N-24 (n24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-24 (n24-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.14 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n24-il-1000000-n5.txt Download as CSV file: xf-n24-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-24
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.8981 0.08896 0.08597 -0.0422 0.8930 0.0221
-18.250 -0.9321 0.08021 0.07710 -0.0483 0.8886 0.0221
-18.000 -0.9758 0.07015 0.06688 -0.0555 0.8837 0.0221
-17.750 -1.0266 0.05878 0.05532 -0.0641 0.8783 0.0220
-17.500 -1.0738 0.04598 0.04226 -0.0758 0.8709 0.0220
-17.250 -1.0995 0.03552 0.03144 -0.0890 0.8621 0.0220
-17.000 -1.1061 0.03280 0.02857 -0.0886 0.8540 0.0220
-16.750 -1.1061 0.03106 0.02670 -0.0867 0.8454 0.0221
-16.500 -1.0964 0.02959 0.02512 -0.0855 0.8371 0.0222
-16.250 -1.0832 0.02833 0.02374 -0.0844 0.8281 0.0223
-16.000 -1.0673 0.02721 0.02252 -0.0833 0.8210 0.0223
-15.750 -1.0494 0.02619 0.02142 -0.0823 0.8150 0.0224
-15.500 -1.0301 0.02527 0.02040 -0.0813 0.8091 0.0225
-15.250 -1.0097 0.02440 0.01944 -0.0804 0.8036 0.0226
-15.000 -0.9882 0.02359 0.01855 -0.0796 0.7982 0.0227
-14.750 -0.9658 0.02283 0.01771 -0.0788 0.7924 0.0228
-14.500 -0.9429 0.02212 0.01691 -0.0780 0.7872 0.0230
-14.250 -0.9192 0.02144 0.01616 -0.0773 0.7824 0.0231
-14.000 -0.8949 0.02079 0.01544 -0.0766 0.7768 0.0232
-13.750 -0.8702 0.02018 0.01475 -0.0760 0.7707 0.0233
-13.500 -0.8449 0.01961 0.01410 -0.0753 0.7653 0.0235
-13.250 -0.8191 0.01907 0.01350 -0.0748 0.7600 0.0236
-13.000 -0.7930 0.01856 0.01292 -0.0743 0.7543 0.0238
-12.750 -0.7665 0.01808 0.01236 -0.0738 0.7488 0.0240
-12.500 -0.7398 0.01759 0.01181 -0.0733 0.7437 0.0241
-12.250 -0.7129 0.01712 0.01128 -0.0729 0.7374 0.0243
-12.000 -0.6856 0.01669 0.01077 -0.0725 0.7307 0.0244
-11.750 -0.6581 0.01627 0.01028 -0.0721 0.7246 0.0245
-11.500 -0.6303 0.01588 0.00983 -0.0718 0.7177 0.0246
-11.250 -0.6023 0.01551 0.00939 -0.0715 0.7112 0.0247
-11.000 -0.5740 0.01515 0.00898 -0.0712 0.7052 0.0248
-10.750 -0.5456 0.01482 0.00859 -0.0710 0.6982 0.0249
-10.500 -0.5169 0.01452 0.00822 -0.0708 0.6913 0.0250
-10.250 -0.4890 0.01405 0.00770 -0.0706 0.6846 0.0253
-10.000 -0.4605 0.01367 0.00726 -0.0704 0.6765 0.0255
-9.750 -0.4316 0.01334 0.00687 -0.0703 0.6689 0.0257
-9.500 -0.4025 0.01304 0.00653 -0.0702 0.6603 0.0259
-9.250 -0.3732 0.01279 0.00621 -0.0701 0.6526 0.0262
-9.000 -0.3438 0.01254 0.00592 -0.0701 0.6449 0.0264
-8.750 -0.3143 0.01232 0.00565 -0.0701 0.6369 0.0267
-8.500 -0.2846 0.01210 0.00539 -0.0701 0.6297 0.0269
-8.250 -0.2549 0.01191 0.00515 -0.0701 0.6216 0.0272
-8.000 -0.2250 0.01173 0.00492 -0.0702 0.6137 0.0275
-7.750 -0.1951 0.01157 0.00471 -0.0703 0.6033 0.0278
-7.500 -0.1651 0.01143 0.00451 -0.0704 0.5931 0.0282
-7.250 -0.1351 0.01131 0.00433 -0.0706 0.5828 0.0285
-7.000 -0.1050 0.01118 0.00416 -0.0707 0.5749 0.0288
-6.750 -0.0751 0.01101 0.00395 -0.0709 0.5663 0.0294
-6.500 -0.0450 0.01088 0.00378 -0.0711 0.5585 0.0299
-6.250 -0.0149 0.01076 0.00363 -0.0712 0.5504 0.0305
-6.000 0.0152 0.01068 0.00349 -0.0715 0.5422 0.0312
-5.750 0.0454 0.01057 0.00337 -0.0717 0.5360 0.0319
-5.500 0.0756 0.01050 0.00326 -0.0719 0.5288 0.0327
-5.250 0.1057 0.01041 0.00314 -0.0722 0.5228 0.0345
-5.000 0.1358 0.01028 0.00302 -0.0724 0.5181 0.0381
-4.750 0.1656 0.01009 0.00294 -0.0727 0.5133 0.0623
-4.500 0.1958 0.01006 0.00291 -0.0730 0.5085 0.0670
-4.250 0.2262 0.01006 0.00288 -0.0734 0.5040 0.0698
-4.000 0.2565 0.01000 0.00284 -0.0737 0.4997 0.0723
-3.750 0.2867 0.00997 0.00280 -0.0740 0.4941 0.0746
-3.500 0.3170 0.00999 0.00278 -0.0744 0.4884 0.0762
-3.250 0.3472 0.00997 0.00275 -0.0748 0.4842 0.0774
-3.000 0.3774 0.00992 0.00271 -0.0752 0.4797 0.0796
-2.750 0.4076 0.00990 0.00269 -0.0756 0.4744 0.0813
-2.500 0.4376 0.00992 0.00268 -0.0760 0.4687 0.0829
-2.250 0.4678 0.00991 0.00267 -0.0764 0.4635 0.0846
-2.000 0.4978 0.00991 0.00266 -0.0768 0.4562 0.0877
-1.750 0.5276 0.00993 0.00267 -0.0773 0.4489 0.0923
-1.500 0.5573 0.00988 0.00268 -0.0777 0.4420 0.1100
-1.250 0.5867 0.00986 0.00272 -0.0781 0.4335 0.1419
-1.000 0.6164 0.00986 0.00275 -0.0786 0.4253 0.1586
-0.750 0.6457 0.00993 0.00281 -0.0790 0.4146 0.1734
-0.500 0.6750 0.00998 0.00287 -0.0795 0.4025 0.1918
-0.250 0.7039 0.01007 0.00296 -0.0799 0.3884 0.2127
0.000 0.7324 0.01018 0.00307 -0.0803 0.3736 0.2396
0.250 0.7607 0.01029 0.00319 -0.0807 0.3606 0.2705
0.500 0.7891 0.01037 0.00332 -0.0811 0.3501 0.3054
0.750 0.8173 0.01044 0.00345 -0.0815 0.3419 0.3449
1.000 0.8454 0.01047 0.00358 -0.0818 0.3344 0.3968
1.250 0.8728 0.01048 0.00374 -0.0821 0.3275 0.4704
1.500 0.8995 0.01033 0.00391 -0.0823 0.3213 0.5983
1.750 0.9255 0.01032 0.00410 -0.0823 0.3139 0.6935
2.250 1.0097 0.01014 0.00456 -0.0892 0.3030 0.9994
2.500 1.0384 0.01034 0.00472 -0.0898 0.2991 1.0002
2.750 1.0644 0.01055 0.00489 -0.0897 0.2946 1.0002
3.000 1.0906 0.01072 0.00504 -0.0898 0.2908 1.0002
3.250 1.1166 0.01090 0.00520 -0.0898 0.2863 1.0002
3.500 1.1420 0.01111 0.00538 -0.0897 0.2821 1.0002
3.750 1.1670 0.01134 0.00557 -0.0896 0.2784 1.0002
4.000 1.1922 0.01154 0.00577 -0.0896 0.2754 1.0002
4.250 1.2176 0.01172 0.00594 -0.0895 0.2728 1.0002
4.500 1.2424 0.01193 0.00614 -0.0894 0.2689 1.0002
4.750 1.2664 0.01217 0.00636 -0.0892 0.2651 1.0002
5.000 1.2895 0.01245 0.00662 -0.0889 0.2612 1.0002
5.250 1.3128 0.01270 0.00686 -0.0886 0.2578 1.0002
5.500 1.3361 0.01292 0.00709 -0.0883 0.2550 1.0002
5.750 1.3587 0.01318 0.00735 -0.0880 0.2522 1.0002
6.000 1.3799 0.01348 0.00765 -0.0874 0.2491 1.0002
6.250 1.3976 0.01386 0.00802 -0.0863 0.2459 1.0002
6.500 1.4131 0.01427 0.00843 -0.0847 0.2427 1.0002
6.750 1.4321 0.01461 0.00880 -0.0839 0.2407 1.0002
7.000 1.4512 0.01499 0.00919 -0.0831 0.2380 1.0002
7.250 1.4698 0.01541 0.00962 -0.0823 0.2347 1.0002
7.500 1.4875 0.01591 0.01012 -0.0815 0.2309 1.0002
7.750 1.5044 0.01648 0.01068 -0.0806 0.2268 1.0002
8.000 1.5235 0.01695 0.01117 -0.0801 0.2237 1.0002
8.250 1.5413 0.01750 0.01173 -0.0794 0.2194 1.0002
8.500 1.5564 0.01824 0.01244 -0.0785 0.2137 1.0002
8.750 1.5724 0.01894 0.01314 -0.0778 0.2080 1.0002
9.000 1.5852 0.01985 0.01402 -0.0768 0.1994 1.0002
9.250 1.5975 0.02083 0.01497 -0.0758 0.1907 1.0002
9.500 1.6072 0.02201 0.01611 -0.0746 0.1813 1.0002
9.750 1.6154 0.02333 0.01738 -0.0734 0.1708 1.0002
10.000 1.6230 0.02472 0.01874 -0.0722 0.1608 1.0002
10.250 1.6294 0.02625 0.02024 -0.0710 0.1519 1.0002
10.750 1.6420 0.02943 0.02339 -0.0689 0.1372 1.0002
11.000 1.6466 0.03121 0.02516 -0.0678 0.1309 1.0002
11.250 1.6536 0.03288 0.02684 -0.0671 0.1261 1.0002
11.500 1.6586 0.03474 0.02871 -0.0663 0.1216 1.0002
11.750 1.6655 0.03648 0.03048 -0.0658 0.1182 1.0002
12.000 1.6723 0.03831 0.03234 -0.0653 0.1151 1.0002
12.250 1.6767 0.04038 0.03443 -0.0648 0.1117 1.0002
12.500 1.6800 0.04259 0.03666 -0.0643 0.1083 1.0002
12.750 1.6862 0.04456 0.03868 -0.0640 0.1062 1.0002
13.000 1.6911 0.04670 0.04086 -0.0637 0.1039 1.0002
13.250 1.6946 0.04901 0.04321 -0.0635 0.1014 1.0002
13.500 1.6960 0.05159 0.04582 -0.0632 0.0989 1.0002
13.750 1.6974 0.05419 0.04847 -0.0631 0.0967 1.0002
14.000 1.7024 0.05642 0.05076 -0.0631 0.0952 1.0002
14.250 1.7047 0.05898 0.05338 -0.0631 0.0932 1.0002
14.500 1.7043 0.06189 0.05633 -0.0630 0.0906 1.0002
14.750 1.7013 0.06510 0.05957 -0.0630 0.0878 1.0002
15.000 1.7006 0.06807 0.06260 -0.0631 0.0853 1.0002
15.250 1.6961 0.07153 0.06610 -0.0632 0.0811 1.0002
15.500 1.6869 0.07560 0.07019 -0.0633 0.0760 1.0002
15.750 1.6734 0.08024 0.07484 -0.0635 0.0693 1.0002
16.000 1.6576 0.08523 0.07985 -0.0637 0.0631 1.0002
16.250 1.6421 0.09031 0.08497 -0.0642 0.0581 1.0002
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