NACA 1410 (naca1410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 100,000 Max Cl/Cd: 42.16 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1410-il-100000-n5.txt Download as CSV file: xf-naca1410-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7027 0.08728 0.08206 -0.0185 1.0000 0.0351
-11.000 -0.7306 0.07546 0.07022 -0.0276 1.0000 0.0347
-10.750 -0.7576 0.06629 0.06093 -0.0359 1.0000 0.0343
-10.500 -0.7837 0.06003 0.05451 -0.0397 1.0000 0.0340
-10.250 -0.8073 0.05510 0.04932 -0.0397 1.0000 0.0341
-10.000 -0.8236 0.05014 0.04392 -0.0391 1.0000 0.0346
-9.750 -0.8320 0.04567 0.03886 -0.0378 1.0000 0.0352
-9.500 -0.8257 0.04261 0.03560 -0.0368 1.0000 0.0360
-9.250 -0.8138 0.04066 0.03352 -0.0358 1.0000 0.0373
-9.000 -0.8007 0.03884 0.03150 -0.0347 1.0000 0.0391
-8.750 -0.7882 0.03657 0.02888 -0.0335 1.0000 0.0412
-8.500 -0.7749 0.03403 0.02585 -0.0320 1.0000 0.0431
-8.250 -0.7591 0.03181 0.02326 -0.0307 1.0000 0.0450
-8.000 -0.7404 0.03051 0.02195 -0.0298 1.0000 0.0473
-7.750 -0.7212 0.02920 0.02044 -0.0288 1.0000 0.0497
-7.500 -0.7015 0.02771 0.01868 -0.0276 1.0000 0.0521
-7.250 -0.6808 0.02652 0.01716 -0.0264 1.0000 0.0549
-7.000 -0.6609 0.02516 0.01583 -0.0254 1.0000 0.0575
-6.750 -0.6400 0.02411 0.01471 -0.0244 1.0000 0.0598
-6.500 -0.6188 0.02317 0.01364 -0.0233 1.0000 0.0631
-6.250 -0.5971 0.02233 0.01261 -0.0221 1.0000 0.0666
-6.000 -0.5768 0.02131 0.01163 -0.0210 1.0000 0.0697
-5.750 -0.5558 0.02051 0.01081 -0.0199 1.0000 0.0732
-5.500 -0.5346 0.01978 0.00999 -0.0187 1.0000 0.0776
-5.250 -0.5138 0.01904 0.00924 -0.0176 1.0000 0.0834
-5.000 -0.4923 0.01843 0.00861 -0.0165 1.0000 0.0923
-4.750 -0.4713 0.01776 0.00800 -0.0154 1.0000 0.1032
-4.500 -0.4497 0.01716 0.00745 -0.0144 1.0000 0.1184
-4.250 -0.4279 0.01661 0.00697 -0.0135 1.0000 0.1396
-4.000 -0.4059 0.01611 0.00660 -0.0127 1.0000 0.1695
-3.750 -0.3838 0.01565 0.00631 -0.0120 1.0000 0.2075
-3.500 -0.3615 0.01521 0.00607 -0.0113 1.0000 0.2546
-3.250 -0.3392 0.01474 0.00583 -0.0106 1.0000 0.3096
-3.000 -0.3172 0.01421 0.00569 -0.0099 1.0000 0.3772
-2.750 -0.2950 0.01385 0.00567 -0.0090 1.0000 0.4626
-2.500 -0.2638 0.01360 0.00558 -0.0099 0.9961 0.5301
-2.250 -0.2274 0.01331 0.00555 -0.0116 0.9888 0.5951
-2.000 -0.1918 0.01308 0.00556 -0.0129 0.9813 0.6647
-1.750 -0.1553 0.01293 0.00560 -0.0142 0.9739 0.7314
-1.500 -0.1209 0.01282 0.00564 -0.0149 0.9648 0.7903
-1.250 -0.0825 0.01279 0.00568 -0.0163 0.9570 0.8443
-1.000 -0.0386 0.01279 0.00571 -0.0190 0.9496 0.8907
-0.750 0.0074 0.01280 0.00569 -0.0222 0.9414 0.9287
-0.500 0.0586 0.01279 0.00564 -0.0267 0.9337 0.9592
-0.250 0.1097 0.01274 0.00555 -0.0314 0.9236 0.9809
0.000 0.1627 0.01264 0.00541 -0.0365 0.9129 0.9960
0.250 0.1999 0.01253 0.00526 -0.0385 0.8963 1.0000
0.500 0.2297 0.01244 0.00513 -0.0388 0.8769 1.0000
0.750 0.2593 0.01235 0.00500 -0.0389 0.8571 1.0000
1.000 0.2861 0.01231 0.00491 -0.0384 0.8347 1.0000
1.250 0.3130 0.01228 0.00481 -0.0378 0.8121 1.0000
1.500 0.3383 0.01229 0.00478 -0.0370 0.7877 1.0000
1.750 0.3638 0.01232 0.00474 -0.0362 0.7635 1.0000
2.000 0.3885 0.01239 0.00475 -0.0352 0.7377 1.0000
2.250 0.4130 0.01249 0.00479 -0.0342 0.7113 1.0000
2.500 0.4372 0.01262 0.00483 -0.0331 0.6838 1.0000
2.750 0.4611 0.01278 0.00490 -0.0320 0.6553 1.0000
3.000 0.4849 0.01298 0.00502 -0.0309 0.6264 1.0000
3.250 0.5084 0.01320 0.00515 -0.0298 0.5966 1.0000
3.500 0.5317 0.01345 0.00530 -0.0287 0.5650 1.0000
3.750 0.5548 0.01372 0.00549 -0.0275 0.5306 1.0000
4.000 0.5777 0.01403 0.00570 -0.0264 0.4957 1.0000
4.250 0.6005 0.01437 0.00594 -0.0253 0.4606 1.0000
4.500 0.6227 0.01477 0.00621 -0.0242 0.4173 1.0000
4.750 0.6437 0.01527 0.00647 -0.0229 0.3617 1.0000
5.000 0.6642 0.01589 0.00680 -0.0217 0.3007 1.0000
5.250 0.6850 0.01658 0.00723 -0.0207 0.2475 1.0000
5.500 0.7058 0.01732 0.00776 -0.0197 0.1978 1.0000
5.750 0.7265 0.01814 0.00836 -0.0187 0.1560 1.0000
6.000 0.7474 0.01897 0.00906 -0.0177 0.1253 1.0000
6.250 0.7680 0.01985 0.00984 -0.0167 0.1043 1.0000
6.500 0.7885 0.02074 0.01072 -0.0156 0.0909 1.0000
6.750 0.8087 0.02164 0.01162 -0.0145 0.0816 1.0000
7.000 0.8284 0.02259 0.01254 -0.0134 0.0746 1.0000
7.250 0.8487 0.02351 0.01356 -0.0122 0.0700 1.0000
7.500 0.8690 0.02448 0.01463 -0.0111 0.0663 1.0000
7.750 0.8886 0.02553 0.01571 -0.0100 0.0632 1.0000
8.000 0.9082 0.02674 0.01695 -0.0089 0.0601 1.0000
8.250 0.9291 0.02779 0.01818 -0.0079 0.0568 1.0000
8.500 0.9495 0.02902 0.01951 -0.0070 0.0544 1.0000
8.750 0.9691 0.03025 0.02079 -0.0060 0.0519 1.0000
9.000 0.9881 0.03184 0.02246 -0.0051 0.0494 1.0000
9.250 1.0074 0.03333 0.02424 -0.0041 0.0471 1.0000
9.500 1.0253 0.03494 0.02608 -0.0029 0.0448 1.0000
9.750 1.0417 0.03636 0.02763 -0.0018 0.0425 1.0000
10.000 1.0574 0.03807 0.02936 -0.0009 0.0405 1.0000
10.250 1.0699 0.04045 0.03206 0.0006 0.0391 1.0000
10.500 1.0786 0.04281 0.03487 0.0024 0.0374 1.0000
10.750 1.0851 0.04507 0.03746 0.0042 0.0357 1.0000
11.000 1.0896 0.04721 0.03984 0.0060 0.0342 1.0000
11.250 1.0916 0.04943 0.04225 0.0078 0.0333 1.0000
11.500 1.0899 0.05180 0.04479 0.0099 0.0326 1.0000
11.750 1.0867 0.05445 0.04757 0.0116 0.0319 1.0000
12.000 1.0777 0.05786 0.05114 0.0130 0.0314 1.0000
12.250 1.0591 0.06194 0.05554 0.0135 0.0312 1.0000
12.500 1.0384 0.06683 0.06073 0.0126 0.0310 1.0000
12.750 1.0162 0.07267 0.06683 0.0100 0.0310 1.0000
13.000 0.9924 0.07958 0.07396 0.0059 0.0311 1.0000
13.250 0.9673 0.08766 0.08222 0.0006 0.0312 1.0000
13.500 0.9413 0.09688 0.09158 -0.0057 0.0315 1.0000
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Polar data table (+)
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