NACA 4415 (naca4415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 500,000 Max Cl/Cd: 97 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4415-il-500000.txt Download as CSV file: xf-naca4415-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7223 0.08142 0.07808 -0.0740 1.0000 0.0203
-15.250 -0.7608 0.07258 0.06907 -0.0788 1.0000 0.0203
-15.000 -0.7828 0.06652 0.06291 -0.0818 1.0000 0.0204
-14.750 -0.8080 0.06027 0.05653 -0.0849 1.0000 0.0203
-14.500 -0.8310 0.05454 0.05067 -0.0876 1.0000 0.0203
-14.250 -0.8570 0.04878 0.04476 -0.0900 1.0000 0.0202
-14.000 -0.8740 0.04470 0.04058 -0.0914 1.0000 0.0203
-13.750 -0.8937 0.04113 0.03691 -0.0917 1.0000 0.0204
-13.500 -0.9159 0.03834 0.03401 -0.0904 1.0000 0.0204
-13.250 -0.9234 0.03584 0.03139 -0.0908 0.9985 0.0206
-13.000 -0.9106 0.03369 0.02907 -0.0932 0.9948 0.0210
-12.750 -0.8987 0.03202 0.02725 -0.0939 0.9905 0.0214
-12.500 -0.8840 0.03051 0.02559 -0.0942 0.9860 0.0216
-12.250 -0.8601 0.02905 0.02395 -0.0958 0.9835 0.0220
-12.000 -0.8444 0.02760 0.02234 -0.0954 0.9780 0.0224
-11.750 -0.8231 0.02603 0.02071 -0.0960 0.9743 0.0229
-11.500 -0.7951 0.02486 0.01950 -0.0975 0.9721 0.0235
-11.250 -0.7739 0.02387 0.01845 -0.0972 0.9676 0.0239
-11.000 -0.7501 0.02298 0.01747 -0.0973 0.9633 0.0247
-10.750 -0.7209 0.02208 0.01644 -0.0983 0.9608 0.0254
-10.500 -0.6912 0.02097 0.01525 -0.0996 0.9590 0.0263
-10.250 -0.6705 0.02013 0.01439 -0.0989 0.9540 0.0271
-10.000 -0.6443 0.01943 0.01364 -0.0990 0.9497 0.0283
-9.750 -0.6125 0.01869 0.01280 -0.1002 0.9475 0.0295
-9.500 -0.5820 0.01765 0.01174 -0.1014 0.9457 0.0311
-9.250 -0.5475 0.01693 0.01097 -0.1030 0.9446 0.0328
-9.000 -0.5273 0.01632 0.01031 -0.1017 0.9384 0.0344
-8.750 -0.4983 0.01562 0.00959 -0.1022 0.9349 0.0367
-8.500 -0.4646 0.01494 0.00888 -0.1036 0.9326 0.0398
-8.250 -0.4266 0.01439 0.00829 -0.1058 0.9309 0.0437
-8.000 -0.3899 0.01375 0.00765 -0.1079 0.9290 0.0484
-7.750 -0.3704 0.01333 0.00724 -0.1062 0.9212 0.0526
-7.500 -0.3375 0.01285 0.00676 -0.1073 0.9171 0.0589
-7.250 -0.3013 0.01240 0.00632 -0.1091 0.9138 0.0669
-7.000 -0.2765 0.01210 0.00603 -0.1084 0.9067 0.0741
-6.750 -0.2465 0.01180 0.00572 -0.1088 0.9006 0.0819
-6.500 -0.2099 0.01153 0.00541 -0.1106 0.8963 0.0903
-6.250 -0.1889 0.01133 0.00523 -0.1090 0.8871 0.0968
-6.000 -0.1569 0.01108 0.00496 -0.1098 0.8809 0.1045
-5.750 -0.1314 0.01095 0.00479 -0.1092 0.8727 0.1108
-5.500 -0.1035 0.01070 0.00455 -0.1091 0.8649 0.1179
-5.250 -0.0768 0.01059 0.00438 -0.1087 0.8567 0.1241
-5.000 -0.0509 0.01036 0.00415 -0.1082 0.8480 0.1314
-4.750 -0.0246 0.01026 0.00400 -0.1077 0.8394 0.1381
-4.500 0.0009 0.01006 0.00380 -0.1071 0.8303 0.1463
-4.000 0.0518 0.00981 0.00352 -0.1058 0.8117 0.1650
-3.750 0.0753 0.00969 0.00339 -0.1047 0.8017 0.1747
-3.500 0.1020 0.00960 0.00325 -0.1043 0.7924 0.1853
-3.250 0.1240 0.00946 0.00314 -0.1030 0.7816 0.1965
-3.000 0.1491 0.00937 0.00302 -0.1022 0.7719 0.2088
-2.750 0.1725 0.00929 0.00293 -0.1011 0.7610 0.2220
-2.500 0.1962 0.00920 0.00286 -0.1001 0.7505 0.2368
-2.250 0.2201 0.00913 0.00278 -0.0991 0.7399 0.2531
-2.000 0.2427 0.00905 0.00272 -0.0979 0.7288 0.2703
-1.750 0.2663 0.00900 0.00266 -0.0968 0.7182 0.2888
-1.500 0.2890 0.00894 0.00262 -0.0956 0.7068 0.3083
-1.250 0.3117 0.00888 0.00258 -0.0944 0.6959 0.3303
-1.000 0.3342 0.00882 0.00254 -0.0932 0.6851 0.3557
-0.750 0.3555 0.00872 0.00252 -0.0917 0.6737 0.3877
-0.500 0.3763 0.00860 0.00251 -0.0901 0.6632 0.4332
-0.250 0.3953 0.00843 0.00251 -0.0882 0.6524 0.5006
0.000 0.4127 0.00822 0.00256 -0.0859 0.6421 0.5843
0.250 0.4297 0.00808 0.00260 -0.0834 0.6322 0.6634
0.500 0.4468 0.00792 0.00265 -0.0809 0.6221 0.7353
0.750 0.4669 0.00778 0.00273 -0.0789 0.6127 0.8149
1.000 0.5376 0.00784 0.00297 -0.0880 0.6008 0.9102
1.250 0.6155 0.00809 0.00317 -0.0988 0.5891 0.9423
1.500 0.6568 0.00836 0.00334 -0.1015 0.5788 0.9608
1.750 0.6936 0.00855 0.00350 -0.1033 0.5686 0.9761
2.000 0.7343 0.00878 0.00364 -0.1060 0.5588 0.9862
2.250 0.7769 0.00897 0.00377 -0.1092 0.5486 0.9935
2.500 0.8247 0.00911 0.00384 -0.1136 0.5387 0.9990
2.750 0.8487 0.00922 0.00389 -0.1129 0.5298 1.0000
3.000 0.8663 0.00932 0.00396 -0.1108 0.5221 1.0000
3.250 0.8838 0.00943 0.00403 -0.1087 0.5138 1.0000
3.500 0.9013 0.00956 0.00411 -0.1065 0.5058 1.0000
3.750 0.9182 0.00968 0.00419 -0.1043 0.4960 1.0000
4.000 0.9353 0.00982 0.00428 -0.1020 0.4868 1.0000
4.250 0.9525 0.00996 0.00439 -0.0998 0.4780 1.0000
4.500 0.9704 0.01011 0.00451 -0.0977 0.4707 1.0000
4.750 0.9883 0.01024 0.00463 -0.0957 0.4629 1.0000
5.000 1.0049 0.01042 0.00476 -0.0934 0.4553 1.0000
5.250 1.0222 0.01054 0.00489 -0.0911 0.4472 1.0000
5.500 1.0363 0.01073 0.00503 -0.0883 0.4400 1.0000
5.750 1.0525 0.01085 0.00516 -0.0859 0.4322 1.0000
6.000 1.0667 0.01104 0.00531 -0.0831 0.4238 1.0000
6.250 1.0835 0.01119 0.00547 -0.0808 0.4160 1.0000
6.500 1.0990 0.01140 0.00565 -0.0784 0.4078 1.0000
6.750 1.1161 0.01159 0.00584 -0.0763 0.3997 1.0000
7.000 1.1318 0.01182 0.00605 -0.0739 0.3906 1.0000
7.250 1.1489 0.01204 0.00627 -0.0719 0.3816 1.0000
7.500 1.1640 0.01233 0.00651 -0.0695 0.3720 1.0000
7.750 1.1818 0.01256 0.00676 -0.0677 0.3625 1.0000
8.000 1.1969 0.01289 0.00706 -0.0654 0.3525 1.0000
8.250 1.2128 0.01321 0.00736 -0.0633 0.3410 1.0000
8.500 1.2288 0.01355 0.00769 -0.0613 0.3298 1.0000
8.750 1.2431 0.01397 0.00806 -0.0591 0.3173 1.0000
9.000 1.2562 0.01444 0.00849 -0.0567 0.3038 1.0000
9.250 1.2688 0.01497 0.00895 -0.0544 0.2886 1.0000
9.500 1.2808 0.01555 0.00948 -0.0520 0.2731 1.0000
9.750 1.2927 0.01617 0.01004 -0.0497 0.2577 1.0000
10.000 1.3049 0.01681 0.01064 -0.0475 0.2438 1.0000
10.250 1.3167 0.01750 0.01128 -0.0453 0.2303 1.0000
10.500 1.3281 0.01823 0.01198 -0.0432 0.2183 1.0000
10.750 1.3381 0.01906 0.01277 -0.0410 0.2059 1.0000
11.250 1.3593 0.02075 0.01442 -0.0370 0.1858 1.0000
11.500 1.3691 0.02169 0.01534 -0.0351 0.1774 1.0000
11.750 1.3789 0.02266 0.01631 -0.0332 0.1693 1.0000
12.000 1.3888 0.02366 0.01731 -0.0315 0.1617 1.0000
12.250 1.3969 0.02480 0.01845 -0.0297 0.1547 1.0000
12.500 1.4066 0.02588 0.01956 -0.0281 0.1490 1.0000
12.750 1.4156 0.02706 0.02074 -0.0266 0.1430 1.0000
13.000 1.4218 0.02845 0.02214 -0.0250 0.1376 1.0000
13.250 1.4320 0.02960 0.02334 -0.0237 0.1323 1.0000
13.500 1.4370 0.03119 0.02493 -0.0222 0.1269 1.0000
13.750 1.4457 0.03253 0.02633 -0.0211 0.1218 1.0000
14.000 1.4517 0.03413 0.02795 -0.0199 0.1165 1.0000
14.250 1.4562 0.03591 0.02975 -0.0188 0.1112 1.0000
14.500 1.4623 0.03760 0.03148 -0.0178 0.1057 1.0000
14.750 1.4646 0.03969 0.03360 -0.0168 0.1003 1.0000
15.000 1.4688 0.04166 0.03560 -0.0160 0.0942 1.0000
15.250 1.4697 0.04399 0.03795 -0.0152 0.0884 1.0000
15.500 1.4688 0.04658 0.04054 -0.0144 0.0822 1.0000
15.750 1.4685 0.04917 0.04317 -0.0139 0.0765 1.0000
16.000 1.4636 0.05231 0.04631 -0.0134 0.0716 1.0000
16.250 1.4617 0.05519 0.04924 -0.0131 0.0669 1.0000
16.500 1.4549 0.05870 0.05278 -0.0128 0.0634 1.0000
16.750 1.4537 0.06165 0.05580 -0.0128 0.0605 1.0000
17.000 1.4474 0.06525 0.05944 -0.0128 0.0579 1.0000
17.250 1.4399 0.06904 0.06328 -0.0130 0.0556 1.0000
17.500 1.4371 0.07235 0.06668 -0.0132 0.0537 1.0000
17.750 1.4315 0.07605 0.07045 -0.0136 0.0521 1.0000
18.000 1.4234 0.08010 0.07455 -0.0142 0.0507 1.0000
18.250 1.4133 0.08448 0.07898 -0.0148 0.0493 1.0000
18.500 1.4111 0.08788 0.08248 -0.0154 0.0481 1.0000
18.750 1.4072 0.09154 0.08622 -0.0161 0.0469 1.0000
19.000 1.4011 0.09552 0.09027 -0.0170 0.0459 1.0000
19.250 1.3935 0.09974 0.09454 -0.0180 0.0448 1.0000
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