LA2573A (la2573a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LA2573A (la2573a-il) Reynolds number: 500,000 Max Cl/Cd: 102.55 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-la2573a-il-500000.txt Download as CSV file: xf-la2573a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LA2573A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4799 0.08748 0.08350 0.0104 0.4761 0.0394
-8.250 -0.4867 0.08274 0.07879 0.0070 0.4751 0.0402
-8.000 -0.5857 0.06500 0.06078 -0.0041 0.4781 0.0420
-7.750 -0.5765 0.06272 0.05849 -0.0035 0.4763 0.0422
-7.500 -0.5667 0.06056 0.05629 -0.0030 0.4745 0.0424
-7.250 -0.5560 0.05845 0.05413 -0.0025 0.4728 0.0426
-7.000 -0.5446 0.05632 0.05193 -0.0020 0.4711 0.0429
-6.750 -0.5333 0.05385 0.04936 -0.0016 0.4694 0.0433
-6.500 -0.5482 0.04477 0.03948 0.0003 0.4691 0.0472
-6.250 -0.5290 0.04287 0.03757 0.0006 0.4670 0.0475
-6.000 -0.5092 0.04138 0.03606 0.0011 0.4649 0.0478
-5.750 -0.4894 0.03984 0.03448 0.0016 0.4636 0.0482
-5.500 -0.4977 0.02823 0.02138 0.0067 0.4633 0.0422
-5.250 -0.4729 0.02670 0.01983 0.0072 0.4616 0.0413
-5.000 -0.4505 0.02464 0.01757 0.0080 0.4600 0.0408
-4.750 -0.4270 0.02276 0.01543 0.0089 0.4584 0.0406
-4.500 -0.4020 0.02130 0.01372 0.0097 0.4567 0.0408
-4.250 -0.3761 0.02026 0.01244 0.0104 0.4550 0.0413
-4.000 -0.3494 0.01936 0.01135 0.0109 0.4533 0.0416
-3.750 -0.3223 0.01869 0.01052 0.0114 0.4516 0.0418
-3.500 -0.2953 0.01756 0.00931 0.0117 0.4498 0.0422
-3.250 -0.2681 0.01691 0.00863 0.0120 0.4477 0.0428
-3.000 -0.2408 0.01656 0.00825 0.0123 0.4455 0.0434
-2.750 -0.2130 0.01610 0.00780 0.0126 0.4445 0.0440
-2.500 -0.1853 0.01568 0.00737 0.0129 0.4433 0.0448
-2.250 -0.1576 0.01533 0.00700 0.0133 0.4419 0.0458
-2.000 -0.1296 0.01509 0.00671 0.0136 0.4402 0.0467
-1.750 -0.1029 0.01451 0.00616 0.0140 0.4385 0.0477
-1.500 -0.0757 0.01418 0.00586 0.0144 0.4367 0.0487
-1.250 -0.0483 0.01393 0.00562 0.0147 0.4350 0.0500
-1.000 -0.0208 0.01371 0.00539 0.0151 0.4335 0.0513
-0.750 0.0067 0.01354 0.00519 0.0154 0.4320 0.0526
-0.500 0.0334 0.01326 0.00494 0.0158 0.4305 0.0547
-0.250 0.0610 0.01318 0.00486 0.0161 0.4287 0.0572
0.000 0.0880 0.01319 0.00487 0.0164 0.4264 0.0598
0.250 0.1157 0.01299 0.00473 0.0167 0.4253 0.0631
0.500 0.1434 0.01283 0.00461 0.0170 0.4240 0.0678
0.750 0.1712 0.01270 0.00454 0.0172 0.4226 0.0757
1.000 0.1984 0.01249 0.00447 0.0176 0.4210 0.0988
1.250 0.2183 0.01135 0.00437 0.0187 0.4193 0.3981
1.500 0.2212 0.00987 0.00458 0.0244 0.4179 0.8877
1.750 0.2443 0.01002 0.00476 0.0263 0.4162 0.9217
2.000 0.2691 0.01018 0.00491 0.0278 0.4146 0.9418
2.250 0.2991 0.01037 0.00507 0.0282 0.4131 0.9564
2.500 0.3584 0.01074 0.00535 0.0226 0.4110 0.9662
2.750 0.4535 0.01138 0.00590 0.0098 0.4078 0.9807
3.000 0.5156 0.01140 0.00591 0.0032 0.4061 0.9876
3.250 0.5462 0.01140 0.00592 0.0027 0.4042 0.9890
3.500 0.5756 0.01140 0.00592 0.0024 0.4021 0.9903
3.750 0.6048 0.01142 0.00594 0.0022 0.4002 0.9916
4.000 0.6338 0.01144 0.00595 0.0020 0.3983 0.9929
4.250 0.6633 0.01143 0.00592 0.0018 0.3964 0.9938
4.500 0.6935 0.01144 0.00589 0.0013 0.3945 0.9946
4.750 0.7243 0.01151 0.00593 0.0008 0.3926 0.9956
5.000 0.7546 0.01169 0.00611 0.0002 0.3903 0.9966
5.250 0.7846 0.01167 0.00615 -0.0002 0.3883 0.9976
5.500 0.8142 0.01169 0.00621 -0.0006 0.3860 0.9986
5.750 0.8442 0.01169 0.00624 -0.0010 0.3835 0.9995
6.000 0.8727 0.01169 0.00625 -0.0011 0.3811 1.0000
6.250 0.8977 0.01168 0.00623 -0.0005 0.3789 1.0000
6.500 0.9225 0.01171 0.00624 0.0001 0.3767 1.0000
6.750 0.9469 0.01188 0.00640 0.0007 0.3740 1.0000
7.000 0.9713 0.01188 0.00650 0.0013 0.3713 1.0000
7.250 0.9958 0.01172 0.00638 0.0021 0.3667 1.0000
7.500 1.0204 0.01139 0.00598 0.0029 0.3604 1.0000
7.750 1.0445 0.01127 0.00592 0.0036 0.3536 1.0000
8.000 1.0686 0.01124 0.00593 0.0043 0.3486 1.0000
8.250 1.0921 0.01128 0.00594 0.0051 0.3443 1.0000
8.500 1.1156 0.01135 0.00610 0.0059 0.3393 1.0000
8.750 1.1388 0.01140 0.00620 0.0067 0.3334 1.0000
9.000 1.1614 0.01150 0.00629 0.0076 0.3277 1.0000
9.250 1.1839 0.01161 0.00647 0.0085 0.3201 1.0000
9.500 1.2054 0.01177 0.00662 0.0095 0.3123 1.0000
9.750 1.2265 0.01196 0.00685 0.0106 0.3026 1.0000
10.000 1.2470 0.01221 0.00711 0.0117 0.2918 1.0000
10.250 1.2665 0.01256 0.00743 0.0129 0.2782 1.0000
10.500 1.2849 0.01305 0.00787 0.0141 0.2608 1.0000
10.750 1.3019 0.01374 0.00848 0.0152 0.2397 1.0000
11.000 1.3163 0.01472 0.00934 0.0164 0.2139 1.0000
11.250 1.3277 0.01600 0.01048 0.0177 0.1855 1.0000
11.500 1.3350 0.01758 0.01194 0.0190 0.1574 1.0000
11.750 1.3363 0.01955 0.01380 0.0204 0.1330 1.0000
12.000 1.3274 0.02220 0.01644 0.0214 0.1163 1.0000
12.250 1.3036 0.02720 0.02153 0.0199 0.1095 1.0000
12.750 1.2637 0.03624 0.03061 0.0186 0.0947 1.0000
13.000 1.2465 0.04036 0.03474 0.0181 0.0882 1.0000
13.250 1.2301 0.04441 0.03878 0.0176 0.0822 1.0000
13.500 1.2181 0.04806 0.04243 0.0172 0.0765 1.0000
13.750 1.2077 0.05168 0.04606 0.0166 0.0716 1.0000
14.000 1.1984 0.05538 0.04975 0.0159 0.0673 1.0000
14.250 1.1952 0.05852 0.05292 0.0153 0.0633 1.0000
14.500 1.1887 0.06210 0.05649 0.0145 0.0601 1.0000
14.750 1.1884 0.06503 0.05946 0.0139 0.0576 1.0000
15.000 1.1860 0.06823 0.06266 0.0132 0.0549 1.0000
15.250 1.1820 0.07170 0.06614 0.0123 0.0531 1.0000
15.500 1.1844 0.07441 0.06891 0.0117 0.0513 1.0000
15.750 1.1845 0.07741 0.07193 0.0110 0.0497 1.0000
16.000 1.1822 0.08078 0.07531 0.0101 0.0484 1.0000
16.250 1.1824 0.08382 0.07838 0.0093 0.0471 1.0000
16.500 1.1852 0.08658 0.08119 0.0086 0.0460 1.0000
16.750 1.1872 0.08948 0.08413 0.0078 0.0449 1.0000
17.000 1.1891 0.09240 0.08707 0.0069 0.0438 1.0000
17.250 1.1905 0.09537 0.09004 0.0060 0.0429 1.0000
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Polar data table (+)
Polar graphs
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