N-10 (n10-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 500,000 Max Cl/Cd: 92.03 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n10-il-500000-n5.txt Download as CSV file: xf-n10-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8937 0.04231 0.03964 -0.0833 0.9999 0.0134
-14.500 -0.9267 0.03655 0.03357 -0.0833 0.9999 0.0134
-14.250 -0.9345 0.03337 0.03013 -0.0817 0.9999 0.0137
-14.000 -0.9350 0.03083 0.02733 -0.0798 0.9999 0.0141
-13.750 -0.9276 0.02913 0.02545 -0.0780 0.9999 0.0145
-13.500 -0.9117 0.02849 0.02479 -0.0765 0.9999 0.0149
-13.250 -0.8916 0.02797 0.02423 -0.0757 0.9996 0.0154
-13.000 -0.8618 0.02715 0.02333 -0.0769 0.9977 0.0160
-12.750 -0.8336 0.02601 0.02203 -0.0781 0.9957 0.0167
-12.500 -0.8062 0.02455 0.02033 -0.0793 0.9937 0.0175
-12.250 -0.7798 0.02313 0.01864 -0.0801 0.9908 0.0183
-12.000 -0.7487 0.02268 0.01817 -0.0811 0.9882 0.0189
-11.750 -0.7156 0.02243 0.01790 -0.0824 0.9861 0.0194
-11.500 -0.6838 0.02203 0.01744 -0.0835 0.9836 0.0201
-11.250 -0.6553 0.02135 0.01665 -0.0840 0.9795 0.0209
-11.000 -0.6246 0.02052 0.01563 -0.0850 0.9764 0.0218
-10.750 -0.5924 0.01975 0.01467 -0.0863 0.9740 0.0226
-10.500 -0.5666 0.01899 0.01376 -0.0861 0.9675 0.0232
-10.250 -0.5371 0.01818 0.01289 -0.0869 0.9633 0.0240
-10.000 -0.5087 0.01777 0.01244 -0.0871 0.9571 0.0246
-9.750 -0.4786 0.01734 0.01194 -0.0876 0.9512 0.0254
-9.500 -0.4491 0.01683 0.01134 -0.0881 0.9447 0.0262
-9.250 -0.4198 0.01626 0.01066 -0.0884 0.9372 0.0270
-9.000 -0.3903 0.01574 0.01002 -0.0888 0.9292 0.0278
-8.750 -0.3608 0.01523 0.00938 -0.0891 0.9202 0.0284
-8.500 -0.3322 0.01476 0.00879 -0.0891 0.9088 0.0288
-8.250 -0.3049 0.01399 0.00788 -0.0890 0.8952 0.0295
-8.000 -0.2782 0.01337 0.00716 -0.0888 0.8805 0.0303
-7.750 -0.2515 0.01295 0.00663 -0.0884 0.8663 0.0309
-7.500 -0.2247 0.01259 0.00617 -0.0881 0.8539 0.0315
-7.250 -0.1979 0.01227 0.00575 -0.0877 0.8426 0.0321
-7.000 -0.1710 0.01199 0.00539 -0.0874 0.8316 0.0329
-6.750 -0.1439 0.01172 0.00503 -0.0871 0.8221 0.0337
-6.500 -0.1168 0.01144 0.00467 -0.0868 0.8129 0.0343
-6.250 -0.0896 0.01118 0.00433 -0.0866 0.8029 0.0349
-6.000 -0.0624 0.01095 0.00402 -0.0863 0.7925 0.0354
-5.750 -0.0352 0.01075 0.00373 -0.0860 0.7812 0.0359
-5.500 -0.0077 0.01053 0.00346 -0.0858 0.7702 0.0365
-5.250 0.0196 0.01027 0.00314 -0.0856 0.7593 0.0378
-5.000 0.0470 0.01009 0.00290 -0.0854 0.7474 0.0393
-4.750 0.0745 0.00995 0.00271 -0.0852 0.7333 0.0412
-4.500 0.1018 0.00984 0.00253 -0.0850 0.7165 0.0434
-4.250 0.1290 0.00976 0.00236 -0.0847 0.6972 0.0458
-4.000 0.1558 0.00967 0.00220 -0.0844 0.6771 0.0515
-3.500 0.2100 0.00952 0.00200 -0.0839 0.6457 0.0790
-3.250 0.2376 0.00946 0.00193 -0.0838 0.6346 0.0950
-3.000 0.2650 0.00939 0.00185 -0.0837 0.6241 0.1119
-2.750 0.2921 0.00919 0.00183 -0.0837 0.6137 0.1698
-2.500 0.3197 0.00913 0.00182 -0.0836 0.6036 0.2038
-2.250 0.3473 0.00910 0.00180 -0.0836 0.5929 0.2278
-2.000 0.3745 0.00903 0.00179 -0.0835 0.5804 0.2604
-1.750 0.4016 0.00889 0.00179 -0.0834 0.5660 0.3140
-1.500 0.4279 0.00865 0.00182 -0.0833 0.5486 0.4254
-1.250 0.4537 0.00842 0.00186 -0.0831 0.5254 0.5378
-1.000 0.4779 0.00838 0.00191 -0.0825 0.4833 0.6245
-0.750 0.4987 0.00829 0.00204 -0.0811 0.4375 0.7659
-0.500 0.5171 0.00824 0.00222 -0.0787 0.4082 0.9036
-0.250 0.5529 0.00841 0.00232 -0.0803 0.3877 0.9723
0.000 0.5909 0.00859 0.00240 -0.0827 0.3744 1.0001
0.250 0.6165 0.00877 0.00249 -0.0823 0.3638 1.0001
0.500 0.6423 0.00894 0.00258 -0.0820 0.3537 1.0001
0.750 0.6684 0.00910 0.00268 -0.0817 0.3459 1.0001
1.000 0.6946 0.00925 0.00279 -0.0815 0.3389 1.0001
1.250 0.7207 0.00943 0.00290 -0.0812 0.3323 1.0001
1.500 0.7472 0.00957 0.00301 -0.0811 0.3264 1.0001
1.750 0.7736 0.00972 0.00314 -0.0809 0.3216 1.0001
2.000 0.7998 0.00990 0.00328 -0.0807 0.3173 1.0001
2.250 0.8265 0.01003 0.00341 -0.0806 0.3129 1.0001
2.500 0.8530 0.01018 0.00356 -0.0805 0.3085 1.0001
2.750 0.8792 0.01035 0.00371 -0.0803 0.3046 1.0001
3.000 0.9054 0.01053 0.00388 -0.0801 0.3010 1.0001
3.250 0.9320 0.01067 0.00404 -0.0801 0.2967 1.0001
3.500 0.9583 0.01084 0.00421 -0.0799 0.2919 1.0001
3.750 0.9840 0.01104 0.00440 -0.0797 0.2872 1.0001
4.000 1.0103 0.01119 0.00459 -0.0796 0.2823 1.0001
4.250 1.0363 0.01137 0.00478 -0.0795 0.2759 1.0001
4.500 1.0618 0.01158 0.00498 -0.0793 0.2691 1.0001
4.750 1.0869 0.01182 0.00519 -0.0791 0.2566 1.0001
5.000 1.1117 0.01208 0.00541 -0.0788 0.2380 1.0001
5.250 1.1328 0.01263 0.00574 -0.0780 0.1949 1.0001
5.500 1.1511 0.01342 0.00629 -0.0768 0.1574 1.0001
5.750 1.1721 0.01398 0.00677 -0.0759 0.1407 1.0001
6.000 1.1936 0.01449 0.00722 -0.0752 0.1292 1.0001
6.250 1.2160 0.01489 0.00762 -0.0746 0.1215 1.0001
6.500 1.2378 0.01533 0.00804 -0.0739 0.1146 1.0001
6.750 1.2599 0.01572 0.00845 -0.0733 0.1077 1.0001
7.000 1.2809 0.01619 0.00890 -0.0725 0.0998 1.0001
7.250 1.3009 0.01670 0.00938 -0.0715 0.0871 1.0001
7.500 1.3117 0.01788 0.01025 -0.0693 0.0480 1.0001
8.000 1.3310 0.01996 0.01218 -0.0642 0.0163 1.0001
8.250 1.3453 0.02064 0.01291 -0.0624 0.0146 1.0001
8.500 1.3600 0.02131 0.01365 -0.0607 0.0136 1.0001
8.750 1.3732 0.02208 0.01449 -0.0589 0.0126 1.0001
9.000 1.3848 0.02298 0.01545 -0.0570 0.0117 1.0001
9.250 1.3956 0.02395 0.01650 -0.0552 0.0110 1.0001
9.500 1.4078 0.02484 0.01749 -0.0536 0.0106 1.0001
9.750 1.4188 0.02586 0.01859 -0.0520 0.0102 1.0001
10.000 1.4286 0.02699 0.01980 -0.0504 0.0098 1.0001
10.250 1.4373 0.02825 0.02115 -0.0489 0.0095 1.0001
10.500 1.4448 0.02966 0.02264 -0.0475 0.0091 1.0001
10.750 1.4507 0.03127 0.02434 -0.0461 0.0088 1.0001
11.000 1.4538 0.03320 0.02636 -0.0447 0.0085 1.0001
11.250 1.4538 0.03551 0.02878 -0.0434 0.0083 1.0001
11.500 1.4589 0.03743 0.03081 -0.0425 0.0081 1.0001
11.750 1.4625 0.03957 0.03305 -0.0418 0.0079 1.0001
12.000 1.4646 0.04194 0.03553 -0.0413 0.0077 1.0001
12.250 1.4649 0.04461 0.03831 -0.0409 0.0075 1.0001
12.500 1.4634 0.04759 0.04141 -0.0407 0.0073 1.0001
12.750 1.4607 0.05084 0.04477 -0.0407 0.0072 1.0001
13.000 1.4567 0.05439 0.04844 -0.0409 0.0070 1.0001
13.250 1.4516 0.05819 0.05235 -0.0414 0.0069 1.0001
13.500 1.4448 0.06231 0.05659 -0.0420 0.0068 1.0001
13.750 1.4372 0.06673 0.06113 -0.0429 0.0067 1.0001
14.000 1.4285 0.07144 0.06596 -0.0440 0.0067 1.0001
14.250 1.4185 0.07646 0.07112 -0.0454 0.0066 1.0001
14.500 1.4081 0.08172 0.07649 -0.0469 0.0065 1.0001
14.750 1.3971 0.08717 0.08206 -0.0486 0.0065 1.0001
15.000 1.3857 0.09273 0.08773 -0.0505 0.0064 1.0001
15.250 1.3740 0.09837 0.09349 -0.0523 0.0064 1.0001
15.500 1.3623 0.10407 0.09929 -0.0543 0.0063 1.0001
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Polar data table (+)
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