00160 -0.0864 0.8538 0.0641
-2.000 0.1755 0.00701 0.00152 -0.0858 0.8441 0.0744
-1.750 0.2019 0.00696 0.00146 -0.0854 0.8345 0.0839
-1.500 0.2277 0.00688 0.00139 -0.0848 0.8225 0.0925
-1.250 0.2535 0.00687 0.00134 -0.0842 0.8084 0.0979
-1.000 0.2787 0.00682 0.00126 -0.0834 0.7922 0.1046
-0.750 0.3039 0.00681 0.00121 -0.0827 0.7740 0.1107
-0.500 0.3290 0.00682 0.00116 -0.0820 0.7529 0.1148
-0.250 0.3531 0.00682 0.00111 -0.0810 0.7289 0.1222
0.000 0.3766 0.00689 0.00108 -0.0800 0.7008 0.1281
0.250 0.3997 0.00695 0.00107 -0.0789 0.6744 0.1401
1.000 0.4645 0.00620 0.00119 -0.0752 0.6310 0.5147
1.250 0.4815 0.00519 0.00138 -0.0726 0.6215 0.9322
1.500 0.5422 0.00539 0.00152 -0.0799 0.6071 0.9715
1.750 0.5791 0.00557 0.00163 -0.0818 0.5922 0.9832
2.000 0.6242 0.00573 0.00172 -0.0856 0.5733 0.9892
2.250 0.6628 0.00592 0.00180 -0.0880 0.5481 0.9943
2.500 0.7039 0.00617 0.00185 -0.0910 0.4987 0.9981
2.750 0.7323 0.00664 0.00199 -0.0914 0.4281 1.0000
3.000 0.7491 0.00702 0.00214 -0.0892 0.3805 1.0000
3.250 0.7671 0.00736 0.00229 -0.0872 0.3390 1.0000
3.500 0.7853 0.00769 0.00244 -0.0853 0.3017 1.0000
4.000 0.8249 0.00821 0.00275 -0.0820 0.2586 1.0000
4.500 0.8666 0.00863 0.00306 -0.0791 0.2336 1.0000
4.750 0.8878 0.00883 0.00321 -0.0778 0.2226 1.0000
5.000 0.9090 0.00903 0.00337 -0.0764 0.2137 1.0000
5.250 0.9312 0.00919 0.00352 -0.0752 0.2074 1.0000
5.500 0.9524 0.00940 0.00370 -0.0739 0.1999 1.0000
5.750 0.9747 0.00955 0.00384 -0.0727 0.1925 1.0000
6.000 0.9961 0.00976 0.00402 -0.0714 0.1833 1.0000
6.250 1.0176 0.00996 0.00419 -0.0702 0.1736 1.0000
6.500 1.0389 0.01018 0.00438 -0.0689 0.1619 1.0000
6.750 1.0580 0.01054 0.00462 -0.0672 0.1391 1.0000
7.000 1.0701 0.01133 0.00509 -0.0644 0.0903 1.0000
7.250 1.0850 0.01196 0.00558 -0.0620 0.0634 1.0000
7.500 1.0963 0.01286 0.00625 -0.0590 0.0284 1.0000
7.750 1.1139 0.01334 0.00672 -0.0571 0.0236 1.0000
8.000 1.1329 0.01372 0.00712 -0.0555 0.0215 1.0000
8.250 1.1494 0.01426 0.00768 -0.0534 0.0190 1.0000
8.500 1.1686 0.01459 0.00804 -0.0518 0.0181 1.0000
8.750 1.1858 0.01497 0.00846 -0.0499 0.0171 1.0000
9.000 1.2015 0.01540 0.00891 -0.0477 0.0163 1.0000
9.250 1.2139 0.01603 0.00958 -0.0449 0.0152 1.0000
9.500 1.2279 0.01659 0.01019 -0.0425 0.0146 1.0000
9.750 1.2438 0.01704 0.01068 -0.0405 0.0142 1.0000
10.000 1.2598 0.01750 0.01120 -0.0386 0.0136 1.0000
10.250 1.2742 0.01807 0.01180 -0.0364 0.0131 1.0000
10.500 1.2895 0.01859 0.01235 -0.0345 0.0125 1.0000
10.750 1.3006 0.01937 0.01317 -0.0321 0.0120 1.0000
11.000 1.3030 0.02069 0.01461 -0.0284 0.0115 1.0000
11.250 1.3193 0.02117 0.01514 -0.0269 0.0112 1.0000
11.500 1.3308 0.02197 0.01600 -0.0248 0.0111 1.0000
11.750 1.3418 0.02281 0.01691 -0.0227 0.0108 1.0000
12.000 1.3525 0.02369 0.01786 -0.0207 0.0105 1.0000
12.250 1.3606 0.02476 0.01900 -0.0185 0.0104 1.0000
12.500 1.3694 0.02583 0.02014 -0.0165 0.0101 1.0000
12.750 1.3783 0.02692 0.02129 -0.0146 0.0099 1.0000
13.000 1.3865 0.02809 0.02252 -0.0129 0.0096 1.0000
13.250 1.3925 0.02946 0.02396 -0.0111 0.0094 1.0000
13.500 1.3926 0.03135 0.02592 -0.0090 0.0090 1.0000
13.750 1.3871 0.03384 0.02852 -0.0068 0.0088 1.0000
14.000 1.3818 0.03645 0.03125 -0.0049 0.0087 1.0000
14.250 1.3835 0.03856 0.03346 -0.0037 0.0086 1.0000
14.500 1.3883 0.04044 0.03543 -0.0030 0.0085 1.0000
14.750 1.3899 0.04272 0.03782 -0.0023 0.0084 1.0000
15.000 1.3945 0.04484 0.04003 -0.0019 0.0082 1.0000
15.250 1.3920 0.04779 0.04309 -0.0016 0.0082 1.0000
15.500 1.3893 0.05090 0.04631 -0.0016 0.0081 1.0000
15.750 1.3847 0.05439 0.04992 -0.0018 0.0080 1.0000
16.000 1.3856 0.05737 0.05298 -0.0023 0.0078 1.0000
16.250 1.3792 0.06129 0.05701 -0.0030 0.0077 1.0000
16.500 1.3731 0.06532 0.06116 -0.0039 0.0076 1.0000
16.750 1.3630 0.06999 0.06595 -0.0050 0.0076 1.0000
17.000 1.3575 0.07432 0.07038 -0.0065 0.0075 1.0000
17.250 1.3457 0.07950 0.07568 -0.0082 0.0075 1.0000
17.500 1.3378 0.08453 0.08081 -0.0103 0.0073 1.0000
17.750 1.3272 0.08990 0.08629 -0.0124 0.0073 1.0000
18.000 1.3147 0.09570 0.09221 -0.0147 0.0073 1.0000
18.250 1.3047 0.10130 0.09790 -0.0173 0.0072 1.0000
18.500 1.2901 0.10755 0.10428 -0.0199 0.0072 1.0000
18.750 1.2816 0.11310 0.10991 -0.0226 0.0071 1.0000
19.000 1.2673 0.11952 0.11645 -0.0256 0.0071 1.0000
19.250 1.2529 0.12611 0.12315 -0.0288 0.0071 1.0000
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