NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 50,000 Max Cl/Cd: 38.11 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a410-il-50000.txt Download as CSV file: xf-naca64a410-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
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 -0.4052 0.09867 0.09190 -0.0237 1.0000 0.2911
-8.000 -0.4047 0.09605 0.08936 -0.0225 1.0000 0.3064
-7.750 -0.4090 0.09395 0.08735 -0.0208 1.0000 0.3231
-7.500 -0.4209 0.09249 0.08603 -0.0184 1.0000 0.3395
-7.250 -0.3998 0.08842 0.08195 -0.0162 1.0000 0.3634
-7.000 -0.4182 0.08769 0.08138 -0.0125 1.0000 0.3831
-6.750 -0.4111 0.08510 0.07884 -0.0091 1.0000 0.4118
-6.500 -0.3867 0.08146 0.07515 -0.0063 1.0000 0.4518
-6.250 -0.3861 0.07952 0.07328 -0.0024 1.0000 0.4831
-6.000 -0.3793 0.07695 0.07076 0.0008 1.0000 0.5119
-5.000 -0.4456 0.04886 0.04134 -0.0446 1.0000 0.1637
-4.750 -0.4216 0.04434 0.03632 -0.0458 1.0000 0.1465
-4.500 -0.3944 0.04080 0.03187 -0.0470 1.0000 0.1357
-4.250 -0.3700 0.03766 0.02841 -0.0471 1.0000 0.1323
-4.000 -0.3425 0.03486 0.02506 -0.0474 1.0000 0.1278
-3.750 -0.3141 0.03258 0.02221 -0.0474 1.0000 0.1263
-3.500 -0.2872 0.03084 0.02014 -0.0473 1.0000 0.1318
-3.250 -0.2595 0.02932 0.01818 -0.0470 1.0000 0.1374
-3.000 -0.2333 0.02771 0.01656 -0.0465 1.0000 0.1440
-2.750 -0.2081 0.02648 0.01529 -0.0457 1.0000 0.1577
-2.500 -0.1823 0.02541 0.01413 -0.0451 1.0000 0.1788
-2.250 -0.1526 0.02385 0.01295 -0.0457 1.0000 0.2326
-2.000 -0.1508 0.02080 0.01298 -0.0360 1.0000 0.8273
-1.750 -0.1357 0.02039 0.01243 -0.0327 1.0000 1.0000
-1.500 -0.1110 0.02062 0.01216 -0.0336 1.0000 1.0000
-1.250 -0.0864 0.02092 0.01203 -0.0345 1.0000 1.0000
-1.000 -0.0623 0.02128 0.01204 -0.0352 1.0000 1.0000
-0.750 -0.0385 0.02169 0.01214 -0.0358 1.0000 1.0000
-0.500 -0.0153 0.02214 0.01233 -0.0363 1.0000 1.0000
-0.250 0.0076 0.02264 0.01257 -0.0368 1.0000 1.0000
0.000 0.0301 0.02317 0.01290 -0.0372 1.0000 1.0000
0.250 0.0522 0.02375 0.01330 -0.0376 1.0000 1.0000
0.500 0.0740 0.02436 0.01376 -0.0379 1.0000 1.0000
0.750 0.0955 0.02502 0.01426 -0.0383 1.0000 1.0000
1.000 0.1167 0.02571 0.01484 -0.0386 1.0000 1.0000
1.250 0.1376 0.02644 0.01548 -0.0389 1.0000 1.0000
1.500 0.1581 0.02721 0.01617 -0.0391 1.0000 1.0000
1.750 0.1784 0.02802 0.01692 -0.0394 1.0000 1.0000
2.000 0.1984 0.02887 0.01772 -0.0397 1.0000 1.0000
2.250 0.2182 0.02977 0.01858 -0.0399 1.0000 1.0000
2.500 0.2453 0.03086 0.01966 -0.0417 0.9965 1.0000
2.750 0.2855 0.03227 0.02109 -0.0459 0.9866 1.0000
3.000 0.3222 0.03361 0.02248 -0.0494 0.9760 1.0000
3.250 0.3585 0.03498 0.02391 -0.0528 0.9651 1.0000
3.500 0.3968 0.03640 0.02544 -0.0564 0.9538 1.0000
3.750 0.4348 0.03780 0.02695 -0.0599 0.9418 1.0000
4.000 0.4671 0.03903 0.02831 -0.0622 0.9281 1.0000
4.250 0.5034 0.04022 0.02969 -0.0649 0.9109 1.0000
4.500 0.5363 0.04119 0.03084 -0.0667 0.8907 1.0000
4.750 0.5852 0.04199 0.03189 -0.0703 0.8669 1.0000
5.000 0.6340 0.04233 0.03256 -0.0732 0.8413 1.0000
5.250 0.6706 0.04249 0.03301 -0.0739 0.8159 1.0000
5.500 0.7143 0.04218 0.03306 -0.0749 0.7898 1.0000
5.750 0.7724 0.04044 0.03187 -0.0759 0.7592 1.0000
6.000 0.8831 0.03010 0.02255 -0.0718 0.6915 1.0000
6.250 0.9104 0.02389 0.01618 -0.0584 0.4895 1.0000
6.500 0.8892 0.02756 0.01718 -0.0496 0.2375 1.0000
6.750 0.8949 0.03064 0.01952 -0.0462 0.1762 1.0000
7.000 0.9277 0.03326 0.02170 -0.0460 0.1417 1.0000
7.250 0.9812 0.03641 0.02481 -0.0483 0.1229 1.0000
7.500 1.0189 0.03968 0.02810 -0.0493 0.1115 1.0000
7.750 1.0463 0.04252 0.03147 -0.0484 0.1073 1.0000
8.000 1.0712 0.04587 0.03529 -0.0474 0.1054 1.0000
8.250 1.0907 0.04941 0.03932 -0.0459 0.1045 1.0000
8.500 1.1057 0.05294 0.04326 -0.0441 0.1029 1.0000
8.750 1.1190 0.05669 0.04732 -0.0425 0.1011 1.0000
9.000 1.1224 0.06061 0.05187 -0.0397 0.1022 1.0000
9.250 1.1184 0.06508 0.05695 -0.0367 0.1054 1.0000
9.500 1.1150 0.06980 0.06207 -0.0343 0.1086 1.0000
9.750 1.1281 0.07590 0.06823 -0.0338 0.1122 1.0000
10.000 1.0873 0.07903 0.07207 -0.0293 0.1170 1.0000
10.250 1.0578 0.08368 0.07696 -0.0270 0.1205 1.0000
10.500 1.0586 0.08965 0.08306 -0.0267 0.1280 1.0000
10.750 1.0101 0.09471 0.08824 -0.0270 0.1294 1.0000
11.000 0.9562 0.10350 0.09709 -0.0326 0.1327 1.0000
11.250 0.9096 0.12149 0.11502 -0.0470 0.1702 1.0000
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Polar data table (+)
Polar graphs
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