SD7034 (sd7034-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 50,000 Max Cl/Cd: 27.84 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7034-il-50000.txt Download as CSV file: xf-sd7034-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD7034
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3167 0.10700 0.10052 -0.0275 1.0000 0.2096
-8.250 -0.2949 0.10160 0.09513 -0.0262 1.0000 0.2171
-8.000 -0.3108 0.10134 0.09504 -0.0272 1.0000 0.2253
-7.750 -0.2912 0.09653 0.09025 -0.0258 1.0000 0.2342
-7.500 -0.3159 0.09693 0.09087 -0.0252 1.0000 0.2412
-7.250 -0.2993 0.09277 0.08674 -0.0232 1.0000 0.2534
-7.000 -0.3344 0.09382 0.08804 -0.0199 1.0000 0.2569
-6.750 -0.3226 0.09024 0.08449 -0.0173 1.0000 0.2695
-6.500 -0.3574 0.09102 0.08547 -0.0132 1.0000 0.2724
-6.250 -0.3526 0.08810 0.08261 -0.0098 1.0000 0.2829
-6.000 -0.3887 0.08877 0.08345 -0.0080 1.0000 0.2890
-5.750 -0.3821 0.08572 0.08046 -0.0041 1.0000 0.3015
-5.500 -0.3921 0.08390 0.07873 -0.0016 1.0000 0.3109
-5.000 -0.4213 0.08146 0.07648 0.0003 1.0000 0.3382
-4.750 -0.4234 0.07916 0.07424 0.0030 1.0000 0.3545
-4.500 -0.4225 0.07661 0.07174 0.0066 1.0000 0.3719
-4.250 -0.4199 0.07429 0.06949 0.0109 1.0000 0.3932
-3.500 -0.3003 0.04708 0.04025 -0.0440 1.0000 0.1659
-3.250 -0.2707 0.04293 0.03558 -0.0468 1.0000 0.1545
-3.000 -0.2427 0.03983 0.03194 -0.0488 1.0000 0.1543
-2.750 -0.2158 0.03739 0.02899 -0.0500 1.0000 0.1560
-2.500 -0.1890 0.03539 0.02641 -0.0509 1.0000 0.1597
-2.250 -0.1654 0.03389 0.02463 -0.0511 1.0000 0.1678
-2.000 -0.1231 0.03255 0.02285 -0.0543 0.9934 0.1818
-1.750 -0.0764 0.03167 0.02175 -0.0582 0.9838 0.2071
-1.500 -0.0345 0.03098 0.02096 -0.0612 0.9735 0.2410
-1.250 0.0063 0.03040 0.02048 -0.0638 0.9631 0.2914
-1.000 0.0488 0.02956 0.02019 -0.0666 0.9531 0.4000
-0.750 0.0888 0.02740 0.01982 -0.0666 0.9436 1.0000
-0.500 0.1251 0.02822 0.02006 -0.0691 0.9308 1.0000
-0.250 0.1606 0.02907 0.02049 -0.0713 0.9178 1.0000
0.000 0.1952 0.02995 0.02104 -0.0734 0.9049 1.0000
0.250 0.2301 0.03083 0.02164 -0.0755 0.8921 1.0000
0.500 0.2667 0.03172 0.02228 -0.0777 0.8792 1.0000
0.750 0.3074 0.03260 0.02293 -0.0804 0.8666 1.0000
1.000 0.3360 0.03341 0.02359 -0.0812 0.8529 1.0000
1.250 0.3631 0.03426 0.02429 -0.0818 0.8391 1.0000
1.500 0.3914 0.03511 0.02503 -0.0824 0.8252 1.0000
1.750 0.4202 0.03598 0.02579 -0.0831 0.8116 1.0000
2.000 0.4505 0.03681 0.02654 -0.0839 0.7980 1.0000
2.250 0.4827 0.03759 0.02725 -0.0848 0.7846 1.0000
2.500 0.5200 0.03823 0.02783 -0.0862 0.7716 1.0000
2.750 0.5522 0.03890 0.02846 -0.0869 0.7580 1.0000
3.000 0.5754 0.03978 0.02932 -0.0865 0.7436 1.0000
3.250 0.5991 0.04065 0.03018 -0.0862 0.7291 1.0000
3.500 0.6230 0.04153 0.03105 -0.0858 0.7148 1.0000
3.750 0.6472 0.04240 0.03193 -0.0854 0.7005 1.0000
4.000 0.6719 0.04324 0.03279 -0.0850 0.6863 1.0000
4.250 0.6977 0.04401 0.03359 -0.0847 0.6721 1.0000
4.500 0.7243 0.04473 0.03435 -0.0843 0.6584 1.0000
4.750 0.7556 0.04514 0.03481 -0.0840 0.6450 1.0000
5.000 0.8026 0.04434 0.03411 -0.0842 0.6341 1.0000
5.250 0.8234 0.04517 0.03500 -0.0831 0.6194 1.0000
5.500 0.8426 0.04616 0.03605 -0.0820 0.6048 1.0000
5.750 0.8625 0.04707 0.03705 -0.0808 0.5903 1.0000
6.000 0.8814 0.04810 0.03816 -0.0796 0.5759 1.0000
6.250 0.9005 0.04909 0.03923 -0.0783 0.5615 1.0000
7.000 0.9667 0.05120 0.04165 -0.0745 0.5203 1.0000
7.250 1.0500 0.04591 0.03656 -0.0738 0.5109 1.0000
7.500 1.0711 0.04655 0.03731 -0.0724 0.4961 1.0000
7.750 1.0953 0.04686 0.03775 -0.0709 0.4812 1.0000
8.000 1.1198 0.04717 0.03819 -0.0695 0.4662 1.0000
8.250 1.1522 0.04668 0.03781 -0.0681 0.4508 1.0000
8.500 1.1871 0.04599 0.03722 -0.0669 0.4349 1.0000
8.750 1.2108 0.04633 0.03768 -0.0653 0.4185 1.0000
9.000 1.2262 0.04742 0.03890 -0.0636 0.4021 1.0000
9.250 1.0355 0.07144 0.06274 -0.0640 0.3978 1.0000
9.500 1.2576 0.04942 0.04115 -0.0599 0.3685 1.0000
9.750 1.2802 0.04974 0.04158 -0.0582 0.3503 1.0000
10.000 1.3294 0.04776 0.03947 -0.0574 0.3271 1.0000
10.250 0.9928 0.09260 0.08405 -0.0663 0.3531 1.0000
10.500 1.3465 0.05085 0.04282 -0.0530 0.2926 1.0000
10.750 1.3643 0.05162 0.04362 -0.0511 0.2734 1.0000
11.000 1.3925 0.05189 0.04374 -0.0499 0.2524 1.0000
11.250 1.3977 0.05383 0.04578 -0.0476 0.2372 1.0000
11.500 1.4045 0.05586 0.04787 -0.0455 0.2228 1.0000
11.750 1.3773 0.06002 0.05239 -0.0421 0.2176 1.0000
12.000 1.3795 0.06226 0.05467 -0.0400 0.2061 1.0000
12.250 1.3425 0.06760 0.06027 -0.0376 0.2049 1.0000
12.500 1.2937 0.07535 0.06823 -0.0376 0.2068 1.0000
12.750 1.2397 0.08576 0.07873 -0.0403 0.2092 1.0000
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Polar data table (+)
Polar graphs
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