GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.16 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe629-il-1000000.txt Download as CSV file: xf-goe629-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 629 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9816 0.08165 0.07854 -0.0654 1.0000 0.0205
-17.250 -1.0824 0.06383 0.06047 -0.0758 1.0000 0.0196
-17.000 -1.1800 0.04543 0.04171 -0.0878 1.0000 0.0185
-16.750 -1.2139 0.03663 0.03266 -0.0948 1.0000 0.0185
-16.500 -1.2318 0.03203 0.02791 -0.0971 1.0000 0.0187
-16.250 -1.2433 0.02927 0.02503 -0.0967 1.0000 0.0190
-16.000 -1.2514 0.02740 0.02306 -0.0947 1.0000 0.0192
-15.750 -1.2585 0.02603 0.02160 -0.0916 1.0000 0.0196
-15.500 -1.2663 0.02504 0.02054 -0.0873 1.0000 0.0199
-15.250 -1.2812 0.02432 0.01975 -0.0811 1.0000 0.0202
-15.000 -1.2966 0.02361 0.01897 -0.0745 1.0000 0.0206
-14.750 -1.3022 0.02275 0.01806 -0.0697 1.0000 0.0212
-14.500 -1.2800 0.02167 0.01691 -0.0701 0.9986 0.0225
-14.250 -1.2540 0.02070 0.01588 -0.0710 0.9967 0.0241
-14.000 -1.2282 0.01970 0.01484 -0.0719 0.9948 0.0264
-13.750 -1.2008 0.01880 0.01391 -0.0730 0.9935 0.0292
-13.500 -1.1772 0.01802 0.01310 -0.0730 0.9910 0.0325
-13.250 -1.1510 0.01735 0.01242 -0.0734 0.9886 0.0359
-13.000 -1.1232 0.01670 0.01176 -0.0741 0.9866 0.0396
-12.750 -1.0932 0.01619 0.01122 -0.0751 0.9851 0.0426
-12.500 -1.0620 0.01573 0.01076 -0.0762 0.9839 0.0458
-12.250 -1.0300 0.01532 0.01032 -0.0775 0.9830 0.0484
-12.000 -0.9973 0.01494 0.00996 -0.0788 0.9822 0.0513
-11.750 -0.9722 0.01468 0.00965 -0.0784 0.9787 0.0532
-11.500 -0.9438 0.01429 0.00924 -0.0788 0.9761 0.0553
-11.250 -0.9127 0.01396 0.00891 -0.0797 0.9744 0.0575
-11.000 -0.8800 0.01371 0.00864 -0.0809 0.9731 0.0595
-10.750 -0.8463 0.01349 0.00837 -0.0821 0.9720 0.0609
-10.500 -0.8136 0.01305 0.00792 -0.0834 0.9710 0.0633
-10.250 -0.7783 0.01275 0.00763 -0.0851 0.9702 0.0654
-10.000 -0.7423 0.01248 0.00734 -0.0870 0.9692 0.0672
-9.750 -0.7164 0.01229 0.00711 -0.0865 0.9645 0.0685
-9.500 -0.6851 0.01203 0.00681 -0.0873 0.9611 0.0699
-9.250 -0.6544 0.01158 0.00636 -0.0880 0.9581 0.0725
-9.000 -0.6207 0.01133 0.00611 -0.0893 0.9554 0.0749
-8.750 -0.5941 0.01116 0.00592 -0.0890 0.9498 0.0767
-8.500 -0.5661 0.01100 0.00571 -0.0889 0.9444 0.0780
-8.250 -0.5362 0.01069 0.00535 -0.0894 0.9402 0.0797
-8.000 -0.5124 0.01036 0.00501 -0.0886 0.9341 0.0819
-7.750 -0.4868 0.01012 0.00475 -0.0881 0.9282 0.0837
-7.500 -0.4578 0.00991 0.00451 -0.0882 0.9235 0.0855
-7.250 -0.4329 0.00974 0.00432 -0.0876 0.9175 0.0871
-7.000 -0.4065 0.00959 0.00412 -0.0871 0.9114 0.0883
-6.500 -0.3550 0.00914 0.00363 -0.0861 0.8990 0.0931
-6.250 -0.3284 0.00896 0.00344 -0.0857 0.8926 0.0959
-6.000 -0.3019 0.00881 0.00326 -0.0853 0.8862 0.0983
-5.750 -0.2757 0.00870 0.00311 -0.0848 0.8793 0.1001
-5.500 -0.2492 0.00850 0.00291 -0.0844 0.8729 0.1055
-5.250 -0.2236 0.00836 0.00279 -0.0839 0.8660 0.1100
-5.000 -0.1971 0.00823 0.00265 -0.0834 0.8589 0.1156
-4.750 -0.1707 0.00811 0.00255 -0.0830 0.8520 0.1224
-4.500 -0.1444 0.00801 0.00244 -0.0825 0.8440 0.1289
-4.250 -0.1178 0.00792 0.00236 -0.0821 0.8366 0.1359
-4.000 -0.0910 0.00787 0.00228 -0.0817 0.8286 0.1403
-3.750 -0.0647 0.00777 0.00218 -0.0812 0.8209 0.1467
-3.500 -0.0384 0.00771 0.00211 -0.0807 0.8115 0.1513
-3.250 -0.0117 0.00769 0.00204 -0.0803 0.8018 0.1542
-3.000 0.0139 0.00760 0.00193 -0.0796 0.7910 0.1599
-2.750 0.0398 0.00753 0.00187 -0.0790 0.7799 0.1649
-2.500 0.0658 0.00751 0.00180 -0.0785 0.7688 0.1687
-2.250 0.0918 0.00748 0.00173 -0.0779 0.7570 0.1726
-2.000 0.1173 0.00741 0.00167 -0.0772 0.7447 0.1786
-1.750 0.1426 0.00739 0.00161 -0.0765 0.7304 0.1837
-1.500 0.1679 0.00738 0.00156 -0.0758 0.7157 0.1894
-1.250 0.1927 0.00735 0.00152 -0.0750 0.7009 0.1989
-1.000 0.2175 0.00732 0.00149 -0.0742 0.6860 0.2106
-0.750 0.2422 0.00729 0.00147 -0.0734 0.6704 0.2274
-0.500 0.2666 0.00724 0.00145 -0.0726 0.6547 0.2510
-0.250 0.2909 0.00719 0.00145 -0.0718 0.6398 0.2796
0.000 0.3151 0.00715 0.00146 -0.0709 0.6256 0.3108
0.250 0.3391 0.00709 0.00147 -0.0700 0.6122 0.3460
0.500 0.3628 0.00704 0.00149 -0.0691 0.5990 0.3844
0.750 0.3863 0.00696 0.00152 -0.0681 0.5863 0.4355
1.000 0.4095 0.00683 0.00156 -0.0671 0.5757 0.4962
1.250 0.4314 0.00672 0.00161 -0.0658 0.5658 0.5646
1.500 0.4532 0.00652 0.00165 -0.0644 0.5572 0.6450
1.750 0.4716 0.00633 0.00173 -0.0622 0.5488 0.7429
2.000 0.4919 0.00617 0.00181 -0.0604 0.5405 0.8216
2.250 0.5159 0.00612 0.00193 -0.0592 0.5307 0.8902
2.500 0.5545 0.00622 0.00208 -0.0613 0.5183 0.9357
2.750 0.5986 0.00638 0.00221 -0.0648 0.5052 0.9546
3.000 0.6383 0.00656 0.00233 -0.0673 0.4906 0.9652
3.250 0.6766 0.00674 0.00246 -0.0695 0.4782 0.9726
3.500 0.7089 0.00694 0.00259 -0.0703 0.4616 0.9805
3.750 0.7483 0.00715 0.00272 -0.0728 0.4387 0.9847
4.000 0.7848 0.00743 0.00286 -0.0747 0.4099 0.9890
4.250 0.8176 0.00775 0.00303 -0.0759 0.3802 0.9932
4.500 0.8584 0.00806 0.00321 -0.0788 0.3533 0.9966
4.750 0.8969 0.00837 0.00340 -0.0813 0.3310 0.9994
5.250 0.9390 0.00879 0.00369 -0.0786 0.3019 1.0000
5.500 0.9573 0.00896 0.00383 -0.0766 0.2911 1.0000
5.750 0.9747 0.00917 0.00398 -0.0745 0.2787 1.0000
6.250 1.0088 0.00964 0.00433 -0.0701 0.2495 1.0000
6.500 1.0249 0.00992 0.00452 -0.0677 0.2297 1.0000
6.750 1.0389 0.01029 0.00477 -0.0650 0.2051 1.0000
7.000 1.0517 0.01072 0.00505 -0.0621 0.1803 1.0000
7.250 1.0644 0.01115 0.00537 -0.0592 0.1602 1.0000
7.750 1.0886 0.01191 0.00597 -0.0530 0.1298 1.0000
8.250 1.1132 0.01266 0.00658 -0.0471 0.1046 1.0000
8.500 1.1268 0.01306 0.00693 -0.0445 0.0938 1.0000
8.750 1.1406 0.01349 0.00730 -0.0420 0.0835 1.0000
9.000 1.1541 0.01396 0.00772 -0.0395 0.0728 1.0000
9.250 1.1650 0.01458 0.00823 -0.0367 0.0558 1.0000
9.500 1.1748 0.01529 0.00883 -0.0338 0.0427 1.0000
9.750 1.1884 0.01585 0.00937 -0.0316 0.0385 1.0000
10.000 1.2022 0.01641 0.00993 -0.0295 0.0362 1.0000
10.250 1.2165 0.01697 0.01051 -0.0275 0.0347 1.0000
10.500 1.2319 0.01749 0.01106 -0.0257 0.0338 1.0000
10.750 1.2465 0.01807 0.01167 -0.0239 0.0330 1.0000
11.000 1.2601 0.01872 0.01235 -0.0221 0.0321 1.0000
11.250 1.2716 0.01951 0.01316 -0.0200 0.0310 1.0000
11.500 1.2817 0.02042 0.01411 -0.0179 0.0302 1.0000
11.750 1.2958 0.02110 0.01484 -0.0164 0.0298 1.0000
12.000 1.3089 0.02188 0.01567 -0.0148 0.0294 1.0000
12.250 1.3213 0.02272 0.01656 -0.0133 0.0289 1.0000
12.500 1.3330 0.02363 0.01751 -0.0118 0.0284 1.0000
12.750 1.3436 0.02465 0.01858 -0.0102 0.0279 1.0000
13.000 1.3536 0.02574 0.01971 -0.0088 0.0274 1.0000
13.250 1.3610 0.02706 0.02108 -0.0072 0.0269 1.0000
13.500 1.3655 0.02866 0.02273 -0.0056 0.0264 1.0000
13.750 1.3657 0.03064 0.02479 -0.0039 0.0259 1.0000
14.000 1.3741 0.03206 0.02627 -0.0029 0.0256 1.0000
14.250 1.3837 0.03342 0.02769 -0.0020 0.0253 1.0000
14.500 1.3910 0.03501 0.02935 -0.0011 0.0251 1.0000
14.750 1.3980 0.03668 0.03109 -0.0004 0.0247 1.0000
15.000 1.4034 0.03856 0.03303 0.0003 0.0244 1.0000
15.250 1.4083 0.04055 0.03509 0.0009 0.0240 1.0000
15.500 1.4118 0.04275 0.03735 0.0013 0.0237 1.0000
15.750 1.4141 0.04513 0.03979 0.0017 0.0234 1.0000
16.000 1.4158 0.04765 0.04237 0.0018 0.0231 1.0000
16.250 1.4162 0.05039 0.04517 0.0019 0.0227 1.0000
16.500 1.4117 0.05373 0.04858 0.0018 0.0224 1.0000
16.750 1.4034 0.05758 0.05253 0.0015 0.0222 1.0000
17.000 1.3942 0.06162 0.05665 0.0011 0.0220 1.0000
17.250 1.4011 0.06388 0.05899 0.0007 0.0217 1.0000
17.500 1.4003 0.06704 0.06223 0.0002 0.0215 1.0000
17.750 1.3987 0.07036 0.06563 -0.0004 0.0214 1.0000
18.000 1.3979 0.07365 0.06901 -0.0011 0.0211 1.0000
18.250 1.3941 0.07736 0.07280 -0.0020 0.0209 1.0000
18.500 1.3911 0.08100 0.07652 -0.0029 0.0207 1.0000
18.750 1.3874 0.08478 0.08038 -0.0039 0.0204 1.0000
19.000 1.3839 0.08860 0.08428 -0.0051 0.0201 1.0000
19.250 1.3794 0.09261 0.08836 -0.0063 0.0199 1.0000
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