N-10 (n10-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 100,000 Max Cl/Cd: 52.04 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n10-il-100000.txt Download as CSV file: xf-n10-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: N-10
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3590 0.09733 0.09239 -0.0326 0.9999 0.1208
-10.000 -0.3800 0.09546 0.09066 -0.0343 0.9999 0.1247
-9.750 -0.4194 0.09421 0.08962 -0.0369 0.9999 0.1258
-9.500 -0.4104 0.08996 0.08541 -0.0335 0.9999 0.1277
-9.250 -0.3892 0.08732 0.08274 -0.0295 0.9999 0.1322
-9.000 -0.4020 0.08541 0.08094 -0.0281 0.9999 0.1360
-8.750 -0.4325 0.08331 0.07896 -0.0305 0.9999 0.1397
-8.500 -0.4519 0.07984 0.07553 -0.0321 0.9999 0.1420
-8.250 -0.4385 0.07829 0.07405 -0.0252 0.9999 0.1458
-8.000 -0.4446 0.07615 0.07193 -0.0245 0.9999 0.1517
-7.750 -0.4557 0.07239 0.06814 -0.0274 0.9999 0.1576
-7.500 -0.4507 0.07061 0.06641 -0.0237 0.9999 0.1613
-7.250 -0.4529 0.06693 0.06260 -0.0278 0.9999 0.1720
-7.000 -0.4465 0.06537 0.06082 -0.0299 0.9999 0.1853
-6.750 -0.4405 0.06174 0.05734 -0.0272 0.9999 0.1877
-6.500 -0.4169 0.05865 0.05412 -0.0305 0.9966 0.2028
-6.250 -0.3571 0.03989 0.03339 -0.0468 0.9937 0.1124
-6.000 -0.3190 0.03588 0.02906 -0.0499 0.9888 0.1043
-5.750 -0.2768 0.03233 0.02482 -0.0535 0.9847 0.1019
-5.500 -0.2371 0.02995 0.02190 -0.0562 0.9794 0.1016
-5.250 -0.1949 0.02807 0.01955 -0.0590 0.9738 0.1018
-5.000 -0.1526 0.02671 0.01788 -0.0619 0.9672 0.1045
-4.750 -0.1070 0.02568 0.01651 -0.0651 0.9596 0.1099
-4.500 -0.0649 0.02427 0.01504 -0.0677 0.9509 0.1147
-4.250 -0.0136 0.02313 0.01385 -0.0718 0.9436 0.1240
-4.000 0.0248 0.02216 0.01300 -0.0736 0.9327 0.1393
-3.750 0.0677 0.02118 0.01224 -0.0762 0.9237 0.1710
-3.500 0.1115 0.01962 0.01150 -0.0791 0.9161 0.3113
-3.250 0.1445 0.01821 0.01130 -0.0799 0.9080 0.5771
-3.000 0.2028 0.01716 0.01106 -0.0834 0.9037 1.0001
-2.750 0.2533 0.01688 0.01048 -0.0874 0.8985 1.0001
-2.500 0.2838 0.01686 0.01025 -0.0878 0.8869 1.0001
-2.250 0.3193 0.01676 0.00997 -0.0889 0.8775 1.0001
-2.000 0.3595 0.01650 0.00955 -0.0908 0.8694 1.0001
-1.750 0.3893 0.01645 0.00936 -0.0908 0.8577 1.0001
-1.500 0.4229 0.01628 0.00908 -0.0913 0.8473 1.0001
-1.250 0.4585 0.01603 0.00870 -0.0921 0.8375 1.0001
-1.000 0.4856 0.01600 0.00858 -0.0914 0.8242 1.0001
-0.750 0.5133 0.01596 0.00845 -0.0909 0.8110 1.0001
-0.500 0.5414 0.01589 0.00831 -0.0903 0.7973 1.0001
-0.250 0.5691 0.01581 0.00815 -0.0896 0.7826 1.0001
0.000 0.5959 0.01574 0.00799 -0.0888 0.7663 1.0001
0.250 0.6223 0.01566 0.00783 -0.0878 0.7486 1.0001
0.500 0.6491 0.01555 0.00764 -0.0869 0.7299 1.0001
0.750 0.6753 0.01549 0.00747 -0.0859 0.7091 1.0001
1.000 0.7006 0.01548 0.00737 -0.0849 0.6854 1.0001
1.250 0.7266 0.01555 0.00729 -0.0840 0.6611 1.0001
1.500 0.7527 0.01574 0.00729 -0.0832 0.6366 1.0001
1.750 0.7774 0.01606 0.00749 -0.0823 0.6121 1.0001
2.000 0.8028 0.01643 0.00771 -0.0817 0.5911 1.0001
2.250 0.8284 0.01680 0.00796 -0.0812 0.5731 1.0001
2.500 0.8537 0.01717 0.00824 -0.0807 0.5567 1.0001
2.750 0.8786 0.01751 0.00852 -0.0802 0.5413 1.0001
3.000 0.9031 0.01783 0.00879 -0.0795 0.5263 1.0001
3.250 0.9275 0.01816 0.00910 -0.0790 0.5121 1.0001
3.500 0.9520 0.01853 0.00947 -0.0785 0.4996 1.0001
3.750 0.9769 0.01892 0.00985 -0.0780 0.4883 1.0001
4.000 1.0023 0.01931 0.01019 -0.0777 0.4775 1.0001
4.250 1.0273 0.01974 0.01062 -0.0773 0.4667 1.0001
4.500 1.0516 0.02023 0.01118 -0.0769 0.4570 1.0001
4.750 1.0777 0.02073 0.01164 -0.0767 0.4478 1.0001
5.000 1.1016 0.02123 0.01223 -0.0762 0.4374 1.0001
5.250 1.1253 0.02177 0.01285 -0.0757 0.4268 1.0001
5.500 1.1503 0.02232 0.01338 -0.0754 0.4163 1.0001
5.750 1.1740 0.02288 0.01399 -0.0748 0.4050 1.0001
6.000 1.1957 0.02348 0.01473 -0.0740 0.3930 1.0001
6.250 1.2179 0.02409 0.01543 -0.0732 0.3801 1.0001
6.500 1.2394 0.02472 0.01611 -0.0724 0.3658 1.0001
6.750 1.2594 0.02535 0.01682 -0.0712 0.3496 1.0001
7.000 1.2780 0.02597 0.01749 -0.0698 0.3315 1.0001
7.250 1.2959 0.02654 0.01806 -0.0683 0.3129 1.0001
7.500 1.3127 0.02705 0.01855 -0.0667 0.2952 1.0001
7.750 1.3259 0.02746 0.01902 -0.0645 0.2779 1.0001
8.000 1.3370 0.02784 0.01954 -0.0621 0.2614 1.0001
8.250 1.3482 0.02826 0.02007 -0.0597 0.2462 1.0001
8.500 1.3581 0.02874 0.02063 -0.0572 0.2316 1.0001
8.750 1.3662 0.02931 0.02128 -0.0546 0.2172 1.0001
9.000 1.3716 0.03001 0.02203 -0.0517 0.2035 1.0001
9.250 1.3755 0.03093 0.02299 -0.0487 0.1909 1.0001
9.500 1.3779 0.03211 0.02417 -0.0458 0.1782 1.0001
9.750 1.3778 0.03359 0.02567 -0.0430 0.1645 1.0001
10.000 1.3749 0.03541 0.02756 -0.0403 0.1492 1.0001
10.250 1.3673 0.03775 0.03001 -0.0377 0.1304 1.0001
10.500 1.3530 0.04092 0.03314 -0.0353 0.1109 1.0001
10.750 1.3393 0.04454 0.03680 -0.0335 0.0896 1.0001
11.000 1.3290 0.04808 0.04032 -0.0323 0.0776 1.0001
11.250 1.3201 0.05168 0.04389 -0.0316 0.0706 1.0001
11.500 1.3125 0.05528 0.04753 -0.0312 0.0654 1.0001
11.750 1.3053 0.05891 0.05116 -0.0307 0.0617 1.0001
12.000 1.3019 0.06222 0.05457 -0.0303 0.0583 1.0001
12.250 1.2987 0.06550 0.05789 -0.0299 0.0558 1.0001
12.500 1.3004 0.06804 0.06032 -0.0287 0.0534 1.0001
12.750 1.3031 0.07085 0.06333 -0.0280 0.0516 1.0001
13.000 1.3053 0.07378 0.06641 -0.0275 0.0498 1.0001
13.250 1.3070 0.07678 0.06952 -0.0272 0.0481 1.0001
13.500 1.3098 0.07960 0.07236 -0.0269 0.0464 1.0001
13.750 1.3199 0.08177 0.07447 -0.0254 0.0445 1.0001
14.000 1.3139 0.08603 0.07900 -0.0261 0.0439 1.0001
14.250 1.3074 0.09055 0.08379 -0.0269 0.0435 1.0001
14.500 1.2983 0.09555 0.08905 -0.0282 0.0432 1.0001
14.750 1.2861 0.10115 0.09491 -0.0300 0.0431 1.0001
15.000 1.2712 0.10743 0.10144 -0.0326 0.0431 1.0001
15.250 1.2533 0.11451 0.10876 -0.0360 0.0431 1.0001
15.500 1.2328 0.12240 0.11687 -0.0402 0.0433 1.0001
15.750 1.2100 0.13122 0.12591 -0.0453 0.0436 1.0001
16.000 1.1852 0.14101 0.13589 -0.0512 0.0440 1.0001
16.250 1.1592 0.15175 0.14679 -0.0577 0.0445 1.0001
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