GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.85 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe564-il-1000000.txt Download as CSV file: xf-goe564-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 564 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3615 0.12195 0.12029 -0.0261 1.0000 0.0146
-12.000 -0.9416 0.03566 0.03342 -0.0643 1.0000 0.0095
-11.750 -0.9541 0.03133 0.02879 -0.0621 1.0000 0.0095
-11.500 -0.9515 0.02896 0.02620 -0.0599 1.0000 0.0097
-11.250 -0.9459 0.02695 0.02397 -0.0577 1.0000 0.0098
-11.000 -0.9340 0.02571 0.02258 -0.0559 1.0000 0.0100
-10.750 -0.9267 0.02185 0.01826 -0.0552 0.9990 0.0105
-10.500 -0.8989 0.02068 0.01698 -0.0563 0.9976 0.0110
-10.250 -0.8691 0.01993 0.01614 -0.0574 0.9963 0.0113
-10.000 -0.8388 0.01922 0.01533 -0.0585 0.9951 0.0118
-9.750 -0.8083 0.01847 0.01446 -0.0597 0.9942 0.0124
-9.500 -0.7815 0.01764 0.01348 -0.0600 0.9922 0.0128
-9.250 -0.7514 0.01724 0.01299 -0.0607 0.9904 0.0132
-9.000 -0.7238 0.01589 0.01149 -0.0616 0.9884 0.0142
-8.750 -0.6909 0.01571 0.01130 -0.0628 0.9870 0.0149
-8.500 -0.6580 0.01537 0.01092 -0.0641 0.9858 0.0157
-8.250 -0.6251 0.01492 0.01037 -0.0654 0.9848 0.0165
-8.000 -0.5910 0.01465 0.01002 -0.0669 0.9840 0.0170
-7.750 -0.5663 0.01354 0.00880 -0.0667 0.9807 0.0183
-7.500 -0.5365 0.01326 0.00851 -0.0672 0.9782 0.0191
-7.250 -0.5046 0.01309 0.00832 -0.0682 0.9764 0.0201
-7.000 -0.4716 0.01295 0.00813 -0.0693 0.9750 0.0213
-6.750 -0.4379 0.01278 0.00792 -0.0706 0.9739 0.0219
-6.500 -0.4074 0.01158 0.00660 -0.0716 0.9727 0.0235
-6.250 -0.3738 0.01124 0.00625 -0.0729 0.9719 0.0248
-6.000 -0.3393 0.01098 0.00597 -0.0745 0.9712 0.0262
-5.750 -0.3141 0.01066 0.00560 -0.0738 0.9665 0.0272
-5.500 -0.2826 0.01037 0.00528 -0.0746 0.9641 0.0280
-5.250 -0.2505 0.00993 0.00477 -0.0755 0.9621 0.0288
-5.000 -0.2193 0.00920 0.00399 -0.0764 0.9600 0.0309
-4.750 -0.1866 0.00883 0.00360 -0.0774 0.9581 0.0322
-4.500 -0.1593 0.00856 0.00330 -0.0772 0.9532 0.0337
-4.250 -0.1304 0.00829 0.00300 -0.0774 0.9484 0.0349
-4.000 -0.0991 0.00804 0.00272 -0.0780 0.9450 0.0359
-3.750 -0.0701 0.00783 0.00247 -0.0782 0.9403 0.0366
-3.500 -0.0434 0.00752 0.00213 -0.0778 0.9340 0.0398
-3.250 -0.0128 0.00729 0.00190 -0.0783 0.9295 0.0432
-3.000 0.0134 0.00712 0.00172 -0.0778 0.9225 0.0484
-2.750 0.0417 0.00684 0.00157 -0.0779 0.9158 0.0796
-2.500 0.0685 0.00673 0.00149 -0.0775 0.9054 0.0941
-2.250 0.0960 0.00663 0.00139 -0.0772 0.8938 0.1034
-2.000 0.1235 0.00659 0.00130 -0.0770 0.8826 0.1096
-1.750 0.1504 0.00651 0.00121 -0.0766 0.8716 0.1179
-1.500 0.1769 0.00647 0.00115 -0.0762 0.8602 0.1240
-1.250 0.2033 0.00641 0.00108 -0.0757 0.8485 0.1332
-1.000 0.2291 0.00636 0.00102 -0.0751 0.8339 0.1460
-0.750 0.2548 0.00629 0.00097 -0.0745 0.8191 0.1648
-0.500 0.2798 0.00616 0.00093 -0.0738 0.8046 0.2088
-0.250 0.3026 0.00577 0.00091 -0.0729 0.7888 0.3476
0.000 0.3220 0.00514 0.00091 -0.0713 0.7728 0.5789
0.250 0.3391 0.00464 0.00094 -0.0689 0.7546 0.7680
0.500 0.3587 0.00439 0.00100 -0.0666 0.7288 0.8955
0.750 0.4038 0.00457 0.00108 -0.0702 0.6804 0.9597
1.000 0.4440 0.00487 0.00116 -0.0729 0.6361 0.9760
1.250 0.4776 0.00508 0.00124 -0.0742 0.6083 0.9851
1.500 0.5155 0.00525 0.00131 -0.0764 0.5846 0.9917
1.750 0.5677 0.00547 0.00138 -0.0819 0.5500 0.9996
2.000 0.5909 0.00569 0.00143 -0.0809 0.5074 1.0000
2.250 0.6099 0.00599 0.00151 -0.0791 0.4543 1.0000
2.500 0.6285 0.00636 0.00164 -0.0772 0.3989 1.0000
2.750 0.6474 0.00675 0.00178 -0.0753 0.3425 1.0000
3.000 0.6658 0.00719 0.00196 -0.0735 0.2833 1.0000
3.250 0.6862 0.00753 0.00212 -0.0720 0.2455 1.0000
3.500 0.7081 0.00777 0.00226 -0.0707 0.2254 1.0000
4.000 0.7535 0.00816 0.00255 -0.0685 0.1986 1.0000
4.250 0.7768 0.00834 0.00269 -0.0676 0.1889 1.0000
4.500 0.7997 0.00854 0.00284 -0.0665 0.1768 1.0000
4.750 0.8226 0.00875 0.00301 -0.0655 0.1653 1.0000
5.000 0.8456 0.00896 0.00316 -0.0645 0.1526 1.0000
5.250 0.8683 0.00919 0.00334 -0.0635 0.1362 1.0000
5.500 0.8892 0.00957 0.00356 -0.0621 0.1067 1.0000
5.750 0.9104 0.00993 0.00384 -0.0608 0.0909 1.0000
6.000 0.9328 0.01021 0.00409 -0.0598 0.0823 1.0000
6.250 0.9546 0.01054 0.00438 -0.0586 0.0722 1.0000
6.500 0.9763 0.01088 0.00466 -0.0574 0.0548 1.0000
6.750 0.9945 0.01155 0.00514 -0.0556 0.0314 1.0000
7.000 1.0162 0.01192 0.00553 -0.0545 0.0278 1.0000
7.250 1.0369 0.01239 0.00602 -0.0531 0.0238 1.0000
7.500 1.0592 0.01271 0.00636 -0.0521 0.0219 1.0000
7.750 1.0801 0.01315 0.00682 -0.0508 0.0198 1.0000
8.000 1.1000 0.01371 0.00743 -0.0493 0.0180 1.0000
8.250 1.1220 0.01404 0.00779 -0.0483 0.0169 1.0000
8.500 1.1434 0.01441 0.00818 -0.0472 0.0158 1.0000
8.750 1.1631 0.01494 0.00873 -0.0458 0.0147 1.0000
9.000 1.1797 0.01572 0.00959 -0.0438 0.0137 1.0000
9.250 1.2006 0.01610 0.01002 -0.0426 0.0131 1.0000
9.500 1.2201 0.01658 0.01054 -0.0413 0.0125 1.0000
9.750 1.2389 0.01709 0.01110 -0.0398 0.0119 1.0000
10.000 1.2569 0.01764 0.01170 -0.0382 0.0114 1.0000
10.250 1.2719 0.01840 0.01250 -0.0361 0.0108 1.0000
10.500 1.2805 0.01949 0.01370 -0.0330 0.0102 1.0000
10.750 1.2964 0.01995 0.01422 -0.0311 0.0100 1.0000
11.000 1.3087 0.02062 0.01497 -0.0285 0.0097 1.0000
11.250 1.3216 0.02127 0.01568 -0.0262 0.0094 1.0000
11.500 1.3335 0.02199 0.01647 -0.0238 0.0091 1.0000
11.750 1.3443 0.02277 0.01733 -0.0214 0.0089 1.0000
12.000 1.3544 0.02362 0.01824 -0.0190 0.0086 1.0000
12.250 1.3641 0.02450 0.01920 -0.0167 0.0083 1.0000
12.500 1.3719 0.02551 0.02028 -0.0143 0.0080 1.0000
12.750 1.3755 0.02686 0.02172 -0.0115 0.0079 1.0000
13.000 1.3653 0.02933 0.02436 -0.0076 0.0076 1.0000
13.250 1.3610 0.03150 0.02667 -0.0048 0.0075 1.0000
13.500 1.3656 0.03300 0.02829 -0.0030 0.0074 1.0000
13.750 1.3701 0.03457 0.02997 -0.0014 0.0073 1.0000
14.000 1.3737 0.03630 0.03180 -0.0001 0.0072 1.0000
14.250 1.3749 0.03833 0.03395 0.0011 0.0071 1.0000
14.500 1.3723 0.04088 0.03663 0.0021 0.0070 1.0000
14.750 1.3657 0.04405 0.03994 0.0028 0.0069 1.0000
15.000 1.3595 0.04739 0.04342 0.0030 0.0069 1.0000
15.250 1.3553 0.05075 0.04692 0.0025 0.0068 1.0000
15.500 1.3481 0.05470 0.05100 0.0017 0.0067 1.0000
15.750 1.3403 0.05903 0.05546 0.0003 0.0066 1.0000
16.000 1.3297 0.06401 0.06057 -0.0017 0.0065 1.0000
16.250 1.3120 0.07039 0.06712 -0.0044 0.0065 1.0000
16.500 1.2986 0.07652 0.07339 -0.0075 0.0065 1.0000
16.750 1.2748 0.08467 0.08171 -0.0116 0.0066 1.0000
17.000 1.2584 0.09196 0.08913 -0.0155 0.0066 1.0000
17.250 1.2373 0.10037 0.09769 -0.0201 0.0066 1.0000
17.500 1.2100 0.11030 0.10777 -0.0255 0.0067 1.0000
17.750 1.1874 0.11958 0.11719 -0.0307 0.0067 1.0000
18.000 1.1666 0.12866 0.12638 -0.0359 0.0067 1.0000
18.250 1.1392 0.13961 0.13747 -0.0422 0.0067 1.0000
18.500 1.1165 0.14984 0.14781 -0.0482 0.0068 1.0000
18.750 1.0851 0.16308 0.16120 -0.0559 0.0069 1.0000
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