SA7024 (sa7024-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7024 (sa7024-il) Reynolds number: 200,000 Max Cl/Cd: 74.62 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7024-il-200000-n5.txt Download as CSV file: xf-sa7024-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7024
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3840 0.09396 0.09051 -0.0271 1.0000 0.0237
-7.750 -0.3848 0.09120 0.08781 -0.0273 1.0000 0.0237
-7.500 -0.3876 0.08849 0.08517 -0.0274 1.0000 0.0238
-7.250 -0.3860 0.08525 0.08198 -0.0287 1.0000 0.0238
-7.000 -0.3830 0.08186 0.07863 -0.0305 1.0000 0.0238
-6.750 -0.3789 0.07822 0.07502 -0.0327 1.0000 0.0238
-6.500 -0.3735 0.07451 0.07132 -0.0349 1.0000 0.0238
-6.250 -0.3702 0.06972 0.06658 -0.0373 1.0000 0.0240
-6.000 -0.3697 0.06431 0.06116 -0.0395 1.0000 0.0245
-5.750 -0.3626 0.06004 0.05686 -0.0413 0.9999 0.0248
-5.500 -0.3282 0.05341 0.05007 -0.0498 0.9958 0.0250
-5.250 -0.3038 0.04992 0.04654 -0.0524 0.9920 0.0196
-5.000 -0.2550 0.03727 0.03321 -0.0639 0.9869 0.0153
-4.750 -0.2229 0.03406 0.02981 -0.0685 0.9831 0.0171
-4.500 -0.1900 0.03104 0.02647 -0.0716 0.9781 0.0191
-4.250 -0.1520 0.02471 0.01928 -0.0749 0.9736 0.0167
-4.000 -0.1145 0.02168 0.01563 -0.0770 0.9702 0.0157
-3.750 -0.0822 0.02006 0.01365 -0.0779 0.9647 0.0153
-3.250 -0.0123 0.01691 0.00986 -0.0809 0.9564 0.0149
-3.000 0.0183 0.01556 0.00832 -0.0813 0.9495 0.0149
-2.750 0.0535 0.01437 0.00694 -0.0827 0.9447 0.0150
-2.500 0.0862 0.01325 0.00573 -0.0836 0.9380 0.0153
-2.250 0.1210 0.01241 0.00478 -0.0849 0.9315 0.0161
-2.000 0.1539 0.01185 0.00411 -0.0858 0.9230 0.0178
-1.750 0.1898 0.01142 0.00359 -0.0873 0.9159 0.0220
-1.500 0.2218 0.01098 0.00315 -0.0880 0.9054 0.0380
-1.250 0.2539 0.01016 0.00289 -0.0891 0.8950 0.1902
-1.000 0.2855 0.00952 0.00275 -0.0901 0.8834 0.3566
-0.750 0.3161 0.00906 0.00265 -0.0906 0.8701 0.4863
-0.500 0.3357 0.00807 0.00264 -0.0881 0.8550 0.7987
-0.250 0.3744 0.00778 0.00241 -0.0897 0.8390 1.0000
0.000 0.4038 0.00782 0.00228 -0.0897 0.8212 1.0000
0.250 0.4318 0.00789 0.00220 -0.0895 0.8018 1.0000
0.500 0.4595 0.00797 0.00214 -0.0892 0.7820 1.0000
0.750 0.4866 0.00808 0.00210 -0.0888 0.7611 1.0000
1.000 0.5133 0.00820 0.00208 -0.0883 0.7395 1.0000
1.250 0.5397 0.00834 0.00209 -0.0878 0.7164 1.0000
1.500 0.5657 0.00851 0.00213 -0.0872 0.6923 1.0000
1.750 0.5916 0.00869 0.00217 -0.0866 0.6678 1.0000
2.250 0.6429 0.00908 0.00232 -0.0855 0.6189 1.0000
2.500 0.6684 0.00929 0.00246 -0.0849 0.5947 1.0000
2.750 0.6937 0.00953 0.00259 -0.0843 0.5698 1.0000
3.000 0.7188 0.00978 0.00273 -0.0836 0.5435 1.0000
3.250 0.7436 0.01005 0.00289 -0.0830 0.5155 1.0000
3.500 0.7684 0.01034 0.00308 -0.0823 0.4872 1.0000
3.750 0.7932 0.01064 0.00333 -0.0817 0.4599 1.0000
4.000 0.8178 0.01096 0.00356 -0.0811 0.4329 1.0000
4.250 0.8424 0.01129 0.00382 -0.0805 0.4068 1.0000
4.500 0.8668 0.01164 0.00410 -0.0799 0.3807 1.0000
4.750 0.8911 0.01201 0.00441 -0.0793 0.3540 1.0000
5.000 0.9151 0.01242 0.00474 -0.0786 0.3246 1.0000
5.250 0.9385 0.01289 0.00517 -0.0779 0.2916 1.0000
5.500 0.9615 0.01341 0.00557 -0.0772 0.2571 1.0000
5.750 0.9832 0.01409 0.00602 -0.0764 0.2091 1.0000
6.000 1.0050 0.01480 0.00653 -0.0756 0.1673 1.0000
6.250 1.0279 0.01539 0.00705 -0.0749 0.1406 1.0000
6.500 1.0493 0.01618 0.00766 -0.0741 0.1042 1.0000
6.750 1.0704 0.01701 0.00839 -0.0732 0.0732 1.0000
7.000 1.0911 0.01789 0.00916 -0.0723 0.0473 1.0000
7.250 1.1104 0.01897 0.01011 -0.0711 0.0217 1.0000
7.500 1.1299 0.02004 0.01118 -0.0699 0.0119 1.0000
7.750 1.1503 0.02097 0.01226 -0.0687 0.0094 1.0000
8.000 1.1698 0.02197 0.01337 -0.0675 0.0074 1.0000
8.250 1.1879 0.02311 0.01466 -0.0662 0.0063 1.0000
8.500 1.2058 0.02422 0.01597 -0.0648 0.0058 1.0000
8.750 1.2223 0.02546 0.01746 -0.0632 0.0055 1.0000
9.000 1.2370 0.02683 0.01903 -0.0614 0.0053 1.0000
9.250 1.2500 0.02832 0.02071 -0.0595 0.0051 1.0000
9.500 1.2614 0.02992 0.02251 -0.0574 0.0049 1.0000
9.750 1.2711 0.03166 0.02445 -0.0552 0.0048 1.0000
10.000 1.2785 0.03348 0.02646 -0.0528 0.0047 1.0000
10.250 1.2831 0.03539 0.02858 -0.0501 0.0046 1.0000
10.500 1.2859 0.03746 0.03086 -0.0473 0.0046 1.0000
10.750 1.2869 0.03973 0.03335 -0.0447 0.0045 1.0000
11.000 1.2860 0.04222 0.03608 -0.0424 0.0045 1.0000
11.250 1.2828 0.04503 0.03913 -0.0403 0.0045 1.0000
11.500 1.2779 0.04811 0.04246 -0.0388 0.0045 1.0000
11.750 1.2706 0.05165 0.04626 -0.0377 0.0045 1.0000
12.000 1.2615 0.05557 0.05044 -0.0374 0.0045 1.0000
12.250 1.2503 0.06010 0.05521 -0.0380 0.0045 1.0000
12.500 1.2379 0.06518 0.06054 -0.0394 0.0045 1.0000
12.750 1.2232 0.07106 0.06666 -0.0418 0.0045 1.0000
13.000 1.2081 0.07757 0.07338 -0.0451 0.0045 1.0000
13.250 1.1917 0.08487 0.08090 -0.0493 0.0046 1.0000
13.500 1.1740 0.09302 0.08925 -0.0543 0.0046 1.0000
13.750 1.1562 0.10180 0.09821 -0.0598 0.0046 1.0000
14.000 1.1373 0.11151 0.10809 -0.0660 0.0047 1.0000
14.250 1.1185 0.12188 0.11860 -0.0724 0.0047 1.0000
14.500 1.0984 0.13329 0.13013 -0.0794 0.0048 1.0000
14.750 1.0769 0.14606 0.14299 -0.0868 0.0050 1.0000
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Polar data table (+)
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