N-10 (n10-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 200,000 Max Cl/Cd: 68.87 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n10-il-200000-n5.txt Download as CSV file: xf-n10-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4132 0.08818 0.08455 -0.0409 0.9999 0.0269
-11.000 -0.4255 0.08294 0.07938 -0.0428 0.9999 0.0273
-10.750 -0.4464 0.07725 0.07378 -0.0446 0.9999 0.0277
-10.250 -0.5547 0.04024 0.03583 -0.0706 0.9889 0.0288
-10.000 -0.5315 0.03676 0.03206 -0.0737 0.9845 0.0298
-9.750 -0.5062 0.03491 0.03005 -0.0752 0.9786 0.0306
-9.500 -0.4777 0.03279 0.02768 -0.0773 0.9746 0.0317
-9.250 -0.4532 0.03051 0.02507 -0.0784 0.9681 0.0332
-9.000 -0.4256 0.02770 0.02173 -0.0800 0.9636 0.0347
-8.750 -0.3987 0.02559 0.01913 -0.0808 0.9577 0.0358
-8.500 -0.3701 0.02374 0.01697 -0.0817 0.9523 0.0370
-8.250 -0.3380 0.02251 0.01563 -0.0831 0.9486 0.0381
-8.000 -0.3112 0.02148 0.01444 -0.0831 0.9406 0.0390
-7.750 -0.2795 0.02041 0.01319 -0.0841 0.9357 0.0400
-7.500 -0.2500 0.01952 0.01213 -0.0845 0.9292 0.0411
-7.250 -0.2195 0.01871 0.01117 -0.0851 0.9228 0.0426
-7.000 -0.1871 0.01787 0.01016 -0.0859 0.9173 0.0438
-6.750 -0.1576 0.01711 0.00927 -0.0861 0.9083 0.0445
-6.500 -0.1261 0.01643 0.00846 -0.0867 0.8997 0.0452
-6.250 -0.0958 0.01555 0.00755 -0.0871 0.8900 0.0465
-6.000 -0.0666 0.01497 0.00693 -0.0873 0.8792 0.0479
-5.750 -0.0369 0.01454 0.00644 -0.0875 0.8693 0.0500
-5.500 -0.0075 0.01414 0.00597 -0.0876 0.8591 0.0524
-5.250 0.0204 0.01379 0.00553 -0.0874 0.8477 0.0545
-5.000 0.0483 0.01342 0.00509 -0.0872 0.8367 0.0568
-4.750 0.0762 0.01310 0.00472 -0.0871 0.8261 0.0608
-4.500 0.1037 0.01287 0.00442 -0.0868 0.8148 0.0663
-4.250 0.1309 0.01261 0.00416 -0.0866 0.8034 0.0760
-4.000 0.1581 0.01238 0.00392 -0.0863 0.7916 0.0928
-3.750 0.1850 0.01210 0.00368 -0.0860 0.7794 0.1177
-3.500 0.2113 0.01177 0.00358 -0.0857 0.7663 0.1787
-3.250 0.2382 0.01162 0.00347 -0.0854 0.7527 0.2180
-3.000 0.2650 0.01145 0.00336 -0.0852 0.7401 0.2524
-2.750 0.2910 0.01112 0.00329 -0.0849 0.7274 0.3263
-2.500 0.3155 0.01061 0.00326 -0.0844 0.7140 0.4685
-2.250 0.3388 0.01016 0.00323 -0.0834 0.7001 0.6060
-2.000 0.3588 0.00969 0.00328 -0.0810 0.6864 0.7786
-1.750 0.3923 0.00955 0.00328 -0.0813 0.6719 0.9161
-1.500 0.4382 0.00959 0.00319 -0.0849 0.6567 0.9871
-1.250 0.4706 0.00969 0.00313 -0.0859 0.6423 1.0001
-1.000 0.4957 0.00981 0.00312 -0.0853 0.6282 1.0001
-0.750 0.5208 0.00995 0.00313 -0.0847 0.6138 1.0001
-0.500 0.5460 0.01009 0.00316 -0.0842 0.5984 1.0001
-0.250 0.5710 0.01025 0.00320 -0.0836 0.5813 1.0001
0.000 0.5961 0.01040 0.00325 -0.0830 0.5614 1.0001
0.250 0.6209 0.01058 0.00331 -0.0824 0.5372 1.0001
0.500 0.6451 0.01079 0.00337 -0.0817 0.5070 1.0001
1.000 0.6910 0.01141 0.00358 -0.0800 0.4446 1.0001
1.250 0.7145 0.01175 0.00375 -0.0792 0.4234 1.0001
1.500 0.7384 0.01206 0.00394 -0.0786 0.4074 1.0001
1.750 0.7627 0.01237 0.00415 -0.0781 0.3956 1.0001
2.000 0.7877 0.01263 0.00436 -0.0777 0.3858 1.0001
2.250 0.8126 0.01291 0.00458 -0.0773 0.3770 1.0001
2.500 0.8375 0.01319 0.00482 -0.0769 0.3686 1.0001
2.750 0.8625 0.01346 0.00506 -0.0765 0.3614 1.0001
3.000 0.8876 0.01373 0.00531 -0.0762 0.3540 1.0001
3.250 0.9124 0.01403 0.00558 -0.0758 0.3481 1.0001
3.500 0.9379 0.01426 0.00585 -0.0756 0.3424 1.0001
3.750 0.9628 0.01455 0.00613 -0.0752 0.3366 1.0001
4.000 0.9876 0.01484 0.00644 -0.0749 0.3311 1.0001
4.250 1.0127 0.01509 0.00674 -0.0746 0.3249 1.0001
4.500 1.0369 0.01541 0.00706 -0.0742 0.3188 1.0001
4.750 1.0618 0.01567 0.00739 -0.0739 0.3128 1.0001
5.000 1.0862 0.01595 0.00773 -0.0735 0.3067 1.0001
5.250 1.1100 0.01628 0.00808 -0.0731 0.3010 1.0001
5.500 1.1345 0.01653 0.00844 -0.0727 0.2940 1.0001
5.750 1.1573 0.01687 0.00882 -0.0721 0.2861 1.0001
6.000 1.1804 0.01714 0.00917 -0.0716 0.2739 1.0001
6.250 1.2021 0.01747 0.00952 -0.0708 0.2573 1.0001
6.500 1.2230 0.01784 0.00990 -0.0700 0.2324 1.0001
6.750 1.2395 0.01850 0.01038 -0.0685 0.1948 1.0001
7.000 1.2535 0.01938 0.01108 -0.0668 0.1683 1.0001
7.250 1.2686 0.02020 0.01184 -0.0652 0.1534 1.0001
7.500 1.2835 0.02100 0.01261 -0.0636 0.1421 1.0001
7.750 1.2971 0.02177 0.01338 -0.0617 0.1322 1.0001
8.000 1.3109 0.02249 0.01414 -0.0599 0.1220 1.0001
8.250 1.3236 0.02330 0.01498 -0.0580 0.1131 1.0001
8.500 1.3358 0.02416 0.01585 -0.0562 0.1022 1.0001
8.750 1.3489 0.02500 0.01671 -0.0546 0.0839 1.0001
9.000 1.3492 0.02673 0.01814 -0.0517 0.0498 1.0001
9.250 1.3469 0.02872 0.02001 -0.0487 0.0302 1.0001
9.500 1.3488 0.03051 0.02180 -0.0464 0.0237 1.0001
9.750 1.3530 0.03221 0.02356 -0.0445 0.0211 1.0001
10.000 1.3560 0.03409 0.02554 -0.0428 0.0194 1.0001
10.250 1.3611 0.03586 0.02746 -0.0415 0.0185 1.0001
10.500 1.3646 0.03785 0.02959 -0.0402 0.0177 1.0001
10.750 1.3666 0.04006 0.03195 -0.0392 0.0170 1.0001
11.000 1.3666 0.04255 0.03459 -0.0383 0.0164 1.0001
11.250 1.3643 0.04541 0.03758 -0.0376 0.0159 1.0001
11.500 1.3592 0.04870 0.04102 -0.0371 0.0154 1.0001
11.750 1.3507 0.05257 0.04504 -0.0370 0.0149 1.0001
12.000 1.3458 0.05618 0.04880 -0.0372 0.0146 1.0001
12.250 1.3409 0.05990 0.05268 -0.0376 0.0143 1.0001
12.500 1.3345 0.06396 0.05690 -0.0382 0.0140 1.0001
12.750 1.3270 0.06834 0.06144 -0.0391 0.0138 1.0001
13.000 1.3184 0.07300 0.06625 -0.0402 0.0136 1.0001
13.250 1.3095 0.07787 0.07126 -0.0415 0.0134 1.0001
13.500 1.3005 0.08289 0.07642 -0.0430 0.0132 1.0001
13.750 1.2918 0.08795 0.08160 -0.0445 0.0131 1.0001
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Polar data table (+)
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