N-24 (n24-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-24 (n24-il) Reynolds number: 500,000 Max Cl/Cd: 84.43 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n24-il-500000-n5.txt Download as CSV file: xf-n24-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7466 0.08997 0.08665 -0.0437 0.9014 0.0258
-17.000 -0.8176 0.07430 0.07068 -0.0557 0.8979 0.0257
-16.750 -0.8597 0.06328 0.05944 -0.0647 0.8923 0.0257
-16.500 -0.8893 0.05402 0.04995 -0.0729 0.8859 0.0257
-16.250 -0.9074 0.04581 0.04150 -0.0817 0.8795 0.0257
-16.000 -0.9182 0.03963 0.03507 -0.0892 0.8705 0.0257
-15.750 -0.9246 0.03677 0.03202 -0.0894 0.8624 0.0258
-15.500 -0.9262 0.03485 0.02997 -0.0879 0.8536 0.0259
-15.250 -0.9194 0.03322 0.02819 -0.0866 0.8461 0.0260
-15.000 -0.9081 0.03176 0.02660 -0.0856 0.8399 0.0261
-14.750 -0.8939 0.03043 0.02516 -0.0847 0.8337 0.0262
-14.500 -0.8781 0.02923 0.02383 -0.0836 0.8278 0.0263
-14.250 -0.8606 0.02812 0.02259 -0.0826 0.8224 0.0265
-14.000 -0.8412 0.02707 0.02144 -0.0818 0.8164 0.0266
-13.750 -0.8211 0.02610 0.02034 -0.0810 0.8103 0.0268
-13.500 -0.8002 0.02521 0.01932 -0.0801 0.8051 0.0270
-13.250 -0.7775 0.02436 0.01838 -0.0794 0.7998 0.0272
-13.000 -0.7544 0.02357 0.01749 -0.0788 0.7940 0.0275
-12.750 -0.7309 0.02283 0.01662 -0.0780 0.7882 0.0277
-12.500 -0.7067 0.02211 0.01581 -0.0774 0.7826 0.0279
-12.250 -0.6818 0.02142 0.01502 -0.0769 0.7764 0.0280
-12.000 -0.6567 0.02078 0.01428 -0.0763 0.7706 0.0282
-11.750 -0.6311 0.02019 0.01358 -0.0758 0.7653 0.0284
-11.500 -0.6048 0.01962 0.01294 -0.0753 0.7594 0.0285
-11.250 -0.5783 0.01909 0.01232 -0.0749 0.7532 0.0286
-11.000 -0.5521 0.01853 0.01167 -0.0744 0.7473 0.0288
-10.750 -0.5259 0.01786 0.01097 -0.0741 0.7406 0.0291
-10.500 -0.4992 0.01730 0.01036 -0.0737 0.7336 0.0293
-10.250 -0.4721 0.01681 0.00980 -0.0734 0.7274 0.0296
-10.000 -0.4443 0.01635 0.00930 -0.0731 0.7207 0.0299
-9.750 -0.4164 0.01594 0.00883 -0.0729 0.7138 0.0301
-9.500 -0.3882 0.01556 0.00838 -0.0727 0.7074 0.0305
-9.250 -0.3596 0.01519 0.00797 -0.0726 0.7001 0.0308
-9.000 -0.3311 0.01487 0.00757 -0.0724 0.6927 0.0311
-8.750 -0.3022 0.01455 0.00720 -0.0723 0.6851 0.0315
-8.500 -0.2732 0.01427 0.00685 -0.0723 0.6768 0.0319
-8.250 -0.2440 0.01402 0.00652 -0.0722 0.6695 0.0324
-8.000 -0.2147 0.01376 0.00621 -0.0722 0.6617 0.0329
-7.500 -0.1562 0.01322 0.00557 -0.0723 0.6471 0.0341
-7.250 -0.1267 0.01301 0.00530 -0.0723 0.6393 0.0349
-7.000 -0.0971 0.01282 0.00506 -0.0724 0.6313 0.0357
-6.750 -0.0674 0.01265 0.00483 -0.0725 0.6216 0.0366
-6.500 -0.0378 0.01247 0.00460 -0.0726 0.6123 0.0380
-6.250 -0.0082 0.01229 0.00439 -0.0727 0.6029 0.0406
-6.000 0.0210 0.01206 0.00426 -0.0729 0.5948 0.0559
-5.750 0.0511 0.01201 0.00419 -0.0731 0.5860 0.0656
-5.500 0.0811 0.01199 0.00410 -0.0733 0.5775 0.0699
-5.250 0.1110 0.01193 0.00402 -0.0735 0.5684 0.0738
-5.000 0.1410 0.01193 0.00394 -0.0737 0.5609 0.0765
-4.750 0.1708 0.01183 0.00384 -0.0740 0.5549 0.0791
-4.500 0.2007 0.01177 0.00376 -0.0742 0.5487 0.0819
-4.000 0.2605 0.01170 0.00361 -0.0748 0.5370 0.0854
-3.750 0.2902 0.01164 0.00354 -0.0751 0.5314 0.0877
-3.500 0.3199 0.01160 0.00349 -0.0754 0.5261 0.0904
-3.250 0.3497 0.01157 0.00344 -0.0757 0.5215 0.0939
-3.000 0.3795 0.01151 0.00341 -0.0760 0.5161 0.0988
-2.750 0.4090 0.01147 0.00339 -0.0763 0.5101 0.1068
-2.500 0.4383 0.01143 0.00339 -0.0766 0.5045 0.1261
-2.250 0.4679 0.01136 0.00340 -0.0770 0.4994 0.1477
-2.000 0.4974 0.01133 0.00341 -0.0774 0.4938 0.1652
-1.750 0.5267 0.01133 0.00343 -0.0777 0.4882 0.1811
-1.500 0.5561 0.01131 0.00346 -0.0781 0.4831 0.2000
-1.250 0.5854 0.01128 0.00349 -0.0785 0.4766 0.2216
-1.000 0.6143 0.01130 0.00354 -0.0788 0.4694 0.2456
-0.750 0.6434 0.01128 0.00360 -0.0792 0.4626 0.2757
-0.500 0.6721 0.01125 0.00366 -0.0795 0.4548 0.3158
-0.250 0.7006 0.01125 0.00374 -0.0799 0.4476 0.3568
0.000 0.7289 0.01119 0.00383 -0.0802 0.4390 0.4146
0.250 0.7561 0.01110 0.00394 -0.0804 0.4303 0.4979
0.500 0.7823 0.01092 0.00408 -0.0804 0.4198 0.6180
0.750 0.8070 0.01077 0.00421 -0.0800 0.4087 0.7286
1.250 0.8980 0.01090 0.00469 -0.0881 0.3793 1.0002
1.500 0.9239 0.01114 0.00485 -0.0880 0.3687 1.0002
1.750 0.9494 0.01140 0.00503 -0.0879 0.3597 1.0002
2.000 0.9748 0.01165 0.00522 -0.0878 0.3512 1.0002
2.250 0.9997 0.01192 0.00543 -0.0876 0.3437 1.0002
2.500 1.0248 0.01217 0.00563 -0.0874 0.3367 1.0002
2.750 1.0486 0.01249 0.00588 -0.0871 0.3294 1.0002
3.000 1.0734 0.01273 0.00609 -0.0869 0.3238 1.0002
3.250 1.0976 0.01300 0.00633 -0.0867 0.3184 1.0002
3.500 1.1207 0.01331 0.00660 -0.0863 0.3134 1.0002
3.750 1.1441 0.01360 0.00686 -0.0859 0.3092 1.0002
4.000 1.1677 0.01385 0.00710 -0.0856 0.3048 1.0002
4.250 1.1900 0.01416 0.00739 -0.0851 0.3003 1.0002
4.500 1.2111 0.01451 0.00771 -0.0844 0.2963 1.0002
4.750 1.2316 0.01486 0.00805 -0.0837 0.2928 1.0002
5.000 1.2533 0.01514 0.00835 -0.0831 0.2893 1.0002
5.250 1.2717 0.01550 0.00872 -0.0821 0.2850 1.0002
5.500 1.2872 0.01594 0.00914 -0.0805 0.2810 1.0002
5.750 1.3026 0.01644 0.00963 -0.0791 0.2774 1.0002
6.000 1.3209 0.01686 0.01006 -0.0781 0.2742 1.0002
6.250 1.3402 0.01727 0.01050 -0.0774 0.2710 1.0002
6.500 1.3589 0.01773 0.01097 -0.0766 0.2679 1.0002
6.750 1.3766 0.01825 0.01151 -0.0758 0.2648 1.0002
7.000 1.3934 0.01884 0.01210 -0.0749 0.2617 1.0002
7.250 1.4099 0.01948 0.01274 -0.0741 0.2588 1.0002
7.500 1.4292 0.01997 0.01328 -0.0736 0.2563 1.0002
7.750 1.4475 0.02054 0.01388 -0.0731 0.2533 1.0002
8.000 1.4646 0.02119 0.01455 -0.0725 0.2500 1.0002
8.250 1.4802 0.02194 0.01532 -0.0718 0.2466 1.0002
8.500 1.4945 0.02280 0.01618 -0.0710 0.2433 1.0002
8.750 1.5117 0.02349 0.01692 -0.0705 0.2405 1.0002
9.000 1.5282 0.02423 0.01771 -0.0701 0.2370 1.0002
9.250 1.5428 0.02513 0.01863 -0.0695 0.2329 1.0002
9.500 1.5549 0.02621 0.01972 -0.0687 0.2287 1.0002
9.750 1.5686 0.02720 0.02075 -0.0682 0.2247 1.0002
10.000 1.5822 0.02821 0.02179 -0.0676 0.2195 1.0002
10.250 1.5911 0.02961 0.02318 -0.0668 0.2135 1.0002
10.500 1.6018 0.03088 0.02449 -0.0662 0.2073 1.0002
10.750 1.6089 0.03248 0.02608 -0.0654 0.1996 1.0002
11.000 1.6157 0.03415 0.02775 -0.0647 0.1920 1.0002
11.250 1.6188 0.03619 0.02978 -0.0638 0.1838 1.0002
11.500 1.6239 0.03811 0.03171 -0.0632 0.1755 1.0002
11.750 1.6254 0.04042 0.03401 -0.0625 0.1679 1.0002
12.000 1.6282 0.04266 0.03627 -0.0619 0.1607 1.0002
12.250 1.6288 0.04517 0.03878 -0.0613 0.1547 1.0002
12.500 1.6306 0.04761 0.04126 -0.0609 0.1487 1.0002
12.750 1.6289 0.05047 0.04413 -0.0605 0.1433 1.0002
13.000 1.6295 0.05313 0.04682 -0.0602 0.1379 1.0002
13.250 1.6253 0.05636 0.05007 -0.0599 0.1325 1.0002
13.500 1.6237 0.05937 0.05312 -0.0597 0.1280 1.0002
13.750 1.6221 0.06243 0.05622 -0.0597 0.1241 1.0002
14.000 1.6184 0.06574 0.05957 -0.0596 0.1208 1.0002
14.250 1.6165 0.06890 0.06279 -0.0597 0.1182 1.0002
14.500 1.6163 0.07190 0.06587 -0.0599 0.1158 1.0002
14.750 1.6153 0.07501 0.06903 -0.0601 0.1134 1.0002
15.000 1.6114 0.07853 0.07261 -0.0604 0.1112 1.0002
15.250 1.6055 0.08230 0.07644 -0.0607 0.1089 1.0002
15.500 1.6025 0.08574 0.07995 -0.0611 0.1071 1.0002
15.750 1.6011 0.08904 0.08334 -0.0616 0.1052 1.0002
16.000 1.5992 0.09240 0.08677 -0.0621 0.1031 1.0002
16.250 1.5940 0.09623 0.09066 -0.0627 0.1010 1.0002
16.500 1.5870 0.10032 0.09482 -0.0634 0.0989 1.0002
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Polar data table (+)
Polar graphs
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