NACA 1410 (naca1410-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 100,000 Max Cl/Cd: 44.56 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1410-il-100000.txt Download as CSV file: xf-naca1410-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6299 0.09111 0.08620 -0.0171 1.0000 0.1657
-8.750 -0.7041 0.06367 0.05824 -0.0347 1.0000 0.0925
-8.500 -0.7018 0.05859 0.05305 -0.0346 1.0000 0.0911
-8.250 -0.7037 0.05311 0.04732 -0.0344 1.0000 0.0890
-8.000 -0.7070 0.04703 0.04077 -0.0335 1.0000 0.0862
-7.750 -0.7062 0.04131 0.03438 -0.0319 1.0000 0.0840
-7.500 -0.6931 0.03851 0.03128 -0.0305 1.0000 0.0865
-7.250 -0.6799 0.03562 0.02795 -0.0288 1.0000 0.0892
-7.000 -0.6647 0.03274 0.02456 -0.0271 1.0000 0.0908
-6.750 -0.6474 0.03083 0.02204 -0.0252 1.0000 0.0935
-6.500 -0.6280 0.02834 0.01950 -0.0243 1.0000 0.0974
-6.250 -0.6066 0.02669 0.01767 -0.0232 1.0000 0.1006
-6.000 -0.5848 0.02523 0.01593 -0.0219 1.0000 0.1049
-5.750 -0.5626 0.02370 0.01422 -0.0208 1.0000 0.1098
-5.500 -0.5399 0.02244 0.01297 -0.0199 1.0000 0.1149
-5.250 -0.5166 0.02134 0.01165 -0.0187 1.0000 0.1210
-5.000 -0.4942 0.02011 0.01056 -0.0178 1.0000 0.1292
-4.750 -0.4721 0.01914 0.00963 -0.0167 1.0000 0.1423
-4.500 -0.4503 0.01814 0.00875 -0.0155 1.0000 0.1616
-4.250 -0.4291 0.01710 0.00790 -0.0143 1.0000 0.1948
-4.000 -0.4085 0.01614 0.00731 -0.0132 1.0000 0.2460
-3.750 -0.3877 0.01528 0.00680 -0.0122 1.0000 0.3130
-3.500 -0.3677 0.01439 0.00649 -0.0110 1.0000 0.3976
-3.250 -0.3476 0.01385 0.00642 -0.0095 1.0000 0.5100
-3.000 -0.3279 0.01338 0.00639 -0.0075 1.0000 0.6047
-2.750 -0.3082 0.01309 0.00642 -0.0052 1.0000 0.6866
-2.500 -0.2887 0.01295 0.00649 -0.0027 1.0000 0.7575
-2.250 -0.2694 0.01293 0.00662 0.0001 1.0000 0.8252
-2.000 -0.2435 0.01306 0.00681 0.0018 1.0000 0.8935
-1.750 -0.1878 0.01335 0.00698 -0.0027 1.0000 0.9568
-1.500 -0.1015 0.01354 0.00694 -0.0140 1.0000 0.9933
-1.250 -0.0874 0.01339 0.00668 -0.0133 1.0000 1.0000
-1.000 -0.0890 0.01337 0.00657 -0.0094 1.0000 1.0000
-0.750 -0.0809 0.01349 0.00659 -0.0071 1.0000 1.0000
-0.500 -0.0678 0.01371 0.00672 -0.0056 1.0000 1.0000
-0.250 -0.0483 0.01401 0.00694 -0.0053 0.9988 1.0000
0.000 0.0079 0.01436 0.00721 -0.0117 0.9875 1.0000
0.250 0.0634 0.01464 0.00744 -0.0179 0.9756 1.0000
0.500 0.1185 0.01481 0.00760 -0.0237 0.9628 1.0000
0.750 0.1732 0.01487 0.00767 -0.0292 0.9491 1.0000
1.000 0.2291 0.01482 0.00766 -0.0348 0.9349 1.0000
1.250 0.2826 0.01464 0.00755 -0.0395 0.9198 1.0000
1.500 0.3308 0.01440 0.00738 -0.0430 0.9031 1.0000
1.750 0.3711 0.01417 0.00719 -0.0446 0.8840 1.0000
2.000 0.4027 0.01399 0.00704 -0.0444 0.8612 1.0000
2.250 0.4326 0.01380 0.00687 -0.0438 0.8387 1.0000
2.500 0.4581 0.01369 0.00676 -0.0422 0.8130 1.0000
2.750 0.4818 0.01366 0.00671 -0.0404 0.7858 1.0000
3.000 0.5054 0.01367 0.00668 -0.0387 0.7580 1.0000
3.250 0.5287 0.01372 0.00668 -0.0369 0.7291 1.0000
3.500 0.5514 0.01382 0.00671 -0.0350 0.6980 1.0000
3.750 0.5739 0.01397 0.00679 -0.0332 0.6650 1.0000
4.000 0.5964 0.01416 0.00690 -0.0315 0.6316 1.0000
4.250 0.6188 0.01439 0.00702 -0.0298 0.5972 1.0000
4.500 0.6400 0.01463 0.00718 -0.0280 0.5556 1.0000
4.750 0.6605 0.01491 0.00730 -0.0261 0.5084 1.0000
5.000 0.6805 0.01527 0.00747 -0.0243 0.4580 1.0000
5.250 0.7005 0.01572 0.00778 -0.0226 0.4025 1.0000
5.500 0.7189 0.01637 0.00814 -0.0208 0.3340 1.0000
5.750 0.7346 0.01749 0.00877 -0.0188 0.2490 1.0000
6.000 0.7492 0.01913 0.00985 -0.0168 0.1791 1.0000
6.250 0.7667 0.02064 0.01105 -0.0151 0.1466 1.0000
6.500 0.7867 0.02202 0.01224 -0.0138 0.1295 1.0000
6.750 0.8092 0.02321 0.01342 -0.0128 0.1178 1.0000
7.000 0.8331 0.02473 0.01492 -0.0120 0.1108 1.0000
7.250 0.8578 0.02612 0.01638 -0.0113 0.1050 1.0000
7.500 0.8826 0.02802 0.01822 -0.0109 0.0996 1.0000
7.750 0.9059 0.02945 0.01995 -0.0099 0.0948 1.0000
8.000 0.9293 0.03123 0.02190 -0.0092 0.0911 1.0000
8.250 0.9522 0.03403 0.02465 -0.0089 0.0869 1.0000
8.500 0.9697 0.03575 0.02693 -0.0071 0.0839 1.0000
8.750 0.9862 0.03829 0.02993 -0.0055 0.0814 1.0000
9.000 1.0032 0.04048 0.03238 -0.0043 0.0778 1.0000
9.250 1.0205 0.04340 0.03531 -0.0036 0.0746 1.0000
9.500 1.0278 0.04797 0.04029 -0.0019 0.0735 1.0000
9.750 1.0294 0.05126 0.04416 0.0006 0.0726 1.0000
10.000 1.0255 0.05510 0.04852 0.0031 0.0718 1.0000
10.250 1.0169 0.05937 0.05322 0.0053 0.0713 1.0000
10.500 1.0042 0.06396 0.05813 0.0072 0.0715 1.0000
10.750 0.9889 0.06865 0.06305 0.0088 0.0721 1.0000
11.000 0.9729 0.07343 0.06797 0.0100 0.0728 1.0000
11.250 0.9687 0.07868 0.07332 0.0102 0.0742 1.0000
11.500 0.6842 0.10055 0.09574 -0.0010 0.1018 1.0000
11.750 0.6961 0.10314 0.09836 0.0011 0.1008 1.0000
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Polar data table (+)
Polar graphs
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