N-24 (n24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: N-24 (n24-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.68 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n24-il-1000000.txt Download as CSV file: xf-n24-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8116 0.08480 0.08226 -0.0461 0.9139 0.0263
-17.250 -0.8836 0.06865 0.06584 -0.0594 0.9104 0.0261
-17.000 -0.9263 0.05716 0.05412 -0.0697 0.9046 0.0260
-16.750 -0.9527 0.04779 0.04451 -0.0793 0.8984 0.0260
-16.500 -0.9675 0.04067 0.03716 -0.0881 0.8906 0.0260
-16.250 -0.9779 0.03709 0.03338 -0.0898 0.8829 0.0261
-16.000 -0.9849 0.03496 0.03109 -0.0880 0.8759 0.0261
-15.750 -0.9812 0.03322 0.02920 -0.0865 0.8693 0.0262
-15.500 -0.9724 0.03170 0.02752 -0.0851 0.8634 0.0263
-15.250 -0.9590 0.03034 0.02604 -0.0840 0.8578 0.0264
-15.000 -0.9434 0.02914 0.02471 -0.0829 0.8520 0.0265
-14.750 -0.9262 0.02809 0.02352 -0.0818 0.8465 0.0266
-14.500 -0.9068 0.02715 0.02246 -0.0809 0.8412 0.0267
-14.250 -0.8859 0.02631 0.02151 -0.0800 0.8355 0.0268
-14.000 -0.8697 0.02463 0.01967 -0.0788 0.8297 0.0269
-13.750 -0.8516 0.02313 0.01805 -0.0778 0.8244 0.0272
-13.500 -0.8300 0.02202 0.01689 -0.0769 0.8194 0.0274
-13.250 -0.8072 0.02114 0.01595 -0.0762 0.8139 0.0276
-13.000 -0.7835 0.02039 0.01512 -0.0754 0.8085 0.0278
-12.750 -0.7586 0.01970 0.01438 -0.0748 0.8035 0.0280
-12.500 -0.7331 0.01906 0.01369 -0.0742 0.7978 0.0282
-12.250 -0.7074 0.01849 0.01305 -0.0736 0.7920 0.0285
-12.000 -0.6811 0.01796 0.01244 -0.0731 0.7866 0.0288
-11.750 -0.6544 0.01740 0.01183 -0.0727 0.7813 0.0290
-11.500 -0.6276 0.01687 0.01124 -0.0722 0.7756 0.0292
-11.250 -0.6007 0.01639 0.01067 -0.0718 0.7698 0.0295
-11.000 -0.5731 0.01590 0.01014 -0.0714 0.7646 0.0297
-10.750 -0.5453 0.01545 0.00963 -0.0711 0.7586 0.0299
-10.500 -0.5175 0.01504 0.00914 -0.0708 0.7522 0.0301
-10.250 -0.4891 0.01465 0.00870 -0.0705 0.7463 0.0303
-10.000 -0.4606 0.01429 0.00829 -0.0703 0.7395 0.0305
-9.750 -0.4319 0.01399 0.00792 -0.0701 0.7329 0.0306
-9.500 -0.4044 0.01336 0.00724 -0.0698 0.7268 0.0310
-9.250 -0.3762 0.01289 0.00672 -0.0696 0.7199 0.0315
-9.000 -0.3474 0.01254 0.00630 -0.0695 0.7127 0.0319
-8.750 -0.3181 0.01221 0.00595 -0.0694 0.7060 0.0323
-8.500 -0.2887 0.01194 0.00563 -0.0694 0.6983 0.0328
-8.250 -0.2591 0.01170 0.00533 -0.0694 0.6908 0.0333
-8.000 -0.2294 0.01146 0.00506 -0.0694 0.6824 0.0339
-7.750 -0.1996 0.01128 0.00481 -0.0695 0.6737 0.0344
-7.500 -0.1696 0.01108 0.00456 -0.0696 0.6642 0.0348
-7.250 -0.1399 0.01083 0.00426 -0.0696 0.6547 0.0358
-7.000 -0.1100 0.01062 0.00401 -0.0697 0.6451 0.0368
-6.750 -0.0799 0.01046 0.00380 -0.0699 0.6354 0.0379
-6.500 -0.0498 0.01032 0.00362 -0.0701 0.6254 0.0392
-6.250 -0.0198 0.01014 0.00342 -0.0702 0.6166 0.0429
-6.000 0.0100 0.00994 0.00333 -0.0704 0.6071 0.0622
-5.750 0.0405 0.00992 0.00329 -0.0707 0.5979 0.0702
-5.500 0.0711 0.00991 0.00326 -0.0710 0.5893 0.0749
-5.250 0.1014 0.00988 0.00319 -0.0713 0.5820 0.0780
-5.000 0.1318 0.00980 0.00312 -0.0716 0.5759 0.0815
-4.750 0.1622 0.00979 0.00307 -0.0719 0.5690 0.0837
-4.500 0.1925 0.00977 0.00301 -0.0722 0.5624 0.0854
-4.250 0.2227 0.00967 0.00291 -0.0725 0.5565 0.0882
-4.000 0.2530 0.00962 0.00284 -0.0729 0.5505 0.0906
-3.750 0.2832 0.00961 0.00280 -0.0732 0.5448 0.0929
-3.500 0.3136 0.00956 0.00275 -0.0736 0.5402 0.0947
-3.250 0.3438 0.00950 0.00269 -0.0740 0.5349 0.0988
-3.000 0.3739 0.00948 0.00267 -0.0744 0.5290 0.1040
-2.750 0.4039 0.00939 0.00265 -0.0747 0.5242 0.1191
-2.500 0.4339 0.00929 0.00264 -0.0752 0.5191 0.1481
-2.250 0.4638 0.00924 0.00264 -0.0756 0.5138 0.1683
-2.000 0.4937 0.00924 0.00266 -0.0760 0.5084 0.1865
-1.750 0.5237 0.00916 0.00267 -0.0765 0.5042 0.2105
-1.500 0.5535 0.00908 0.00269 -0.0769 0.4990 0.2438
-1.250 0.5831 0.00905 0.00272 -0.0774 0.4930 0.2784
-1.000 0.6127 0.00897 0.00276 -0.0778 0.4877 0.3220
-0.500 0.6711 0.00876 0.00286 -0.0787 0.4752 0.4483
-0.250 0.6996 0.00858 0.00293 -0.0790 0.4693 0.5425
0.000 0.7269 0.00831 0.00302 -0.0791 0.4626 0.6749
0.250 0.7766 0.00778 0.00322 -0.0839 0.4535 0.9865
0.500 0.8261 0.00796 0.00335 -0.0888 0.4433 1.0002
0.750 0.8540 0.00811 0.00342 -0.0890 0.4331 1.0002
1.000 0.8817 0.00828 0.00350 -0.0892 0.4208 1.0002
1.250 0.9094 0.00844 0.00360 -0.0894 0.4083 1.0002
1.500 0.9366 0.00865 0.00372 -0.0896 0.3946 1.0002
1.750 0.9634 0.00889 0.00387 -0.0897 0.3807 1.0002
2.000 0.9897 0.00917 0.00404 -0.0897 0.3667 1.0002
2.250 1.0161 0.00941 0.00421 -0.0898 0.3545 1.0002
2.500 1.0423 0.00966 0.00439 -0.0899 0.3443 1.0002
2.750 1.0680 0.00993 0.00458 -0.0899 0.3354 1.0002
3.000 1.0943 0.01013 0.00476 -0.0899 0.3295 1.0002
3.250 1.1203 0.01034 0.00493 -0.0900 0.3243 1.0002
3.500 1.1454 0.01061 0.00515 -0.0899 0.3183 1.0002
3.750 1.1710 0.01082 0.00534 -0.0898 0.3135 1.0002
4.000 1.1966 0.01101 0.00552 -0.0899 0.3093 1.0002
4.250 1.2214 0.01125 0.00573 -0.0898 0.3052 1.0002
4.500 1.2451 0.01155 0.00599 -0.0895 0.3002 1.0002
4.750 1.2700 0.01175 0.00620 -0.0894 0.2966 1.0002
5.000 1.2948 0.01195 0.00639 -0.0894 0.2928 1.0002
5.250 1.3185 0.01220 0.00664 -0.0891 0.2890 1.0002
5.500 1.3408 0.01251 0.00692 -0.0887 0.2852 1.0002
5.750 1.3620 0.01285 0.00724 -0.0881 0.2814 1.0002
6.000 1.3858 0.01304 0.00747 -0.0879 0.2795 1.0002
6.250 1.4082 0.01329 0.00774 -0.0876 0.2769 1.0002
6.500 1.4281 0.01361 0.00806 -0.0868 0.2740 1.0002
6.750 1.4437 0.01401 0.00846 -0.0853 0.2710 1.0002
7.000 1.4591 0.01448 0.00893 -0.0839 0.2675 1.0002
7.250 1.4765 0.01493 0.00939 -0.0829 0.2646 1.0002
7.500 1.4975 0.01525 0.00974 -0.0824 0.2625 1.0002
7.750 1.5173 0.01564 0.01016 -0.0819 0.2597 1.0002
8.000 1.5361 0.01610 0.01063 -0.0813 0.2566 1.0002
8.250 1.5531 0.01666 0.01119 -0.0805 0.2532 1.0002
8.500 1.5684 0.01735 0.01187 -0.0795 0.2490 1.0002
8.750 1.5893 0.01774 0.01230 -0.0793 0.2461 1.0002
9.000 1.6080 0.01827 0.01285 -0.0789 0.2420 1.0002
9.250 1.6234 0.01900 0.01358 -0.0781 0.2373 1.0002
9.500 1.6389 0.01975 0.01432 -0.0775 0.2321 1.0002
9.750 1.6560 0.02041 0.01500 -0.0770 0.2266 1.0002
10.000 1.6688 0.02137 0.01594 -0.0762 0.2205 1.0002
10.250 1.6838 0.02221 0.01680 -0.0756 0.2158 1.0002
10.500 1.6979 0.02311 0.01772 -0.0750 0.2102 1.0002
10.750 1.7074 0.02436 0.01894 -0.0740 0.2034 1.0002
11.000 1.7195 0.02545 0.02004 -0.0734 0.1964 1.0002
11.250 1.7262 0.02696 0.02153 -0.0723 0.1881 1.0002
11.500 1.7331 0.02849 0.02303 -0.0713 0.1792 1.0002
11.750 1.7379 0.03021 0.02474 -0.0703 0.1710 1.0002
12.000 1.7392 0.03229 0.02679 -0.0691 0.1623 1.0002
12.250 1.7433 0.03420 0.02870 -0.0683 0.1545 1.0002
12.500 1.7440 0.03645 0.03094 -0.0673 0.1472 1.0002
12.750 1.7462 0.03865 0.03315 -0.0666 0.1411 1.0002
13.000 1.7467 0.04107 0.03557 -0.0659 0.1358 1.0002
13.250 1.7500 0.04327 0.03781 -0.0654 0.1319 1.0002
13.500 1.7502 0.04581 0.04036 -0.0649 0.1280 1.0002
13.750 1.7508 0.04836 0.04295 -0.0645 0.1244 1.0002
14.000 1.7546 0.05066 0.04530 -0.0643 0.1221 1.0002
14.250 1.7557 0.05323 0.04793 -0.0641 0.1196 1.0002
14.500 1.7547 0.05607 0.05080 -0.0639 0.1170 1.0002
14.750 1.7515 0.05919 0.05396 -0.0637 0.1141 1.0002
15.000 1.7529 0.06186 0.05670 -0.0637 0.1123 1.0002
15.250 1.7542 0.06454 0.05944 -0.0638 0.1103 1.0002
15.500 1.7525 0.06758 0.06253 -0.0638 0.1081 1.0002
15.750 1.7473 0.07107 0.06607 -0.0639 0.1060 1.0002
16.000 1.7401 0.07485 0.06990 -0.0640 0.1034 1.0002
16.250 1.7404 0.07776 0.07287 -0.0643 0.1017 1.0002
16.500 1.7385 0.08093 0.07612 -0.0647 0.0998 1.0002
16.750 1.7351 0.08430 0.07954 -0.0650 0.0975 1.0002
17.000 1.7261 0.08844 0.08373 -0.0655 0.0951 1.0002
17.250 1.7158 0.09282 0.08817 -0.0660 0.0926 1.0002
17.500 1.7155 0.09586 0.09128 -0.0666 0.0904 1.0002
17.750 1.7074 0.09999 0.09547 -0.0673 0.0873 1.0002
18.000 1.6943 0.10483 0.10035 -0.0681 0.0841 1.0002
18.250 1.6881 0.10878 0.10435 -0.0690 0.0805 1.0002
18.500 1.6718 0.11420 0.10979 -0.0702 0.0754 1.0002
18.750 1.6562 0.11955 0.11518 -0.0715 0.0702 1.0002
19.000 1.6371 0.12551 0.12117 -0.0730 0.0650 1.0002
|
Polar data table (+)
Polar graphs
<< Back to N-24 (n24-il)