GOE 571 AIRFOIL (goe571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 571 AIRFOIL (goe571-il) Reynolds number: 1,000,000 Max Cl/Cd: 52.53 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe571-il-1000000-n5.txt Download as CSV file: xf-goe571-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 571 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.5113 0.09494 0.09023 -0.1697 0.4907 0.0185
-11.750 0.5173 0.09259 0.08787 -0.1705 0.4862 0.0186
-11.500 0.5229 0.09025 0.08550 -0.1713 0.4818 0.0185
-11.250 0.5286 0.08795 0.08319 -0.1720 0.4777 0.0185
-11.000 0.5303 0.08501 0.08025 -0.1729 0.4749 0.0189
-10.750 0.5310 0.08213 0.07738 -0.1737 0.4715 0.0197
-10.250 0.5296 0.07599 0.07123 -0.1752 0.4645 0.0191
-10.000 0.5188 0.07157 0.06681 -0.1763 0.4624 0.0194
-9.750 0.5377 0.07192 0.06716 -0.1761 0.4574 0.0197
-9.500 0.5169 0.06635 0.06162 -0.1772 0.4556 0.0195
-9.250 0.5117 0.06342 0.05870 -0.1776 0.4535 0.0195
-9.000 0.1527 0.03097 0.02601 -0.1661 0.4705 0.0195
-8.750 0.1796 0.03222 0.02735 -0.1650 0.4650 0.0196
-8.500 0.1292 0.02937 0.02428 -0.1539 0.4630 0.0196
-8.250 0.1292 0.02894 0.02380 -0.1494 0.4591 0.0197
-8.000 0.1053 0.02708 0.02176 -0.1414 0.4571 0.0197
-7.750 0.0977 0.02596 0.02051 -0.1356 0.4541 0.0198
-7.500 0.1061 0.02571 0.02022 -0.1323 0.4502 0.0199
-7.250 0.1040 0.02473 0.01912 -0.1273 0.4467 0.0199
-6.750 0.1102 0.02339 0.01757 -0.1187 0.4392 0.0201
-6.500 0.1149 0.02264 0.01671 -0.1146 0.4365 0.0201
-6.250 0.1220 0.02201 0.01598 -0.1109 0.4335 0.0202
-6.000 0.1323 0.02164 0.01554 -0.1077 0.4303 0.0203
-5.750 0.1391 0.02106 0.01484 -0.1039 0.4273 0.0204
-5.250 0.1527 0.01966 0.01315 -0.0961 0.4225 0.0205
-5.000 0.1672 0.01943 0.01288 -0.0936 0.4205 0.0206
-4.750 0.1794 0.01897 0.01231 -0.0906 0.4185 0.0207
-4.500 0.1916 0.01860 0.01185 -0.0877 0.4161 0.0208
-4.250 0.2035 0.01822 0.01137 -0.0846 0.4138 0.0209
-4.000 0.2166 0.01795 0.01101 -0.0818 0.4113 0.0211
-3.750 0.2295 0.01758 0.01055 -0.0790 0.4090 0.0210
-3.500 0.2425 0.01736 0.01025 -0.0762 0.4063 0.0212
-3.250 0.2580 0.01716 0.01000 -0.0738 0.4046 0.0213
-3.000 0.2739 0.01688 0.00964 -0.0715 0.4031 0.0214
-2.750 0.2901 0.01661 0.00932 -0.0693 0.4014 0.0214
-2.500 0.3064 0.01644 0.00911 -0.0672 0.3998 0.0215
-2.250 0.3219 0.01635 0.00896 -0.0649 0.3979 0.0216
-2.000 0.3373 0.01618 0.00874 -0.0626 0.3960 0.0217
-1.750 0.3530 0.01606 0.00858 -0.0604 0.3942 0.0219
-1.500 0.3681 0.01606 0.00854 -0.0582 0.3923 0.0220
-1.250 0.3825 0.01612 0.00856 -0.0558 0.3902 0.0222
-1.000 0.3977 0.01603 0.00844 -0.0536 0.3883 0.0221
-0.750 0.4160 0.01606 0.00844 -0.0520 0.3874 0.0224
-0.500 0.4336 0.01605 0.00841 -0.0503 0.3863 0.0225
-0.250 0.4514 0.01600 0.00836 -0.0486 0.3852 0.0224
0.000 0.4694 0.01602 0.00837 -0.0471 0.3834 0.0225
0.250 0.4870 0.01593 0.00829 -0.0455 0.3820 0.0229
0.500 0.5041 0.01601 0.00836 -0.0438 0.3805 0.0230
0.750 0.5217 0.01612 0.00847 -0.0424 0.3789 0.0233
1.000 0.5400 0.01624 0.00858 -0.0410 0.3773 0.0233
1.250 0.5564 0.01644 0.00878 -0.0395 0.3755 0.0236
1.500 0.5740 0.01664 0.00897 -0.0382 0.3741 0.0237
1.750 0.5910 0.01690 0.00922 -0.0369 0.3717 0.0239
2.000 0.6121 0.01706 0.00939 -0.0363 0.3708 0.0241
2.250 0.6340 0.01724 0.00957 -0.0358 0.3697 0.0244
2.500 0.6560 0.01744 0.00979 -0.0355 0.3687 0.0246
2.750 0.6784 0.01766 0.01001 -0.0352 0.3675 0.0250
3.000 0.7011 0.01790 0.01027 -0.0351 0.3664 0.0252
3.250 0.7233 0.01820 0.01057 -0.0350 0.3651 0.0255
3.500 0.7462 0.01850 0.01088 -0.0350 0.3639 0.0256
3.750 0.7703 0.01882 0.01120 -0.0354 0.3621 0.0264
4.000 0.7913 0.01928 0.01167 -0.0354 0.3602 0.0263
4.250 0.8136 0.01973 0.01213 -0.0357 0.3584 0.0269
4.500 0.8359 0.02022 0.01262 -0.0361 0.3568 0.0277
4.750 0.8562 0.02081 0.01322 -0.0362 0.3550 0.0277
5.000 0.8837 0.02118 0.01361 -0.0374 0.3544 0.0290
5.250 0.9112 0.02157 0.01403 -0.0386 0.3532 0.0288
5.500 0.9389 0.02200 0.01449 -0.0400 0.3522 0.0310
5.750 0.9623 0.02253 0.01504 -0.0407 0.3509 0.0320
6.250 1.0071 0.02361 0.01616 -0.0417 0.3481 0.0371
6.500 1.0304 0.02426 0.01695 -0.0428 0.3464 0.0989
7.000 1.3163 0.02506 0.01979 -0.0932 0.3413 1.0000
7.250 1.3259 0.02610 0.02083 -0.0918 0.3394 1.0000
7.500 1.3413 0.02682 0.02157 -0.0912 0.3384 1.0000
7.750 1.3554 0.02764 0.02240 -0.0905 0.3376 1.0000
8.000 1.3701 0.02842 0.02320 -0.0898 0.3363 1.0000
8.250 1.3822 0.02941 0.02420 -0.0890 0.3343 1.0000
8.500 1.3942 0.03040 0.02520 -0.0882 0.3326 1.0000
8.750 1.4053 0.03147 0.02628 -0.0873 0.3311 1.0000
9.000 1.4127 0.03283 0.02764 -0.0863 0.3286 1.0000
9.250 1.4230 0.03399 0.02881 -0.0854 0.3276 1.0000
9.500 1.4278 0.03558 0.03040 -0.0843 0.3253 1.0000
9.750 1.4381 0.03676 0.03160 -0.0835 0.3238 1.0000
10.000 1.4493 0.03791 0.03278 -0.0829 0.3227 1.0000
10.250 1.4608 0.03903 0.03393 -0.0824 0.3213 1.0000
10.500 1.4720 0.04019 0.03511 -0.0819 0.3195 1.0000
10.750 1.4801 0.04161 0.03655 -0.0812 0.3178 1.0000
11.000 1.4865 0.04317 0.03813 -0.0804 0.3154 1.0000
11.250 1.4933 0.04470 0.03967 -0.0796 0.3134 1.0000
11.500 1.4940 0.04676 0.04174 -0.0785 0.3112 1.0000
11.750 1.5009 0.04830 0.04330 -0.0779 0.3092 1.0000
12.000 1.5106 0.04963 0.04467 -0.0775 0.3079 1.0000
12.250 1.5179 0.05120 0.04628 -0.0769 0.3060 1.0000
12.500 1.5257 0.05270 0.04780 -0.0764 0.3039 1.0000
12.750 1.5299 0.05456 0.04967 -0.0758 0.3009 1.0000
13.000 1.5274 0.05700 0.05214 -0.0748 0.2980 1.0000
13.250 1.5280 0.05918 0.05432 -0.0740 0.2954 1.0000
13.500 1.5309 0.06120 0.05638 -0.0734 0.2924 1.0000
13.750 1.5343 0.06318 0.05839 -0.0729 0.2891 1.0000
14.000 1.5391 0.06502 0.06026 -0.0724 0.2872 1.0000
14.250 1.5250 0.06872 0.06397 -0.0712 0.2823 1.0000
14.500 1.5281 0.07075 0.06603 -0.0707 0.2792 1.0000
14.750 1.5234 0.07359 0.06891 -0.0700 0.2752 1.0000
15.000 1.5228 0.07603 0.07137 -0.0695 0.2724 1.0000
15.250 1.5060 0.08016 0.07552 -0.0684 0.2678 1.0000
15.500 1.5083 0.08236 0.07775 -0.0681 0.2643 1.0000
15.750 1.5056 0.08509 0.08052 -0.0676 0.2614 1.0000
16.000 1.4979 0.08835 0.08380 -0.0671 0.2577 1.0000
16.250 1.4843 0.09229 0.08777 -0.0664 0.2536 1.0000
16.500 1.4816 0.09508 0.09060 -0.0661 0.2496 1.0000
16.750 1.4734 0.09851 0.09404 -0.0657 0.2453 1.0000
17.000 1.4638 0.10208 0.09764 -0.0653 0.2425 1.0000
17.250 1.4602 0.10500 0.10059 -0.0652 0.2383 1.0000
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