NACA 1410 (naca1410-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 200,000 Max Cl/Cd: 56.59 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1410-il-200000.txt Download as CSV file: xf-naca1410-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7100 0.07275 0.06906 -0.0326 1.0000 0.0439
-10.250 -0.7278 0.06615 0.06242 -0.0369 1.0000 0.0431
-10.000 -0.7513 0.06061 0.05676 -0.0389 1.0000 0.0424
-9.750 -0.7729 0.05498 0.05090 -0.0392 1.0000 0.0418
-9.500 -0.7885 0.04923 0.04481 -0.0387 1.0000 0.0416
-9.250 -0.7967 0.04395 0.03908 -0.0373 1.0000 0.0417
-9.000 -0.7977 0.03935 0.03397 -0.0355 1.0000 0.0422
-8.750 -0.7920 0.03563 0.02974 -0.0335 1.0000 0.0430
-8.500 -0.7808 0.03353 0.02712 -0.0315 1.0000 0.0445
-8.250 -0.7694 0.02983 0.02324 -0.0302 1.0000 0.0467
-8.000 -0.7510 0.02851 0.02182 -0.0290 1.0000 0.0489
-7.750 -0.7327 0.02690 0.01995 -0.0276 1.0000 0.0511
-7.500 -0.7135 0.02571 0.01845 -0.0261 1.0000 0.0539
-7.250 -0.6950 0.02370 0.01614 -0.0247 1.0000 0.0561
-7.000 -0.6745 0.02228 0.01470 -0.0236 1.0000 0.0588
-6.750 -0.6533 0.02147 0.01382 -0.0225 1.0000 0.0620
-6.500 -0.6316 0.02057 0.01275 -0.0213 1.0000 0.0647
-6.250 -0.6095 0.01991 0.01190 -0.0201 1.0000 0.0669
-6.000 -0.5886 0.01836 0.01036 -0.0191 1.0000 0.0704
-5.750 -0.5668 0.01761 0.00961 -0.0180 1.0000 0.0735
-5.500 -0.5448 0.01692 0.00886 -0.0168 1.0000 0.0768
-5.250 -0.5227 0.01635 0.00819 -0.0157 1.0000 0.0804
-5.000 -0.5017 0.01544 0.00737 -0.0146 1.0000 0.0857
-4.750 -0.4796 0.01490 0.00681 -0.0135 1.0000 0.0919
-4.500 -0.4580 0.01418 0.00617 -0.0125 1.0000 0.1015
-4.250 -0.4357 0.01356 0.00561 -0.0116 1.0000 0.1215
-4.000 -0.4134 0.01285 0.00519 -0.0109 1.0000 0.1622
-3.750 -0.3904 0.01232 0.00491 -0.0104 1.0000 0.2141
-3.500 -0.3667 0.01193 0.00475 -0.0100 1.0000 0.2669
-3.250 -0.3427 0.01158 0.00457 -0.0096 1.0000 0.3167
-3.000 -0.3188 0.01112 0.00447 -0.0094 1.0000 0.3835
-2.750 -0.2952 0.01080 0.00452 -0.0089 1.0000 0.4832
-2.500 -0.2716 0.01053 0.00455 -0.0083 1.0000 0.5594
-2.250 -0.2434 0.01026 0.00464 -0.0086 0.9983 0.6371
-2.000 -0.2033 0.01005 0.00473 -0.0109 0.9926 0.7122
-1.750 -0.1639 0.00992 0.00479 -0.0130 0.9859 0.7760
-1.500 -0.1275 0.00983 0.00488 -0.0141 0.9781 0.8374
-1.250 -0.0875 0.00986 0.00500 -0.0157 0.9721 0.8957
-1.000 -0.0419 0.00992 0.00507 -0.0187 0.9657 0.9375
-0.750 0.0144 0.00996 0.00507 -0.0241 0.9626 0.9632
-0.500 0.0743 0.00995 0.00502 -0.0305 0.9596 0.9797
-0.250 0.1355 0.00986 0.00490 -0.0372 0.9544 0.9925
0.000 0.1946 0.00966 0.00468 -0.0435 0.9479 1.0000
0.250 0.2309 0.00943 0.00443 -0.0451 0.9319 1.0000
0.500 0.2590 0.00925 0.00421 -0.0449 0.9111 1.0000
0.750 0.2851 0.00909 0.00402 -0.0442 0.8898 1.0000
1.000 0.3094 0.00898 0.00385 -0.0431 0.8677 1.0000
1.250 0.3328 0.00892 0.00372 -0.0417 0.8437 1.0000
1.500 0.3560 0.00890 0.00363 -0.0404 0.8182 1.0000
1.750 0.3794 0.00893 0.00356 -0.0391 0.7917 1.0000
2.000 0.4029 0.00899 0.00351 -0.0379 0.7643 1.0000
2.250 0.4265 0.00909 0.00351 -0.0367 0.7359 1.0000
2.500 0.4500 0.00922 0.00354 -0.0355 0.7069 1.0000
2.750 0.4734 0.00937 0.00358 -0.0344 0.6759 1.0000
3.000 0.4966 0.00956 0.00364 -0.0332 0.6442 1.0000
3.250 0.5200 0.00976 0.00373 -0.0321 0.6140 1.0000
3.500 0.5430 0.01000 0.00383 -0.0309 0.5812 1.0000
3.750 0.5655 0.01025 0.00396 -0.0297 0.5422 1.0000
4.000 0.5876 0.01055 0.00408 -0.0285 0.5002 1.0000
4.250 0.6101 0.01086 0.00425 -0.0273 0.4602 1.0000
4.500 0.6329 0.01119 0.00447 -0.0263 0.4219 1.0000
4.750 0.6553 0.01158 0.00471 -0.0253 0.3796 1.0000
5.000 0.6774 0.01203 0.00499 -0.0243 0.3303 1.0000
5.250 0.6986 0.01262 0.00534 -0.0232 0.2733 1.0000
5.500 0.7185 0.01342 0.00581 -0.0220 0.2047 1.0000
5.750 0.7367 0.01456 0.00650 -0.0207 0.1343 1.0000
6.000 0.7553 0.01572 0.00737 -0.0193 0.1011 1.0000
6.250 0.7760 0.01660 0.00820 -0.0181 0.0886 1.0000
6.500 0.7975 0.01743 0.00907 -0.0169 0.0820 1.0000
6.750 0.8191 0.01824 0.00987 -0.0159 0.0768 1.0000
7.000 0.8397 0.01937 0.01098 -0.0148 0.0726 1.0000
7.250 0.8627 0.02017 0.01186 -0.0139 0.0693 1.0000
7.500 0.8854 0.02106 0.01281 -0.0131 0.0662 1.0000
7.750 0.9073 0.02220 0.01391 -0.0123 0.0628 1.0000
8.000 0.9298 0.02371 0.01551 -0.0115 0.0603 1.0000
8.250 0.9528 0.02466 0.01663 -0.0107 0.0577 1.0000
8.500 0.9749 0.02563 0.01771 -0.0099 0.0546 1.0000
8.750 0.9966 0.02692 0.01903 -0.0092 0.0519 1.0000
9.000 1.0165 0.02940 0.02169 -0.0083 0.0493 1.0000
9.250 1.0360 0.03055 0.02313 -0.0071 0.0470 1.0000
9.500 1.0546 0.03219 0.02499 -0.0059 0.0447 1.0000
9.750 1.0726 0.03356 0.02647 -0.0048 0.0425 1.0000
10.000 1.0863 0.03710 0.03012 -0.0039 0.0402 1.0000
10.250 1.0951 0.03919 0.03267 -0.0017 0.0390 1.0000
10.500 1.1010 0.04192 0.03583 0.0006 0.0379 1.0000
10.750 1.1024 0.04501 0.03932 0.0030 0.0369 1.0000
11.000 1.1004 0.04808 0.04272 0.0055 0.0359 1.0000
11.250 1.0968 0.05084 0.04574 0.0077 0.0350 1.0000
11.500 1.0937 0.05292 0.04795 0.0101 0.0341 1.0000
11.750 1.0992 0.05447 0.04949 0.0114 0.0330 1.0000
12.000 1.0874 0.05764 0.05283 0.0131 0.0327 1.0000
12.250 1.0654 0.06199 0.05744 0.0139 0.0327 1.0000
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Polar data table (+)
Polar graphs
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