N-24 (n24-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: N-24 (n24-il) Reynolds number: 500,000 Max Cl/Cd: 91.55 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n24-il-500000.txt Download as CSV file: xf-n24-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7146 0.06364 0.06053 -0.0697 0.9129 0.0345
-15.250 -0.7700 0.04838 0.04488 -0.0878 0.9041 0.0343
-15.000 -0.7966 0.04282 0.03902 -0.0919 0.8967 0.0342
-14.750 -0.8116 0.03975 0.03572 -0.0907 0.8887 0.0342
-14.500 -0.8150 0.03719 0.03290 -0.0893 0.8829 0.0342
-14.250 -0.8102 0.03500 0.03046 -0.0881 0.8775 0.0343
-14.000 -0.8001 0.03308 0.02831 -0.0870 0.8714 0.0344
-13.750 -0.7876 0.03146 0.02647 -0.0856 0.8663 0.0345
-13.500 -0.7725 0.03008 0.02486 -0.0843 0.8616 0.0347
-13.250 -0.7540 0.02866 0.02326 -0.0835 0.8556 0.0348
-13.000 -0.7374 0.02675 0.02117 -0.0824 0.8500 0.0350
-12.750 -0.7190 0.02527 0.01955 -0.0811 0.8451 0.0353
-12.500 -0.6963 0.02408 0.01832 -0.0805 0.8395 0.0356
-12.250 -0.6731 0.02313 0.01730 -0.0798 0.8338 0.0360
-12.000 -0.6500 0.02229 0.01636 -0.0789 0.8287 0.0363
-11.750 -0.6258 0.02146 0.01544 -0.0781 0.8234 0.0366
-11.500 -0.6005 0.02067 0.01456 -0.0776 0.8171 0.0369
-11.250 -0.5755 0.01994 0.01372 -0.0768 0.8113 0.0372
-11.000 -0.5503 0.01927 0.01294 -0.0761 0.8057 0.0375
-10.750 -0.5234 0.01861 0.01221 -0.0758 0.7994 0.0379
-10.500 -0.4970 0.01800 0.01151 -0.0752 0.7934 0.0382
-10.250 -0.4708 0.01747 0.01086 -0.0746 0.7878 0.0386
-10.000 -0.4428 0.01694 0.01027 -0.0743 0.7813 0.0389
-9.750 -0.4153 0.01644 0.00970 -0.0739 0.7749 0.0392
-9.500 -0.3895 0.01577 0.00896 -0.0733 0.7689 0.0398
-9.250 -0.3615 0.01521 0.00840 -0.0732 0.7617 0.0405
-9.000 -0.3336 0.01477 0.00791 -0.0728 0.7547 0.0412
-8.750 -0.3055 0.01441 0.00748 -0.0726 0.7483 0.0421
-8.500 -0.2764 0.01405 0.00709 -0.0725 0.7409 0.0430
-8.250 -0.2478 0.01374 0.00669 -0.0723 0.7339 0.0438
-8.000 -0.2189 0.01336 0.00629 -0.0722 0.7268 0.0451
-7.750 -0.1898 0.01305 0.00596 -0.0721 0.7189 0.0467
-7.500 -0.1607 0.01281 0.00565 -0.0720 0.7117 0.0487
-7.250 -0.1310 0.01255 0.00543 -0.0721 0.7032 0.0523
-7.000 -0.1015 0.01240 0.00526 -0.0720 0.6954 0.0589
-6.750 -0.0711 0.01232 0.00518 -0.0722 0.6867 0.0682
-6.500 -0.0410 0.01229 0.00508 -0.0722 0.6778 0.0757
-6.250 -0.0112 0.01213 0.00494 -0.0724 0.6686 0.0819
-6.000 0.0185 0.01203 0.00476 -0.0725 0.6594 0.0868
-5.750 0.0484 0.01191 0.00462 -0.0727 0.6504 0.0915
-5.500 0.0783 0.01185 0.00448 -0.0729 0.6414 0.0948
-5.250 0.1079 0.01168 0.00431 -0.0731 0.6330 0.0986
-5.000 0.1378 0.01159 0.00419 -0.0733 0.6246 0.1022
-4.750 0.1676 0.01155 0.00408 -0.0735 0.6175 0.1048
-4.500 0.1975 0.01142 0.00396 -0.0737 0.6100 0.1085
-4.250 0.2272 0.01136 0.00387 -0.0740 0.6034 0.1128
-4.000 0.2572 0.01130 0.00380 -0.0742 0.5973 0.1180
-3.750 0.2871 0.01121 0.00375 -0.0745 0.5907 0.1258
-3.500 0.3166 0.01116 0.00369 -0.0748 0.5843 0.1371
-3.250 0.3465 0.01106 0.00366 -0.0751 0.5783 0.1552
-3.000 0.3762 0.01098 0.00362 -0.0754 0.5721 0.1769
-2.750 0.4055 0.01092 0.00360 -0.0757 0.5664 0.2009
-2.500 0.4351 0.01084 0.00361 -0.0761 0.5610 0.2271
-2.250 0.4647 0.01075 0.00362 -0.0765 0.5553 0.2573
-2.000 0.4939 0.01070 0.00362 -0.0768 0.5493 0.2924
-1.750 0.5229 0.01062 0.00365 -0.0771 0.5436 0.3363
-1.500 0.5520 0.01046 0.00369 -0.0775 0.5377 0.3959
-1.250 0.5801 0.01028 0.00374 -0.0777 0.5318 0.4787
-1.000 0.6064 0.01000 0.00383 -0.0775 0.5263 0.6109
-0.750 0.6632 0.00918 0.00400 -0.0834 0.5195 0.9802
-0.500 0.7095 0.00938 0.00411 -0.0875 0.5124 1.0002
-0.250 0.7374 0.00951 0.00416 -0.0876 0.5061 1.0002
0.000 0.7654 0.00959 0.00420 -0.0878 0.4990 1.0002
0.250 0.7928 0.00974 0.00426 -0.0878 0.4919 1.0002
0.500 0.8208 0.00984 0.00433 -0.0880 0.4849 1.0002
0.750 0.8483 0.00997 0.00440 -0.0881 0.4770 1.0002
1.000 0.8757 0.01012 0.00449 -0.0882 0.4693 1.0002
1.250 0.9030 0.01025 0.00458 -0.0883 0.4600 1.0002
1.500 0.9299 0.01043 0.00469 -0.0884 0.4504 1.0002
1.750 0.9565 0.01061 0.00481 -0.0884 0.4391 1.0002
2.000 0.9830 0.01080 0.00494 -0.0885 0.4275 1.0002
2.250 1.0087 0.01104 0.00511 -0.0884 0.4157 1.0002
2.500 1.0339 0.01131 0.00529 -0.0883 0.4032 1.0002
2.750 1.0592 0.01157 0.00549 -0.0882 0.3917 1.0002
3.000 1.0835 0.01189 0.00573 -0.0880 0.3812 1.0002
3.250 1.1074 0.01221 0.00597 -0.0877 0.3711 1.0002
3.500 1.1313 0.01253 0.00624 -0.0874 0.3624 1.0002
3.750 1.1544 0.01287 0.00652 -0.0870 0.3543 1.0002
4.000 1.1772 0.01321 0.00681 -0.0866 0.3478 1.0002
4.250 1.2007 0.01350 0.00709 -0.0863 0.3419 1.0002
4.500 1.2221 0.01389 0.00742 -0.0857 0.3360 1.0002
4.750 1.2436 0.01425 0.00776 -0.0851 0.3309 1.0002
5.000 1.2661 0.01454 0.00806 -0.0847 0.3266 1.0002
5.250 1.2866 0.01490 0.00841 -0.0839 0.3220 1.0002
5.500 1.3041 0.01539 0.00885 -0.0828 0.3171 1.0002
5.750 1.3220 0.01576 0.00924 -0.0816 0.3133 1.0002
6.000 1.3398 0.01612 0.00964 -0.0805 0.3097 1.0002
6.250 1.3567 0.01657 0.01009 -0.0793 0.3060 1.0002
6.500 1.3727 0.01710 0.01059 -0.0780 0.3023 1.0002
6.750 1.3885 0.01771 0.01117 -0.0768 0.2983 1.0002
7.000 1.4082 0.01810 0.01163 -0.0762 0.2956 1.0002
7.250 1.4271 0.01855 0.01213 -0.0756 0.2925 1.0002
7.500 1.4449 0.01909 0.01268 -0.0748 0.2892 1.0002
7.750 1.4613 0.01971 0.01330 -0.0740 0.2858 1.0002
8.000 1.4764 0.02045 0.01401 -0.0730 0.2821 1.0002
8.250 1.4949 0.02098 0.01461 -0.0725 0.2795 1.0002
8.500 1.5128 0.02156 0.01525 -0.0720 0.2765 1.0002
8.750 1.5298 0.02221 0.01593 -0.0714 0.2731 1.0002
9.000 1.5448 0.02298 0.01673 -0.0707 0.2697 1.0002
9.250 1.5581 0.02389 0.01761 -0.0698 0.2660 1.0002
9.500 1.5743 0.02463 0.01842 -0.0693 0.2631 1.0002
9.750 1.5907 0.02538 0.01925 -0.0689 0.2596 1.0002
10.000 1.6046 0.02629 0.02020 -0.0684 0.2555 1.0002
10.250 1.6152 0.02745 0.02134 -0.0675 0.2511 1.0002
10.500 1.6282 0.02848 0.02243 -0.0670 0.2467 1.0002
10.750 1.6416 0.02952 0.02353 -0.0666 0.2416 1.0002
11.000 1.6505 0.03089 0.02491 -0.0659 0.2363 1.0002
11.250 1.6603 0.03224 0.02630 -0.0653 0.2312 1.0002
11.500 1.6711 0.03356 0.02767 -0.0649 0.2253 1.0002
11.750 1.6761 0.03537 0.02947 -0.0641 0.2195 1.0002
12.000 1.6859 0.03686 0.03102 -0.0638 0.2137 1.0002
12.250 1.6909 0.03880 0.03299 -0.0632 0.2070 1.0002
12.500 1.6957 0.04080 0.03501 -0.0628 0.2006 1.0002
12.750 1.6984 0.04304 0.03727 -0.0623 0.1932 1.0002
13.000 1.6993 0.04552 0.03976 -0.0618 0.1861 1.0002
13.250 1.6980 0.04828 0.04254 -0.0613 0.1785 1.0002
13.500 1.6972 0.05103 0.04530 -0.0610 0.1718 1.0002
13.750 1.6940 0.05407 0.04836 -0.0606 0.1654 1.0002
14.000 1.6912 0.05712 0.05143 -0.0604 0.1600 1.0002
14.250 1.6891 0.06015 0.05451 -0.0602 0.1548 1.0002
14.500 1.6816 0.06383 0.05820 -0.0601 0.1502 1.0002
14.750 1.6810 0.06675 0.06119 -0.0601 0.1465 1.0002
15.000 1.6785 0.06992 0.06441 -0.0602 0.1427 1.0002
15.250 1.6716 0.07368 0.06820 -0.0603 0.1393 1.0002
15.500 1.6657 0.07734 0.07190 -0.0605 0.1363 1.0002
15.750 1.6662 0.08023 0.07488 -0.0608 0.1336 1.0002
16.000 1.6616 0.08381 0.07851 -0.0611 0.1307 1.0002
16.250 1.6547 0.08770 0.08244 -0.0616 0.1279 1.0002
|
Polar data table (+)
Polar graphs
<< Back to N-24 (n24-il)