SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 50,000 Max Cl/Cd: 31.95 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7032-il-50000.txt Download as CSV file: xf-sd7032-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD7032-099-88
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3441 0.10755 0.10109 -0.0284 1.0000 0.2098
-8.000 -0.3170 0.10163 0.09514 -0.0263 1.0000 0.2204
-7.750 -0.3474 0.10265 0.09640 -0.0259 1.0000 0.2247
-7.500 -0.3236 0.09736 0.09110 -0.0240 1.0000 0.2364
-7.250 -0.3337 0.09551 0.08939 -0.0224 1.0000 0.2425
-7.000 -0.3390 0.09388 0.08786 -0.0201 1.0000 0.2524
-6.750 -0.3384 0.09117 0.08524 -0.0178 1.0000 0.2608
-6.500 -0.3661 0.09126 0.08552 -0.0147 1.0000 0.2685
-6.250 -0.3611 0.08830 0.08263 -0.0119 1.0000 0.2809
-6.000 -0.3651 0.08610 0.08053 -0.0092 1.0000 0.2928
-5.750 -0.3746 0.08427 0.07881 -0.0068 1.0000 0.3047
-5.500 -0.3793 0.08222 0.07686 -0.0039 1.0000 0.3208
-5.250 -0.3854 0.08030 0.07504 -0.0015 1.0000 0.3351
-5.000 -0.3890 0.07828 0.07310 0.0014 1.0000 0.3539
-4.750 -0.4064 0.07723 0.07217 0.0020 1.0000 0.3750
-4.500 -0.3976 0.07410 0.06907 0.0072 1.0000 0.3942
-3.750 -0.2889 0.04666 0.03971 -0.0487 1.0000 0.1493
-3.500 -0.2562 0.04171 0.03418 -0.0519 1.0000 0.1327
-3.250 -0.2271 0.03839 0.03036 -0.0537 1.0000 0.1299
-3.000 -0.1974 0.03562 0.02704 -0.0551 1.0000 0.1298
-2.750 -0.1683 0.03324 0.02413 -0.0559 1.0000 0.1295
-2.500 -0.1407 0.03143 0.02182 -0.0562 1.0000 0.1328
-2.250 -0.1162 0.03005 0.02023 -0.0561 1.0000 0.1417
-2.000 -0.0912 0.02895 0.01874 -0.0557 1.0000 0.1503
-1.750 -0.0686 0.02799 0.01773 -0.0551 1.0000 0.1663
-1.500 -0.0457 0.02713 0.01693 -0.0545 1.0000 0.1931
-1.250 -0.0176 0.02581 0.01611 -0.0548 1.0000 0.2793
-1.000 -0.0147 0.02236 0.01566 -0.0477 1.0000 1.0000
-0.750 0.0087 0.02296 0.01552 -0.0482 1.0000 1.0000
-0.500 0.0298 0.02363 0.01572 -0.0486 1.0000 1.0000
-0.250 0.0713 0.02478 0.01638 -0.0527 0.9900 1.0000
0.000 0.1222 0.02608 0.01725 -0.0583 0.9744 1.0000
0.250 0.1721 0.02731 0.01810 -0.0636 0.9585 1.0000
0.500 0.2204 0.02844 0.01894 -0.0684 0.9426 1.0000
0.750 0.2598 0.02933 0.01961 -0.0715 0.9256 1.0000
1.000 0.2990 0.03018 0.02029 -0.0744 0.9083 1.0000
1.250 0.3384 0.03099 0.02094 -0.0772 0.8911 1.0000
1.500 0.3780 0.03174 0.02156 -0.0798 0.8743 1.0000
1.750 0.4185 0.03241 0.02213 -0.0823 0.8578 1.0000
2.000 0.4598 0.03297 0.02262 -0.0848 0.8415 1.0000
2.250 0.5013 0.03343 0.02304 -0.0870 0.8257 1.0000
2.500 0.5290 0.03405 0.02362 -0.0873 0.8075 1.0000
2.750 0.5622 0.03453 0.02410 -0.0882 0.7903 1.0000
3.000 0.5983 0.03488 0.02445 -0.0893 0.7738 1.0000
3.250 0.6364 0.03507 0.02467 -0.0904 0.7576 1.0000
3.500 0.6761 0.03510 0.02476 -0.0914 0.7420 1.0000
3.750 0.7146 0.03500 0.02470 -0.0920 0.7266 1.0000
4.000 0.7523 0.03479 0.02456 -0.0922 0.7112 1.0000
4.250 0.7897 0.03450 0.02436 -0.0922 0.6958 1.0000
4.500 0.8276 0.03408 0.02401 -0.0921 0.6804 1.0000
4.750 0.8571 0.03414 0.02413 -0.0912 0.6631 1.0000
5.000 0.8820 0.03449 0.02456 -0.0901 0.6446 1.0000
5.250 0.9143 0.03433 0.02451 -0.0893 0.6274 1.0000
5.500 0.9488 0.03399 0.02425 -0.0885 0.6103 1.0000
5.750 0.9841 0.03359 0.02391 -0.0878 0.5933 1.0000
6.000 1.0116 0.03382 0.02424 -0.0867 0.5749 1.0000
6.250 1.0336 0.03449 0.02502 -0.0853 0.5555 1.0000
6.500 1.0631 0.03460 0.02519 -0.0842 0.5369 1.0000
6.750 1.0961 0.03452 0.02515 -0.0834 0.5188 1.0000
7.000 1.1137 0.03563 0.02640 -0.0818 0.4992 1.0000
7.250 1.1373 0.03629 0.02715 -0.0805 0.4798 1.0000
7.500 1.1670 0.03653 0.02740 -0.0795 0.4610 1.0000
7.750 1.1865 0.03755 0.02858 -0.0779 0.4417 1.0000
8.000 1.2059 0.03857 0.02973 -0.0763 0.4222 1.0000
8.250 1.2347 0.03885 0.02999 -0.0753 0.4023 1.0000
8.500 1.2517 0.04009 0.03136 -0.0735 0.3831 1.0000
8.750 1.2691 0.04121 0.03265 -0.0718 0.3634 1.0000
9.000 1.2982 0.04146 0.03279 -0.0707 0.3422 1.0000
9.250 1.3079 0.04318 0.03476 -0.0684 0.3232 1.0000
9.500 1.3286 0.04394 0.03552 -0.0668 0.3019 1.0000
9.750 1.3449 0.04525 0.03688 -0.0649 0.2821 1.0000
10.000 1.3545 0.04696 0.03876 -0.0626 0.2633 1.0000
10.250 1.3810 0.04768 0.03928 -0.0615 0.2416 1.0000
10.500 1.3862 0.04991 0.04174 -0.0590 0.2259 1.0000
10.750 1.3934 0.05228 0.04427 -0.0567 0.2113 1.0000
11.000 1.4002 0.05452 0.04663 -0.0545 0.1974 1.0000
11.250 1.4104 0.05694 0.04912 -0.0527 0.1845 1.0000
11.500 1.3876 0.06119 0.05388 -0.0489 0.1805 1.0000
11.750 1.3959 0.06361 0.05634 -0.0472 0.1695 1.0000
12.000 1.3664 0.06799 0.06105 -0.0436 0.1682 1.0000
12.250 1.3333 0.07317 0.06649 -0.0413 0.1681 1.0000
12.500 1.2964 0.07962 0.07314 -0.0407 0.1692 1.0000
12.750 1.2588 0.08741 0.08106 -0.0421 0.1707 1.0000
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Polar data table (+)
Polar graphs
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