SA7035 (sa7035-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 50,000 Max Cl/Cd: 33.24 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7035-il-50000.txt Download as CSV file: xf-sa7035-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3847 0.09517 0.08866 -0.0157 1.0000 0.2608
-7.500 -0.3852 0.09254 0.08613 -0.0153 1.0000 0.2729
-7.250 -0.4081 0.09220 0.08597 -0.0151 1.0000 0.2829
-7.000 -0.3920 0.08777 0.08158 -0.0133 1.0000 0.2993
-6.750 -0.4113 0.08701 0.08100 -0.0119 1.0000 0.3116
-6.000 -0.3919 0.07736 0.07157 -0.0052 1.0000 0.3586
-5.750 -0.3906 0.07473 0.06904 -0.0028 1.0000 0.3756
-5.500 -0.4077 0.07352 0.06799 -0.0002 1.0000 0.3982
-5.000 -0.4006 0.05091 0.04410 -0.0402 1.0000 0.1421
-4.750 -0.3823 0.04591 0.03872 -0.0407 1.0000 0.1233
-4.500 -0.3617 0.04122 0.03331 -0.0415 1.0000 0.1110
-4.250 -0.3416 0.03763 0.02934 -0.0412 1.0000 0.1064
-4.000 -0.3179 0.03418 0.02520 -0.0410 1.0000 0.1026
-3.750 -0.2950 0.03170 0.02234 -0.0403 1.0000 0.1046
-3.500 -0.2710 0.02967 0.01984 -0.0396 1.0000 0.1104
-3.250 -0.2465 0.02755 0.01742 -0.0387 1.0000 0.1169
-3.000 -0.2218 0.02589 0.01548 -0.0377 1.0000 0.1280
-2.750 -0.1978 0.02429 0.01394 -0.0366 1.0000 0.1532
-2.500 -0.1734 0.02247 0.01243 -0.0356 1.0000 0.2155
-2.250 -0.1567 0.01886 0.01143 -0.0321 1.0000 0.5922
-2.000 -0.1280 0.01772 0.01086 -0.0284 1.0000 1.0000
-1.750 -0.1074 0.01783 0.01037 -0.0284 1.0000 1.0000
-1.500 -0.0871 0.01802 0.01010 -0.0281 1.0000 1.0000
-1.250 -0.0671 0.01827 0.00994 -0.0278 1.0000 1.0000
-1.000 -0.0473 0.01858 0.00991 -0.0275 1.0000 1.0000
-0.750 -0.0279 0.01894 0.00998 -0.0272 1.0000 1.0000
-0.500 -0.0087 0.01936 0.01014 -0.0269 1.0000 1.0000
-0.250 0.0102 0.01982 0.01038 -0.0266 1.0000 1.0000
0.000 0.0286 0.02035 0.01068 -0.0264 1.0000 1.0000
0.250 0.0468 0.02093 0.01109 -0.0263 1.0000 1.0000
0.500 0.0646 0.02158 0.01159 -0.0262 1.0000 1.0000
0.750 0.0916 0.02246 0.01232 -0.0280 0.9957 1.0000
1.000 0.1468 0.02380 0.01348 -0.0348 0.9769 1.0000
1.250 0.2019 0.02504 0.01459 -0.0412 0.9581 1.0000
1.500 0.2492 0.02602 0.01548 -0.0460 0.9381 1.0000
1.750 0.2976 0.02690 0.01632 -0.0506 0.9180 1.0000
2.000 0.3456 0.02765 0.01705 -0.0549 0.8985 1.0000
2.250 0.3862 0.02825 0.01767 -0.0577 0.8773 1.0000
2.500 0.4383 0.02866 0.01814 -0.0619 0.8584 1.0000
2.750 0.4729 0.02910 0.01863 -0.0632 0.8365 1.0000
3.000 0.5251 0.02914 0.01880 -0.0666 0.8174 1.0000
3.250 0.5621 0.02932 0.01906 -0.0676 0.7962 1.0000
3.500 0.6059 0.02911 0.01897 -0.0690 0.7766 1.0000
3.750 0.6452 0.02889 0.01891 -0.0694 0.7564 1.0000
4.000 0.6808 0.02868 0.01882 -0.0692 0.7352 1.0000
4.250 0.7177 0.02830 0.01856 -0.0687 0.7144 1.0000
4.500 0.7506 0.02802 0.01839 -0.0677 0.6919 1.0000
4.750 0.7801 0.02791 0.01843 -0.0663 0.6681 1.0000
5.000 0.8138 0.02749 0.01808 -0.0649 0.6451 1.0000
5.250 0.8416 0.02748 0.01815 -0.0632 0.6196 1.0000
5.500 0.8670 0.02769 0.01847 -0.0615 0.5931 1.0000
5.750 0.8923 0.02795 0.01879 -0.0597 0.5661 1.0000
6.000 0.9172 0.02827 0.01915 -0.0579 0.5386 1.0000
6.250 0.9416 0.02866 0.01958 -0.0562 0.5104 1.0000
6.500 0.9653 0.02915 0.02014 -0.0544 0.4818 1.0000
6.750 0.9883 0.02975 0.02075 -0.0526 0.4528 1.0000
7.000 1.0108 0.03041 0.02142 -0.0508 0.4235 1.0000
7.250 1.0328 0.03119 0.02219 -0.0491 0.3942 1.0000
7.500 1.0545 0.03204 0.02300 -0.0473 0.3647 1.0000
7.750 1.0745 0.03298 0.02396 -0.0455 0.3344 1.0000
8.000 1.0918 0.03415 0.02519 -0.0434 0.3042 1.0000
8.250 1.1085 0.03544 0.02649 -0.0414 0.2744 1.0000
8.500 1.1248 0.03694 0.02800 -0.0394 0.2458 1.0000
8.750 1.1400 0.03856 0.02960 -0.0374 0.2182 1.0000
9.000 1.1570 0.04065 0.03163 -0.0356 0.1940 1.0000
9.250 1.1684 0.04275 0.03388 -0.0335 0.1723 1.0000
9.500 1.1852 0.04548 0.03655 -0.0320 0.1544 1.0000
9.750 1.1929 0.04824 0.03964 -0.0298 0.1398 1.0000
10.000 1.2051 0.05154 0.04305 -0.0282 0.1278 1.0000
10.250 1.1968 0.05543 0.04763 -0.0251 0.1221 1.0000
10.500 1.2033 0.05864 0.05092 -0.0234 0.1130 1.0000
10.750 1.1887 0.06314 0.05592 -0.0208 0.1111 1.0000
11.000 1.1706 0.06769 0.06084 -0.0186 0.1104 1.0000
11.250 1.1469 0.07211 0.06551 -0.0165 0.1107 1.0000
11.500 1.1212 0.07706 0.07065 -0.0157 0.1116 1.0000
11.750 1.0950 0.08278 0.07651 -0.0166 0.1127 1.0000
12.000 1.0703 0.08930 0.08312 -0.0188 0.1139 1.0000
12.250 1.0479 0.09662 0.09049 -0.0220 0.1148 1.0000
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Polar data table (+)
Polar graphs
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