NACA 4415 (naca4415-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 100,000 Max Cl/Cd: 48.43 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4415-il-100000.txt Download as CSV file: xf-naca4415-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3649 0.10746 0.10282 -0.0297 1.0000 0.1485
-8.750 -0.6203 0.07088 0.06627 -0.0480 1.0000 0.0791
-8.500 -0.6400 0.06720 0.06253 -0.0459 1.0000 0.0787
-8.250 -0.6613 0.06278 0.05798 -0.0440 1.0000 0.0782
-8.000 -0.6853 0.05725 0.05215 -0.0422 1.0000 0.0779
-7.750 -0.6987 0.04981 0.04397 -0.0426 0.9966 0.0785
-7.500 -0.6730 0.04677 0.04070 -0.0451 0.9895 0.0814
-7.250 -0.6434 0.04436 0.03802 -0.0477 0.9829 0.0849
-7.000 -0.6291 0.03993 0.03268 -0.0479 0.9744 0.0884
-6.750 -0.5962 0.03918 0.03204 -0.0498 0.9671 0.0937
-6.500 -0.5704 0.03672 0.02881 -0.0505 0.9595 0.1001
-6.250 -0.5407 0.03613 0.02845 -0.0515 0.9513 0.1063
-6.000 -0.5066 0.03479 0.02680 -0.0533 0.9447 0.1152
-5.750 -0.4827 0.03391 0.02563 -0.0529 0.9353 0.1238
-5.500 -0.4436 0.03322 0.02498 -0.0554 0.9293 0.1348
-5.250 -0.4213 0.03243 0.02409 -0.0547 0.9196 0.1441
-5.000 -0.3822 0.03168 0.02318 -0.0569 0.9137 0.1574
-4.750 -0.3602 0.03135 0.02267 -0.0560 0.9034 0.1686
-4.500 -0.3206 0.03076 0.02211 -0.0583 0.8976 0.1821
-4.250 -0.2980 0.03031 0.02164 -0.0575 0.8876 0.1923
-4.000 -0.2593 0.02972 0.02094 -0.0594 0.8814 0.2066
-3.750 -0.2356 0.02948 0.02061 -0.0587 0.8717 0.2183
-3.500 -0.1982 0.02888 0.02005 -0.0604 0.8653 0.2319
-3.250 -0.1696 0.02844 0.01958 -0.0605 0.8570 0.2445
-3.000 -0.1373 0.02796 0.01902 -0.0611 0.8491 0.2594
-2.750 -0.0917 0.02723 0.01831 -0.0639 0.8453 0.2786
-2.500 -0.0762 0.02717 0.01822 -0.0617 0.8332 0.2929
-2.250 -0.0321 0.02636 0.01751 -0.0643 0.8290 0.3162
-2.000 -0.0146 0.02627 0.01747 -0.0624 0.8178 0.3346
-1.750 0.0266 0.02547 0.01682 -0.0643 0.8129 0.3652
-1.500 0.0745 0.02444 0.01597 -0.0672 0.8102 0.4071
-1.250 0.0840 0.02451 0.01624 -0.0640 0.7973 0.4365
-1.000 0.1301 0.02334 0.01549 -0.0665 0.7942 0.5105
-0.750 0.1826 0.02197 0.01490 -0.0696 0.7923 0.6780
-0.500 0.3815 0.02095 0.01440 -0.1001 0.7957 0.9661
-0.250 0.5016 0.02020 0.01339 -0.1171 0.7944 1.0000
0.000 0.5067 0.02032 0.01339 -0.1134 0.7817 1.0000
0.250 0.5512 0.01976 0.01266 -0.1162 0.7756 1.0000
0.500 0.5565 0.02003 0.01284 -0.1122 0.7628 1.0000
0.750 0.6036 0.01951 0.01216 -0.1153 0.7570 1.0000
1.000 0.6078 0.01991 0.01249 -0.1110 0.7441 1.0000
1.250 0.6411 0.01975 0.01221 -0.1117 0.7363 1.0000
1.500 0.6589 0.01993 0.01231 -0.1098 0.7256 1.0000
1.750 0.6821 0.02004 0.01233 -0.1087 0.7162 1.0000
2.000 0.7095 0.02004 0.01224 -0.1084 0.7070 1.0000
2.250 0.7274 0.02032 0.01247 -0.1064 0.6971 1.0000
2.500 0.7588 0.02027 0.01233 -0.1067 0.6886 1.0000
2.750 0.7735 0.02065 0.01267 -0.1042 0.6783 1.0000
3.000 0.8075 0.02057 0.01250 -0.1049 0.6701 1.0000
3.250 0.8196 0.02103 0.01295 -0.1020 0.6597 1.0000
3.500 0.8556 0.02094 0.01275 -0.1031 0.6518 1.0000
3.750 0.8655 0.02146 0.01330 -0.0998 0.6411 1.0000
4.000 0.9041 0.02134 0.01306 -0.1013 0.6334 1.0000
4.250 0.9112 0.02192 0.01368 -0.0975 0.6224 1.0000
4.500 0.9509 0.02181 0.01345 -0.0992 0.6147 1.0000
4.750 0.9567 0.02241 0.01412 -0.0952 0.6037 1.0000
5.000 0.9889 0.02248 0.01411 -0.0956 0.5954 1.0000
5.250 1.0022 0.02291 0.01458 -0.0929 0.5848 1.0000
5.500 1.0265 0.02313 0.01477 -0.0920 0.5754 1.0000
5.750 1.0500 0.02328 0.01488 -0.0909 0.5650 1.0000
6.000 1.0654 0.02365 0.01529 -0.0884 0.5542 1.0000
6.250 1.1030 0.02354 0.01503 -0.0897 0.5444 1.0000
6.500 1.1078 0.02409 0.01569 -0.0855 0.5330 1.0000
6.750 1.1334 0.02426 0.01583 -0.0848 0.5230 1.0000
7.000 1.1524 0.02452 0.01609 -0.0830 0.5123 1.0000
7.250 1.1672 0.02493 0.01654 -0.0806 0.5016 1.0000
7.500 1.2022 0.02492 0.01641 -0.0815 0.4914 1.0000
7.750 1.2048 0.02550 0.01712 -0.0769 0.4800 1.0000
8.000 1.2252 0.02576 0.01737 -0.0754 0.4691 1.0000
8.250 1.2503 0.02589 0.01743 -0.0747 0.4577 1.0000
8.500 1.2552 0.02642 0.01808 -0.0706 0.4461 1.0000
8.750 1.2737 0.02670 0.01834 -0.0688 0.4345 1.0000
9.000 1.2994 0.02683 0.01835 -0.0681 0.4223 1.0000
9.250 1.2995 0.02739 0.01904 -0.0633 0.4101 1.0000
9.500 1.3100 0.02782 0.01950 -0.0603 0.3979 1.0000
9.750 1.3266 0.02812 0.01972 -0.0582 0.3853 1.0000
10.000 1.3373 0.02849 0.02006 -0.0552 0.3727 1.0000
10.250 1.3355 0.02914 0.02079 -0.0502 0.3607 1.0000
10.500 1.3427 0.02970 0.02133 -0.0469 0.3483 1.0000
10.750 1.3555 0.03021 0.02175 -0.0445 0.3357 1.0000
11.000 1.3614 0.03086 0.02238 -0.0412 0.3233 1.0000
11.250 1.3601 0.03177 0.02336 -0.0371 0.3115 1.0000
11.500 1.3656 0.03259 0.02415 -0.0341 0.2997 1.0000
11.750 1.3764 0.03329 0.02474 -0.0319 0.2879 1.0000
12.000 1.3741 0.03442 0.02596 -0.0282 0.2771 1.0000
12.250 1.3767 0.03557 0.02713 -0.0254 0.2667 1.0000
12.500 1.3891 0.03644 0.02786 -0.0237 0.2562 1.0000
12.750 1.3848 0.03794 0.02952 -0.0205 0.2471 1.0000
13.000 1.3921 0.03914 0.03069 -0.0186 0.2379 1.0000
13.250 1.3950 0.04048 0.03205 -0.0163 0.2289 1.0000
13.500 1.3959 0.04210 0.03375 -0.0141 0.2206 1.0000
13.750 1.4053 0.04326 0.03480 -0.0127 0.2116 1.0000
14.000 1.3985 0.04539 0.03713 -0.0103 0.2043 1.0000
14.250 1.4119 0.04645 0.03802 -0.0092 0.1950 1.0000
14.500 1.3986 0.04908 0.04092 -0.0068 0.1886 1.0000
14.750 1.4110 0.05028 0.04195 -0.0058 0.1799 1.0000
15.000 1.3960 0.05325 0.04518 -0.0039 0.1736 1.0000
15.250 1.4069 0.05459 0.04637 -0.0030 0.1652 1.0000
15.500 1.3910 0.05793 0.04998 -0.0015 0.1593 1.0000
15.750 1.4033 0.05926 0.05114 -0.0007 0.1512 1.0000
16.000 1.3851 0.06310 0.05527 0.0003 0.1461 1.0000
16.250 1.4025 0.06408 0.05601 0.0010 0.1380 1.0000
16.500 1.3804 0.06858 0.06084 0.0016 0.1342 1.0000
16.750 1.3787 0.07129 0.06361 0.0020 0.1289 1.0000
17.000 1.3841 0.07355 0.06585 0.0025 0.1235 1.0000
17.250 1.3636 0.07846 0.07103 0.0023 0.1204 1.0000
17.500 1.3636 0.08117 0.07380 0.0023 0.1161 1.0000
17.750 1.3736 0.08311 0.07569 0.0027 0.1119 1.0000
18.000 1.3465 0.08926 0.08216 0.0015 0.1102 1.0000
18.250 1.3187 0.09592 0.08910 -0.0003 0.1085 1.0000
18.500 1.2887 0.10330 0.09673 -0.0028 0.1071 1.0000
18.750 1.2121 0.11894 0.11279 -0.0101 0.1082 1.0000
19.000 1.3029 0.10762 0.10102 -0.0030 0.1009 1.0000
19.250 1.2512 0.11897 0.11270 -0.0083 0.1010 1.0000
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