NACA 1410 (naca1410-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 200,000 Max Cl/Cd: 50.59 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1410-il-200000-n5.txt Download as CSV file: xf-naca1410-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8647 0.06544 0.06159 -0.0294 1.0000 0.0184
-12.000 -0.9111 0.05265 0.04842 -0.0410 1.0000 0.0180
-11.750 -0.9312 0.04743 0.04293 -0.0436 1.0000 0.0181
-11.500 -0.9443 0.04401 0.03928 -0.0428 1.0000 0.0183
-11.250 -0.9503 0.04111 0.03611 -0.0414 1.0000 0.0187
-11.000 -0.9502 0.03829 0.03299 -0.0400 1.0000 0.0193
-10.750 -0.9460 0.03565 0.02998 -0.0386 1.0000 0.0202
-10.500 -0.9380 0.03321 0.02709 -0.0372 1.0000 0.0212
-10.250 -0.9250 0.03155 0.02526 -0.0360 1.0000 0.0220
-10.000 -0.9079 0.03056 0.02422 -0.0351 1.0000 0.0229
-9.750 -0.8908 0.02940 0.02291 -0.0341 1.0000 0.0239
-9.500 -0.8738 0.02802 0.02132 -0.0330 1.0000 0.0251
-9.250 -0.8557 0.02673 0.01974 -0.0319 1.0000 0.0267
-9.000 -0.8373 0.02543 0.01822 -0.0308 1.0000 0.0281
-8.750 -0.8182 0.02444 0.01717 -0.0298 1.0000 0.0295
-8.500 -0.7982 0.02358 0.01623 -0.0288 1.0000 0.0309
-8.250 -0.7777 0.02275 0.01526 -0.0278 1.0000 0.0328
-8.000 -0.7568 0.02197 0.01429 -0.0267 1.0000 0.0346
-7.750 -0.7371 0.02090 0.01313 -0.0255 1.0000 0.0362
-7.500 -0.7169 0.02012 0.01230 -0.0244 1.0000 0.0380
-7.250 -0.6958 0.01950 0.01163 -0.0234 1.0000 0.0400
-7.000 -0.6745 0.01886 0.01090 -0.0223 1.0000 0.0420
-6.750 -0.6530 0.01826 0.01019 -0.0212 1.0000 0.0437
-6.500 -0.6325 0.01749 0.00939 -0.0200 1.0000 0.0457
-6.250 -0.6116 0.01687 0.00875 -0.0189 1.0000 0.0479
-6.000 -0.5902 0.01635 0.00818 -0.0178 1.0000 0.0499
-5.750 -0.5685 0.01589 0.00766 -0.0167 1.0000 0.0524
-5.500 -0.5465 0.01548 0.00718 -0.0157 1.0000 0.0549
-5.250 -0.5251 0.01493 0.00664 -0.0147 1.0000 0.0584
-5.000 -0.5029 0.01453 0.00622 -0.0137 1.0000 0.0624
-4.750 -0.4803 0.01419 0.00584 -0.0128 1.0000 0.0674
-4.500 -0.4478 0.01374 0.00543 -0.0141 0.9969 0.0778
-4.250 -0.4123 0.01331 0.00505 -0.0160 0.9929 0.0957
-4.000 -0.3774 0.01288 0.00474 -0.0178 0.9881 0.1211
-3.750 -0.3413 0.01250 0.00447 -0.0198 0.9838 0.1512
-3.500 -0.3074 0.01213 0.00422 -0.0213 0.9779 0.1838
-3.250 -0.2706 0.01177 0.00401 -0.0234 0.9736 0.2225
-3.000 -0.2383 0.01139 0.00382 -0.0245 0.9663 0.2722
-2.750 -0.2036 0.01088 0.00361 -0.0263 0.9611 0.3371
-2.500 -0.1750 0.01035 0.00352 -0.0266 0.9519 0.4328
-2.250 -0.1424 0.01008 0.00340 -0.0276 0.9444 0.4934
-2.000 -0.1116 0.00984 0.00327 -0.0281 0.9348 0.5328
-1.750 -0.0818 0.00959 0.00318 -0.0283 0.9245 0.5747
-1.500 -0.0518 0.00930 0.00310 -0.0285 0.9146 0.6251
-1.250 -0.0236 0.00907 0.00304 -0.0282 0.9026 0.6748
-1.000 0.0039 0.00887 0.00299 -0.0276 0.8894 0.7208
-0.750 0.0312 0.00872 0.00296 -0.0269 0.8754 0.7656
-0.500 0.0584 0.00860 0.00296 -0.0261 0.8603 0.8109
-0.250 0.0866 0.00854 0.00296 -0.0255 0.8441 0.8550
0.000 0.1178 0.00853 0.00296 -0.0254 0.8265 0.8914
0.250 0.1510 0.00856 0.00296 -0.0260 0.8063 0.9204
0.500 0.1852 0.00862 0.00294 -0.0269 0.7840 0.9412
0.750 0.2197 0.00869 0.00292 -0.0279 0.7605 0.9580
1.000 0.2547 0.00877 0.00290 -0.0291 0.7359 0.9719
1.250 0.2910 0.00887 0.00290 -0.0308 0.7101 0.9836
1.500 0.3293 0.00898 0.00290 -0.0329 0.6825 0.9928
1.750 0.3658 0.00912 0.00291 -0.0347 0.6524 1.0000
2.000 0.3896 0.00926 0.00292 -0.0338 0.6240 1.0000
2.250 0.4135 0.00943 0.00297 -0.0330 0.5965 1.0000
2.500 0.4373 0.00960 0.00304 -0.0321 0.5689 1.0000
2.750 0.4609 0.00982 0.00312 -0.0312 0.5379 1.0000
3.000 0.4841 0.01006 0.00323 -0.0303 0.5049 1.0000
3.250 0.5076 0.01030 0.00335 -0.0294 0.4746 1.0000
3.500 0.5307 0.01057 0.00350 -0.0285 0.4404 1.0000
3.750 0.5530 0.01093 0.00367 -0.0274 0.3953 1.0000
4.000 0.5748 0.01137 0.00385 -0.0264 0.3395 1.0000
4.250 0.5967 0.01185 0.00409 -0.0254 0.2875 1.0000
4.500 0.6194 0.01230 0.00437 -0.0246 0.2470 1.0000
4.750 0.6422 0.01277 0.00468 -0.0238 0.2089 1.0000
5.000 0.6649 0.01329 0.00504 -0.0230 0.1726 1.0000
5.250 0.6876 0.01382 0.00542 -0.0222 0.1403 1.0000
5.500 0.7103 0.01438 0.00587 -0.0215 0.1114 1.0000
5.750 0.7328 0.01498 0.00634 -0.0207 0.0881 1.0000
6.000 0.7556 0.01557 0.00686 -0.0199 0.0729 1.0000
6.250 0.7786 0.01611 0.00741 -0.0192 0.0637 1.0000
6.500 0.8015 0.01667 0.00799 -0.0184 0.0584 1.0000
6.750 0.8244 0.01723 0.00860 -0.0176 0.0545 1.0000
7.000 0.8463 0.01790 0.00928 -0.0167 0.0512 1.0000
7.250 0.8682 0.01857 0.01000 -0.0158 0.0487 1.0000
7.500 0.8904 0.01919 0.01072 -0.0150 0.0464 1.0000
7.750 0.9121 0.01987 0.01148 -0.0141 0.0444 1.0000
8.000 0.9333 0.02060 0.01225 -0.0132 0.0424 1.0000
8.250 0.9520 0.02166 0.01331 -0.0121 0.0402 1.0000
8.500 0.9732 0.02241 0.01418 -0.0111 0.0387 1.0000
8.750 0.9941 0.02320 0.01510 -0.0102 0.0369 1.0000
9.000 1.0145 0.02400 0.01599 -0.0093 0.0350 1.0000
9.250 1.0339 0.02486 0.01691 -0.0083 0.0334 1.0000
9.500 1.0508 0.02614 0.01820 -0.0071 0.0317 1.0000
9.750 1.0697 0.02713 0.01936 -0.0060 0.0303 1.0000
10.000 1.0879 0.02814 0.02057 -0.0049 0.0287 1.0000
10.250 1.1050 0.02921 0.02177 -0.0037 0.0273 1.0000
10.500 1.1209 0.03020 0.02285 -0.0025 0.0260 1.0000
10.750 1.1346 0.03144 0.02413 -0.0011 0.0248 1.0000
11.000 1.1471 0.03290 0.02578 0.0004 0.0237 1.0000
11.250 1.1582 0.03439 0.02752 0.0022 0.0226 1.0000
11.500 1.1656 0.03593 0.02927 0.0043 0.0217 1.0000
11.750 1.1717 0.03743 0.03094 0.0063 0.0208 1.0000
12.000 1.1771 0.03888 0.03254 0.0081 0.0201 1.0000
12.250 1.1816 0.04039 0.03414 0.0095 0.0195 1.0000
12.500 1.1841 0.04220 0.03604 0.0108 0.0190 1.0000
12.750 1.1821 0.04477 0.03879 0.0118 0.0185 1.0000
13.000 1.1769 0.04793 0.04225 0.0123 0.0180 1.0000
13.250 1.1690 0.05161 0.04621 0.0122 0.0175 1.0000
13.500 1.1586 0.05589 0.05074 0.0112 0.0172 1.0000
13.750 1.1456 0.06089 0.05598 0.0093 0.0169 1.0000
14.000 1.1298 0.06674 0.06207 0.0064 0.0168 1.0000
14.250 1.1103 0.07367 0.06923 0.0024 0.0167 1.0000
14.500 1.0861 0.08201 0.07780 -0.0028 0.0167 1.0000
14.750 1.0556 0.09226 0.08827 -0.0093 0.0169 1.0000
15.000 1.0155 0.10553 0.10175 -0.0177 0.0172 1.0000
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