GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 100,000 Max Cl/Cd: 46.76 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe290-il-100000-n5.txt Download as CSV file: xf-goe290-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 290 (MVA 290) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4001 0.10134 0.09571 -0.0469 1.0000 0.0611
-11.500 -0.5437 0.06853 0.06266 -0.0696 1.0000 0.0607
-11.250 -0.6140 0.05808 0.05193 -0.0768 1.0000 0.0601
-11.000 -0.6553 0.05465 0.04837 -0.0740 1.0000 0.0600
-10.750 -0.6842 0.05200 0.04557 -0.0701 1.0000 0.0602
-10.500 -0.7048 0.04959 0.04297 -0.0663 1.0000 0.0605
-10.250 -0.6972 0.04570 0.03863 -0.0683 0.9900 0.0614
-10.000 -0.6806 0.04208 0.03447 -0.0707 0.9793 0.0624
-9.750 -0.6558 0.03940 0.03144 -0.0728 0.9695 0.0633
-9.500 -0.6265 0.03778 0.02975 -0.0744 0.9581 0.0643
-9.250 -0.5988 0.03628 0.02814 -0.0756 0.9448 0.0656
-9.000 -0.5733 0.03477 0.02644 -0.0763 0.9288 0.0672
-8.750 -0.5493 0.03318 0.02458 -0.0765 0.9105 0.0688
-8.500 -0.5244 0.03162 0.02262 -0.0766 0.8913 0.0704
-8.250 -0.4957 0.03032 0.02130 -0.0772 0.8726 0.0717
-8.000 -0.4671 0.02920 0.02010 -0.0776 0.8534 0.0732
-7.750 -0.4395 0.02820 0.01892 -0.0776 0.8335 0.0753
-7.500 -0.4134 0.02726 0.01771 -0.0773 0.8133 0.0778
-7.250 -0.3882 0.02636 0.01664 -0.0768 0.7933 0.0798
-7.000 -0.3636 0.02559 0.01583 -0.0763 0.7734 0.0819
-6.750 -0.3392 0.02491 0.01504 -0.0756 0.7544 0.0842
-6.500 -0.3143 0.02429 0.01424 -0.0751 0.7367 0.0872
-6.250 -0.2897 0.02363 0.01352 -0.0745 0.7204 0.0901
-6.000 -0.2651 0.02308 0.01291 -0.0740 0.7053 0.0933
-5.750 -0.2402 0.02258 0.01230 -0.0735 0.6906 0.0971
-5.500 -0.2154 0.02206 0.01172 -0.0730 0.6780 0.1009
-5.250 -0.1904 0.02163 0.01121 -0.0726 0.6671 0.1054
-5.000 -0.1647 0.02124 0.01073 -0.0722 0.6565 0.1108
-4.750 -0.1394 0.02082 0.01026 -0.0719 0.6483 0.1168
-4.500 -0.1133 0.02047 0.00985 -0.0716 0.6397 0.1241
-4.250 -0.0875 0.02009 0.00942 -0.0714 0.6321 0.1339
-4.000 -0.0615 0.01968 0.00900 -0.0711 0.6253 0.1472
-3.750 -0.0357 0.01920 0.00861 -0.0710 0.6182 0.1700
-3.500 -0.0109 0.01862 0.00840 -0.0708 0.6124 0.2303
-3.250 0.0158 0.01848 0.00839 -0.0706 0.6072 0.3002
-3.000 0.0432 0.01847 0.00839 -0.0705 0.6015 0.3356
-2.750 0.0709 0.01849 0.00835 -0.0704 0.5962 0.3607
-2.500 0.0987 0.01852 0.00829 -0.0703 0.5916 0.3814
-2.250 0.1263 0.01853 0.00827 -0.0702 0.5870 0.3999
-2.000 0.1537 0.01853 0.00829 -0.0701 0.5820 0.4202
-1.750 0.1811 0.01854 0.00831 -0.0700 0.5777 0.4413
-1.500 0.2086 0.01853 0.00831 -0.0698 0.5739 0.4613
-1.250 0.2363 0.01854 0.00830 -0.0697 0.5705 0.4822
-1.000 0.2634 0.01853 0.00839 -0.0695 0.5663 0.5038
-0.750 0.2906 0.01852 0.00847 -0.0694 0.5619 0.5248
-0.500 0.3182 0.01851 0.00852 -0.0693 0.5580 0.5451
-0.250 0.3461 0.01852 0.00856 -0.0692 0.5547 0.5673
0.000 0.3736 0.01851 0.00861 -0.0690 0.5516 0.5955
0.250 0.3997 0.01850 0.00877 -0.0685 0.5474 0.6345
0.500 0.4246 0.01846 0.00895 -0.0677 0.5424 0.6877
0.750 0.4496 0.01840 0.00910 -0.0666 0.5375 0.7562
1.000 0.4792 0.01840 0.00920 -0.0662 0.5331 0.8334
1.250 0.5174 0.01852 0.00935 -0.0678 0.5284 0.9020
1.500 0.5580 0.01870 0.00954 -0.0703 0.5223 0.9523
1.750 0.6021 0.01886 0.00961 -0.0737 0.5169 0.9858
2.000 0.6393 0.01901 0.00963 -0.0757 0.5126 1.0000
2.250 0.6620 0.01924 0.00980 -0.0749 0.5082 1.0000
2.500 0.6839 0.01946 0.01001 -0.0740 0.5025 1.0000
2.750 0.7075 0.01962 0.01010 -0.0733 0.4971 1.0000
3.000 0.7328 0.01979 0.01014 -0.0728 0.4928 1.0000
3.250 0.7562 0.02005 0.01040 -0.0722 0.4883 1.0000
3.500 0.7792 0.02032 0.01071 -0.0714 0.4832 1.0000
3.750 0.8035 0.02055 0.01091 -0.0709 0.4785 1.0000
4.000 0.8292 0.02074 0.01103 -0.0705 0.4744 1.0000
4.250 0.8538 0.02099 0.01126 -0.0700 0.4701 1.0000
4.500 0.8761 0.02132 0.01168 -0.0693 0.4646 1.0000
4.750 0.9002 0.02157 0.01193 -0.0687 0.4596 1.0000
5.000 0.9260 0.02175 0.01206 -0.0684 0.4553 1.0000
5.250 0.9493 0.02205 0.01240 -0.0677 0.4503 1.0000
5.500 0.9712 0.02239 0.01282 -0.0669 0.4442 1.0000
5.750 0.9954 0.02259 0.01303 -0.0663 0.4390 1.0000
6.000 1.0202 0.02278 0.01320 -0.0659 0.4342 1.0000
6.250 1.0398 0.02319 0.01374 -0.0647 0.4267 1.0000
6.500 1.0631 0.02337 0.01392 -0.0640 0.4204 1.0000
6.750 1.0842 0.02367 0.01427 -0.0631 0.4135 1.0000
7.000 1.1043 0.02398 0.01465 -0.0620 0.4055 1.0000
7.250 1.1260 0.02418 0.01485 -0.0610 0.3987 1.0000
7.500 1.1436 0.02459 0.01535 -0.0596 0.3892 1.0000
7.750 1.1625 0.02487 0.01564 -0.0583 0.3804 1.0000
8.000 1.1794 0.02522 0.01601 -0.0568 0.3704 1.0000
8.250 1.1943 0.02569 0.01652 -0.0550 0.3598 1.0000
8.500 1.2091 0.02610 0.01690 -0.0532 0.3500 1.0000
8.750 1.2200 0.02668 0.01750 -0.0510 0.3395 1.0000
9.000 1.2287 0.02736 0.01819 -0.0484 0.3300 1.0000
9.250 1.2382 0.02807 0.01886 -0.0462 0.3215 1.0000
9.500 1.2462 0.02903 0.01988 -0.0440 0.3128 1.0000
9.750 1.2547 0.02996 0.02077 -0.0421 0.3055 1.0000
10.000 1.2613 0.03118 0.02205 -0.0402 0.2978 1.0000
10.250 1.2684 0.03237 0.02322 -0.0385 0.2910 1.0000
10.500 1.2740 0.03385 0.02477 -0.0371 0.2845 1.0000
10.750 1.2798 0.03536 0.02631 -0.0357 0.2785 1.0000
11.000 1.2871 0.03682 0.02777 -0.0346 0.2737 1.0000
11.250 1.2925 0.03860 0.02967 -0.0337 0.2691 1.0000
11.500 1.2978 0.04042 0.03157 -0.0328 0.2645 1.0000
11.750 1.3036 0.04216 0.03331 -0.0319 0.2597 1.0000
12.000 1.3074 0.04421 0.03544 -0.0313 0.2550 1.0000
12.250 1.3083 0.04666 0.03801 -0.0308 0.2499 1.0000
12.500 1.3108 0.04889 0.04028 -0.0303 0.2446 1.0000
12.750 1.3151 0.05095 0.04234 -0.0297 0.2398 1.0000
13.000 1.3120 0.05406 0.04562 -0.0297 0.2347 1.0000
13.250 1.3116 0.05682 0.04848 -0.0295 0.2299 1.0000
13.500 1.3156 0.05899 0.05065 -0.0292 0.2250 1.0000
13.750 1.3131 0.06217 0.05396 -0.0293 0.2204 1.0000
14.000 1.3080 0.06576 0.05770 -0.0296 0.2156 1.0000
14.250 1.3070 0.06879 0.06081 -0.0297 0.2107 1.0000
14.500 1.3088 0.07143 0.06349 -0.0298 0.2059 1.0000
14.750 1.2970 0.07621 0.06849 -0.0307 0.2008 1.0000
15.000 1.2893 0.08039 0.07279 -0.0314 0.1952 1.0000
15.250 1.2837 0.08431 0.07680 -0.0321 0.1893 1.0000
15.500 1.2654 0.09037 0.08309 -0.0336 0.1833 1.0000
15.750 1.2557 0.09512 0.08795 -0.0347 0.1767 1.0000
16.000 1.2265 0.10325 0.09636 -0.0371 0.1702 1.0000
16.250 1.1991 0.11127 0.10458 -0.0397 0.1625 1.0000
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