SA7024 (sa7024-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SA7024 (sa7024-il) Reynolds number: 200,000 Max Cl/Cd: 80.53 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7024-il-200000.txt Download as CSV file: xf-sa7024-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3780 0.08792 0.08454 -0.0237 1.0000 0.0340
-7.250 -0.3803 0.08551 0.08219 -0.0233 1.0000 0.0349
-7.000 -0.3846 0.08317 0.07992 -0.0228 1.0000 0.0356
-6.750 -0.3848 0.08030 0.07711 -0.0237 1.0000 0.0366
-6.500 -0.3835 0.07729 0.07414 -0.0254 1.0000 0.0377
-6.250 -0.3796 0.07388 0.07077 -0.0290 1.0000 0.0393
-6.000 -0.3646 0.06965 0.06649 -0.0382 1.0000 0.0408
-5.750 -0.3506 0.06569 0.06242 -0.0428 1.0000 0.0412
-5.500 -0.3465 0.05939 0.05608 -0.0453 1.0000 0.0419
-5.250 -0.3443 0.05668 0.05347 -0.0425 1.0000 0.0430
-5.000 -0.3368 0.05439 0.05120 -0.0412 1.0000 0.0445
-4.750 -0.3241 0.05151 0.04827 -0.0419 1.0000 0.0465
-4.500 -0.3047 0.04774 0.04436 -0.0445 1.0000 0.0502
-4.250 -0.2733 0.04155 0.03767 -0.0508 1.0000 0.0557
-4.000 -0.2599 0.03936 0.03553 -0.0500 1.0000 0.0581
-3.750 -0.2167 0.03527 0.03103 -0.0559 0.9967 0.0700
-3.500 -0.1746 0.03214 0.02754 -0.0606 0.9930 0.0830
-3.250 -0.1348 0.02957 0.02468 -0.0643 0.9884 0.0965
-3.000 -0.0861 0.02325 0.01744 -0.0664 0.9865 0.0516
-2.750 -0.0428 0.01924 0.01270 -0.0682 0.9845 0.0363
-2.500 -0.0019 0.01705 0.01003 -0.0700 0.9811 0.0328
-2.250 0.0367 0.01563 0.00838 -0.0717 0.9755 0.0323
-2.000 0.0787 0.01451 0.00719 -0.0743 0.9712 0.0344
-1.750 0.1165 0.01389 0.00653 -0.0762 0.9642 0.0404
-1.500 0.1584 0.01296 0.00557 -0.0789 0.9588 0.0478
-1.250 0.1968 0.01129 0.00499 -0.0815 0.9534 0.3403
-1.000 0.2290 0.01005 0.00497 -0.0824 0.9467 0.6826
-0.750 0.2745 0.00934 0.00466 -0.0849 0.9434 1.0000
-0.500 0.3124 0.00920 0.00435 -0.0867 0.9338 1.0000
-0.250 0.3530 0.00903 0.00404 -0.0889 0.9260 1.0000
0.000 0.3925 0.00885 0.00375 -0.0909 0.9173 1.0000
0.250 0.4270 0.00872 0.00353 -0.0918 0.9054 1.0000
0.500 0.4607 0.00860 0.00333 -0.0926 0.8923 1.0000
0.750 0.4929 0.00852 0.00316 -0.0930 0.8777 1.0000
1.000 0.5240 0.00846 0.00302 -0.0931 0.8617 1.0000
1.250 0.5517 0.00847 0.00297 -0.0926 0.8420 1.0000
1.500 0.5797 0.00850 0.00290 -0.0922 0.8220 1.0000
1.750 0.6064 0.00857 0.00289 -0.0915 0.7999 1.0000
2.000 0.6332 0.00867 0.00288 -0.0908 0.7781 1.0000
2.250 0.6590 0.00879 0.00292 -0.0901 0.7544 1.0000
2.500 0.6847 0.00895 0.00301 -0.0893 0.7302 1.0000
2.750 0.7102 0.00913 0.00310 -0.0885 0.7052 1.0000
3.000 0.7353 0.00933 0.00320 -0.0877 0.6786 1.0000
3.250 0.7601 0.00955 0.00332 -0.0868 0.6508 1.0000
3.500 0.7847 0.00979 0.00347 -0.0859 0.6222 1.0000
3.750 0.8092 0.01006 0.00368 -0.0851 0.5930 1.0000
4.000 0.8335 0.01035 0.00388 -0.0842 0.5638 1.0000
4.250 0.8576 0.01067 0.00411 -0.0834 0.5342 1.0000
4.500 0.8815 0.01101 0.00436 -0.0825 0.5039 1.0000
4.750 0.9052 0.01137 0.00469 -0.0816 0.4725 1.0000
5.000 0.9284 0.01177 0.00499 -0.0807 0.4379 1.0000
5.250 0.9513 0.01220 0.00533 -0.0798 0.4030 1.0000
5.500 0.9741 0.01267 0.00570 -0.0789 0.3685 1.0000
5.750 0.9968 0.01316 0.00612 -0.0780 0.3346 1.0000
6.000 1.0194 0.01369 0.00658 -0.0771 0.3012 1.0000
6.250 1.0413 0.01428 0.00712 -0.0762 0.2666 1.0000
6.500 1.0626 0.01495 0.00764 -0.0752 0.2278 1.0000
6.750 1.0834 0.01568 0.00820 -0.0743 0.1812 1.0000
7.000 1.1040 0.01650 0.00884 -0.0734 0.1416 1.0000
7.250 1.1244 0.01738 0.00961 -0.0723 0.1096 1.0000
7.500 1.1439 0.01839 0.01046 -0.0713 0.0745 1.0000
7.750 1.1560 0.02056 0.01238 -0.0689 0.0316 1.0000
8.000 1.1682 0.02259 0.01451 -0.0664 0.0232 1.0000
8.250 1.1855 0.02384 0.01589 -0.0647 0.0195 1.0000
8.500 1.1988 0.02555 0.01767 -0.0628 0.0168 1.0000
8.750 1.2087 0.02817 0.02045 -0.0603 0.0156 1.0000
9.000 1.2247 0.03007 0.02254 -0.0585 0.0150 1.0000
9.250 1.2404 0.03234 0.02503 -0.0568 0.0146 1.0000
9.500 1.2551 0.03496 0.02792 -0.0550 0.0143 1.0000
9.750 1.2674 0.03795 0.03125 -0.0531 0.0142 1.0000
10.000 1.2754 0.04126 0.03492 -0.0509 0.0142 1.0000
10.250 1.2783 0.04478 0.03882 -0.0484 0.0143 1.0000
10.500 1.2746 0.04835 0.04275 -0.0453 0.0145 1.0000
10.750 1.2647 0.05178 0.04655 -0.0419 0.0147 1.0000
11.000 1.2511 0.05537 0.05042 -0.0390 0.0148 1.0000
11.250 1.2353 0.05931 0.05461 -0.0370 0.0150 1.0000
11.500 1.2177 0.06370 0.05925 -0.0361 0.0151 1.0000
11.750 1.1991 0.06865 0.06442 -0.0365 0.0152 1.0000
12.000 1.1796 0.07425 0.07018 -0.0381 0.0153 1.0000
12.250 1.1596 0.08061 0.07674 -0.0410 0.0154 1.0000
12.500 1.1395 0.08773 0.08402 -0.0450 0.0156 1.0000
12.750 1.0125 0.09454 0.09121 -0.0451 0.0154 1.0000
13.000 0.9873 0.10282 0.09965 -0.0501 0.0155 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SA7024 (sa7024-il)