NACA 4415 (naca4415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.09 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4415-il-1000000-n5.txt Download as CSV file: xf-naca4415-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4415
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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8402 0.07985 0.07672 -0.0731 1.0000 0.0111
-16.250 -0.8942 0.06955 0.06628 -0.0782 1.0000 0.0110
-16.000 -0.9934 0.05102 0.04744 -0.0906 0.9993 0.0109
-15.750 -1.0322 0.03732 0.03339 -0.1051 0.9971 0.0107
-15.500 -1.0339 0.03203 0.02792 -0.1119 0.9947 0.0108
-15.250 -1.0284 0.02915 0.02490 -0.1148 0.9923 0.0109
-15.000 -1.0218 0.02713 0.02277 -0.1157 0.9890 0.0110
-14.750 -1.0126 0.02532 0.02085 -0.1163 0.9859 0.0112
-14.500 -0.9964 0.02402 0.01946 -0.1168 0.9838 0.0113
-14.250 -0.9869 0.02297 0.01834 -0.1152 0.9795 0.0114
-14.000 -0.9731 0.02204 0.01734 -0.1141 0.9751 0.0117
-13.750 -0.9514 0.02112 0.01637 -0.1142 0.9728 0.0120
-13.500 -0.9265 0.02029 0.01548 -0.1148 0.9713 0.0122
-13.250 -0.9128 0.01960 0.01473 -0.1128 0.9656 0.0124
-13.000 -0.8907 0.01893 0.01400 -0.1125 0.9623 0.0127
-12.750 -0.8653 0.01826 0.01327 -0.1127 0.9600 0.0129
-12.250 -0.8176 0.01708 0.01196 -0.1123 0.9526 0.0133
-12.000 -0.7918 0.01645 0.01128 -0.1125 0.9487 0.0137
-11.750 -0.7611 0.01583 0.01061 -0.1137 0.9461 0.0140
-11.500 -0.7268 0.01524 0.00999 -0.1156 0.9440 0.0145
-11.250 -0.7000 0.01477 0.00947 -0.1157 0.9387 0.0149
-11.000 -0.6683 0.01431 0.00896 -0.1169 0.9338 0.0154
-10.750 -0.6325 0.01385 0.00844 -0.1189 0.9295 0.0160
-10.500 -0.6052 0.01343 0.00798 -0.1191 0.9222 0.0167
-10.250 -0.5746 0.01302 0.00752 -0.1199 0.9150 0.0175
-10.000 -0.5475 0.01268 0.00714 -0.1200 0.9076 0.0184
-9.750 -0.5204 0.01238 0.00678 -0.1199 0.8989 0.0192
-9.500 -0.4955 0.01205 0.00641 -0.1195 0.8900 0.0204
-9.250 -0.4699 0.01179 0.00609 -0.1191 0.8804 0.0215
-9.000 -0.4461 0.01155 0.00580 -0.1183 0.8709 0.0226
-8.750 -0.4221 0.01129 0.00549 -0.1175 0.8612 0.0240
-8.500 -0.3988 0.01108 0.00523 -0.1166 0.8511 0.0255
-8.250 -0.3755 0.01086 0.00496 -0.1156 0.8416 0.0271
-8.000 -0.3523 0.01066 0.00472 -0.1146 0.8317 0.0289
-7.750 -0.3291 0.01046 0.00447 -0.1136 0.8224 0.0311
-7.500 -0.3061 0.01028 0.00425 -0.1126 0.8122 0.0334
-7.250 -0.2830 0.01007 0.00402 -0.1115 0.8031 0.0365
-7.000 -0.2601 0.00990 0.00382 -0.1104 0.7932 0.0400
-6.750 -0.2367 0.00973 0.00362 -0.1095 0.7837 0.0442
-6.250 -0.1903 0.00940 0.00327 -0.1074 0.7645 0.0554
-6.000 -0.1673 0.00927 0.00311 -0.1063 0.7547 0.0613
-5.750 -0.1438 0.00913 0.00297 -0.1053 0.7439 0.0676
-5.500 -0.1203 0.00902 0.00283 -0.1042 0.7341 0.0732
-5.250 -0.0968 0.00893 0.00272 -0.1032 0.7234 0.0793
-5.000 -0.0733 0.00882 0.00260 -0.1022 0.7126 0.0858
-4.750 -0.0499 0.00876 0.00249 -0.1011 0.7019 0.0908
-4.500 -0.0261 0.00867 0.00240 -0.1002 0.6909 0.0964
-4.250 -0.0023 0.00862 0.00231 -0.0992 0.6799 0.1009
-3.750 0.0451 0.00851 0.00214 -0.0971 0.6576 0.1123
-3.500 0.0682 0.00845 0.00207 -0.0960 0.6465 0.1205
-3.250 0.0917 0.00840 0.00201 -0.0950 0.6356 0.1294
-3.000 0.1157 0.00836 0.00195 -0.0941 0.6258 0.1371
-2.500 0.1631 0.00830 0.00186 -0.0920 0.6044 0.1519
-2.250 0.1866 0.00828 0.00182 -0.0910 0.5952 0.1598
-2.000 0.2109 0.00826 0.00178 -0.0901 0.5857 0.1683
-1.750 0.2343 0.00824 0.00176 -0.0891 0.5763 0.1770
-1.500 0.2582 0.00824 0.00173 -0.0881 0.5665 0.1860
-1.250 0.2817 0.00821 0.00172 -0.0871 0.5584 0.1978
-1.000 0.3055 0.00820 0.00171 -0.0861 0.5496 0.2088
-0.750 0.3290 0.00820 0.00170 -0.0851 0.5415 0.2204
-0.500 0.3527 0.00818 0.00170 -0.0841 0.5331 0.2339
-0.250 0.3756 0.00818 0.00171 -0.0830 0.5254 0.2486
0.000 0.3995 0.00817 0.00172 -0.0820 0.5175 0.2620
0.750 0.4672 0.00817 0.00177 -0.0784 0.4950 0.3120
1.000 0.4888 0.00816 0.00180 -0.0770 0.4884 0.3329
1.250 0.5103 0.00815 0.00183 -0.0756 0.4804 0.3548
1.500 0.5307 0.00814 0.00187 -0.0740 0.4733 0.3849
1.750 0.5519 0.00808 0.00191 -0.0725 0.4659 0.4264
2.000 0.5717 0.00803 0.00197 -0.0708 0.4588 0.4745
2.250 0.5910 0.00794 0.00205 -0.0690 0.4518 0.5425
2.500 0.6106 0.00788 0.00214 -0.0672 0.4453 0.6005
2.750 0.6280 0.00785 0.00225 -0.0649 0.4382 0.6611
3.000 0.6472 0.00781 0.00234 -0.0630 0.4318 0.7095
3.250 0.6642 0.00779 0.00245 -0.0606 0.4245 0.7614
3.500 0.6854 0.00758 0.00261 -0.0590 0.4177 0.8827
3.750 0.8535 0.00822 0.00319 -0.0906 0.3873 0.9665
4.000 0.8799 0.00838 0.00332 -0.0902 0.3788 0.9830
4.250 0.9084 0.00860 0.00348 -0.0905 0.3691 0.9918
4.500 0.9455 0.00881 0.00366 -0.0926 0.3597 0.9976
4.750 0.9873 0.00905 0.00383 -0.0959 0.3491 1.0000
5.000 1.0010 0.00920 0.00394 -0.0929 0.3402 1.0000
5.250 1.0162 0.00934 0.00405 -0.0902 0.3315 1.0000
5.500 1.0316 0.00951 0.00419 -0.0877 0.3229 1.0000
5.750 1.0482 0.00967 0.00432 -0.0854 0.3146 1.0000
6.000 1.0636 0.00989 0.00449 -0.0829 0.3050 1.0000
6.250 1.0800 0.01010 0.00466 -0.0806 0.2937 1.0000
6.500 1.0964 0.01034 0.00486 -0.0784 0.2833 1.0000
6.750 1.1121 0.01061 0.00508 -0.0760 0.2726 1.0000
7.000 1.1292 0.01085 0.00529 -0.0740 0.2625 1.0000
7.250 1.1454 0.01116 0.00554 -0.0719 0.2509 1.0000
7.500 1.1611 0.01149 0.00582 -0.0697 0.2394 1.0000
7.750 1.1769 0.01183 0.00611 -0.0675 0.2277 1.0000
8.000 1.1922 0.01222 0.00644 -0.0654 0.2142 1.0000
8.250 1.2072 0.01263 0.00679 -0.0632 0.2015 1.0000
8.500 1.2218 0.01308 0.00718 -0.0610 0.1884 1.0000
8.750 1.2347 0.01362 0.00763 -0.0586 0.1728 1.0000
9.000 1.2488 0.01412 0.00807 -0.0565 0.1612 1.0000
9.250 1.2626 0.01465 0.00855 -0.0544 0.1507 1.0000
9.500 1.2774 0.01516 0.00902 -0.0524 0.1420 1.0000
9.750 1.2933 0.01562 0.00947 -0.0508 0.1368 1.0000
10.000 1.3085 0.01613 0.00997 -0.0490 0.1304 1.0000
10.250 1.3232 0.01669 0.01051 -0.0473 0.1249 1.0000
10.500 1.3384 0.01723 0.01105 -0.0456 0.1195 1.0000
10.750 1.3531 0.01781 0.01163 -0.0440 0.1152 1.0000
11.000 1.3675 0.01842 0.01225 -0.0424 0.1106 1.0000
11.250 1.3817 0.01907 0.01289 -0.0408 0.1057 1.0000
11.500 1.3940 0.01983 0.01364 -0.0390 0.1007 1.0000
11.750 1.4075 0.02055 0.01437 -0.0375 0.0959 1.0000
12.000 1.4185 0.02144 0.01524 -0.0358 0.0908 1.0000
12.250 1.4303 0.02231 0.01613 -0.0342 0.0852 1.0000
12.500 1.4398 0.02335 0.01714 -0.0325 0.0794 1.0000
12.750 1.4489 0.02444 0.01823 -0.0308 0.0737 1.0000
13.000 1.4577 0.02560 0.01939 -0.0293 0.0686 1.0000
13.250 1.4646 0.02692 0.02071 -0.0276 0.0636 1.0000
13.500 1.4723 0.02824 0.02203 -0.0262 0.0586 1.0000
13.750 1.4785 0.02971 0.02351 -0.0247 0.0545 1.0000
14.000 1.4845 0.03125 0.02507 -0.0233 0.0507 1.0000
14.250 1.4904 0.03285 0.02669 -0.0221 0.0477 1.0000
14.500 1.4964 0.03448 0.02835 -0.0210 0.0452 1.0000
14.750 1.5008 0.03630 0.03020 -0.0199 0.0427 1.0000
15.000 1.5066 0.03806 0.03200 -0.0190 0.0408 1.0000
15.250 1.5109 0.04001 0.03398 -0.0182 0.0393 1.0000
15.500 1.5144 0.04207 0.03609 -0.0174 0.0376 1.0000
15.750 1.5193 0.04404 0.03812 -0.0167 0.0366 1.0000
16.000 1.5229 0.04619 0.04032 -0.0162 0.0354 1.0000
16.250 1.5250 0.04854 0.04271 -0.0157 0.0342 1.0000
16.500 1.5263 0.05101 0.04524 -0.0152 0.0333 1.0000
16.750 1.5287 0.05341 0.04771 -0.0150 0.0325 1.0000
17.000 1.5306 0.05592 0.05029 -0.0147 0.0318 1.0000
17.250 1.5311 0.05862 0.05304 -0.0146 0.0308 1.0000
17.500 1.5307 0.06146 0.05594 -0.0145 0.0301 1.0000
17.750 1.5287 0.06451 0.05905 -0.0146 0.0293 1.0000
18.000 1.5265 0.06765 0.06226 -0.0147 0.0286 1.0000
18.250 1.5254 0.07071 0.06540 -0.0149 0.0283 1.0000
18.500 1.5242 0.07381 0.06857 -0.0152 0.0277 1.0000
18.750 1.5219 0.07706 0.07189 -0.0156 0.0273 1.0000
19.000 1.5183 0.08052 0.07543 -0.0161 0.0269 1.0000
19.250 1.5134 0.08419 0.07917 -0.0167 0.0264 1.0000
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