SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 500,000 Max Cl/Cd: 90.06 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7037-il-500000-n5.txt Download as CSV file: xf-sd7037-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7037-092-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4004 0.08100 0.07873 -0.0354 1.0000 0.0083
-8.500 -0.4080 0.07711 0.07489 -0.0362 1.0000 0.0083
-8.250 -0.4205 0.07420 0.07204 -0.0355 1.0000 0.0082
-8.000 -0.4130 0.06771 0.06557 -0.0440 0.9908 0.0081
-7.750 -0.3948 0.05675 0.05456 -0.0618 0.9838 0.0080
-7.500 -0.3942 0.03379 0.03087 -0.0821 0.9711 0.0078
-7.250 -0.3855 0.02480 0.02094 -0.0849 0.9616 0.0079
-7.000 -0.3642 0.02170 0.01735 -0.0854 0.9560 0.0081
-6.750 -0.3422 0.01960 0.01486 -0.0851 0.9498 0.0082
-6.500 -0.3168 0.01823 0.01319 -0.0851 0.9454 0.0084
-6.250 -0.2923 0.01734 0.01205 -0.0846 0.9395 0.0086
-6.000 -0.2694 0.01563 0.01011 -0.0841 0.9336 0.0090
-5.750 -0.2441 0.01474 0.00909 -0.0838 0.9288 0.0092
-5.500 -0.2192 0.01391 0.00814 -0.0833 0.9221 0.0094
-5.250 -0.1936 0.01316 0.00727 -0.0828 0.9165 0.0095
-5.000 -0.1680 0.01250 0.00651 -0.0824 0.9103 0.0098
-4.750 -0.1421 0.01191 0.00584 -0.0820 0.9036 0.0100
-4.500 -0.1158 0.01138 0.00523 -0.0816 0.8974 0.0104
-4.250 -0.0895 0.01091 0.00468 -0.0812 0.8899 0.0108
-4.000 -0.0629 0.01050 0.00419 -0.0808 0.8830 0.0113
-3.750 -0.0361 0.01015 0.00378 -0.0805 0.8745 0.0116
-3.500 -0.0093 0.00975 0.00331 -0.0802 0.8661 0.0124
-3.250 0.0177 0.00947 0.00297 -0.0799 0.8565 0.0136
-3.000 0.0449 0.00924 0.00268 -0.0796 0.8458 0.0150
-2.750 0.0721 0.00901 0.00239 -0.0793 0.8345 0.0166
-2.500 0.0993 0.00878 0.00213 -0.0790 0.8219 0.0216
-2.250 0.1262 0.00851 0.00191 -0.0788 0.8080 0.0470
-2.000 0.1531 0.00827 0.00175 -0.0785 0.7927 0.0839
-1.750 0.1798 0.00799 0.00161 -0.0783 0.7759 0.1424
-1.500 0.2065 0.00779 0.00150 -0.0781 0.7581 0.1965
-1.250 0.2330 0.00756 0.00143 -0.0779 0.7398 0.2709
-1.000 0.2593 0.00732 0.00137 -0.0777 0.7212 0.3599
-0.750 0.2856 0.00710 0.00134 -0.0774 0.7023 0.4485
-0.500 0.3116 0.00689 0.00134 -0.0771 0.6832 0.5449
-0.250 0.3375 0.00678 0.00134 -0.0767 0.6639 0.6169
0.000 0.3632 0.00669 0.00137 -0.0761 0.6450 0.6866
0.250 0.3882 0.00661 0.00142 -0.0754 0.6258 0.7538
0.500 0.4126 0.00658 0.00146 -0.0744 0.6063 0.8113
0.750 0.4359 0.00657 0.00151 -0.0731 0.5874 0.8653
1.000 0.4599 0.00657 0.00153 -0.0720 0.5682 0.9223
1.250 0.4977 0.00664 0.00153 -0.0740 0.5463 0.9838
1.500 0.5268 0.00680 0.00157 -0.0743 0.5261 1.0000
1.750 0.5534 0.00696 0.00163 -0.0740 0.5068 1.0000
2.000 0.5798 0.00714 0.00170 -0.0738 0.4868 1.0000
2.250 0.6062 0.00733 0.00179 -0.0735 0.4674 1.0000
2.500 0.6327 0.00751 0.00188 -0.0732 0.4479 1.0000
2.750 0.6591 0.00771 0.00198 -0.0730 0.4282 1.0000
3.000 0.6853 0.00792 0.00210 -0.0727 0.4087 1.0000
3.250 0.7116 0.00813 0.00223 -0.0724 0.3897 1.0000
3.500 0.7379 0.00835 0.00237 -0.0722 0.3702 1.0000
3.750 0.7639 0.00859 0.00252 -0.0719 0.3509 1.0000
4.000 0.7899 0.00884 0.00270 -0.0716 0.3324 1.0000
4.250 0.8159 0.00909 0.00287 -0.0713 0.3135 1.0000
4.500 0.8417 0.00935 0.00306 -0.0710 0.2948 1.0000
4.750 0.8673 0.00963 0.00328 -0.0707 0.2767 1.0000
5.000 0.8928 0.00992 0.00350 -0.0704 0.2587 1.0000
5.250 0.9184 0.01020 0.00373 -0.0700 0.2427 1.0000
5.500 0.9437 0.01050 0.00397 -0.0697 0.2265 1.0000
5.750 0.9689 0.01082 0.00424 -0.0693 0.2100 1.0000
6.000 0.9935 0.01119 0.00454 -0.0689 0.1911 1.0000
6.250 1.0176 0.01161 0.00485 -0.0684 0.1699 1.0000
6.500 1.0417 0.01202 0.00519 -0.0679 0.1509 1.0000
6.750 1.0657 0.01243 0.00554 -0.0674 0.1350 1.0000
7.000 1.0894 0.01286 0.00591 -0.0668 0.1202 1.0000
7.250 1.1129 0.01330 0.00630 -0.0663 0.1055 1.0000
7.500 1.1360 0.01377 0.00672 -0.0657 0.0908 1.0000
7.750 1.1584 0.01430 0.00718 -0.0650 0.0751 1.0000
8.000 1.1806 0.01484 0.00766 -0.0642 0.0624 1.0000
8.250 1.2023 0.01541 0.00819 -0.0634 0.0506 1.0000
8.500 1.2230 0.01605 0.00878 -0.0625 0.0390 1.0000
8.750 1.2436 0.01668 0.00938 -0.0616 0.0297 1.0000
9.000 1.2635 0.01735 0.01003 -0.0605 0.0211 1.0000
9.250 1.2814 0.01820 0.01083 -0.0592 0.0128 1.0000
9.500 1.3002 0.01890 0.01157 -0.0580 0.0104 1.0000
9.750 1.3184 0.01962 0.01235 -0.0567 0.0091 1.0000
10.000 1.3356 0.02039 0.01318 -0.0553 0.0083 1.0000
10.250 1.3531 0.02106 0.01394 -0.0539 0.0079 1.0000
10.500 1.3691 0.02179 0.01476 -0.0523 0.0077 1.0000
10.750 1.3823 0.02256 0.01562 -0.0503 0.0074 1.0000
11.000 1.3938 0.02339 0.01655 -0.0481 0.0071 1.0000
11.250 1.4041 0.02431 0.01757 -0.0458 0.0068 1.0000
11.500 1.4131 0.02533 0.01868 -0.0436 0.0067 1.0000
11.750 1.4208 0.02646 0.01992 -0.0413 0.0065 1.0000
12.000 1.4262 0.02780 0.02136 -0.0390 0.0063 1.0000
12.250 1.4297 0.02932 0.02299 -0.0368 0.0062 1.0000
12.500 1.4309 0.03111 0.02489 -0.0346 0.0061 1.0000
12.750 1.4293 0.03322 0.02713 -0.0326 0.0059 1.0000
13.000 1.4307 0.03523 0.02926 -0.0311 0.0059 1.0000
13.250 1.4329 0.03728 0.03144 -0.0300 0.0058 1.0000
13.500 1.4324 0.03973 0.03403 -0.0291 0.0058 1.0000
13.750 1.4303 0.04254 0.03696 -0.0286 0.0057 1.0000
14.000 1.4301 0.04530 0.03986 -0.0284 0.0056 1.0000
14.250 1.4253 0.04880 0.04350 -0.0286 0.0056 1.0000
14.500 1.4205 0.05254 0.04738 -0.0293 0.0054 1.0000
14.750 1.4146 0.05661 0.05159 -0.0303 0.0054 1.0000
15.000 1.4088 0.06090 0.05602 -0.0317 0.0053 1.0000
15.250 1.3997 0.06588 0.06114 -0.0335 0.0053 1.0000
15.500 1.3898 0.07126 0.06667 -0.0357 0.0052 1.0000
15.750 1.3791 0.07697 0.07252 -0.0382 0.0052 1.0000
16.000 1.3667 0.08316 0.07885 -0.0411 0.0052 1.0000
16.250 1.3554 0.08939 0.08522 -0.0441 0.0052 1.0000
16.500 1.3428 0.09601 0.09197 -0.0474 0.0051 1.0000
16.750 1.3301 0.10283 0.09893 -0.0509 0.0051 1.0000
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Polar data table (+)
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