NACA 4415 (naca4415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 4415 (naca4415-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.37 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4415-il-1000000.txt Download as CSV file: xf-naca4415-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8197 0.08120 0.07821 -0.0728 1.0000 0.0145
-16.250 -0.8474 0.07460 0.07153 -0.0758 1.0000 0.0144
-16.000 -0.8819 0.06723 0.06407 -0.0791 1.0000 0.0145
-15.750 -0.9187 0.05986 0.05658 -0.0822 1.0000 0.0143
-15.500 -0.9634 0.05142 0.04800 -0.0859 1.0000 0.0142
-15.250 -1.0030 0.04293 0.03935 -0.0904 1.0000 0.0142
-15.000 -1.0357 0.03638 0.03261 -0.0939 1.0000 0.0142
-14.750 -1.0300 0.03186 0.02793 -0.1005 0.9976 0.0143
-14.500 -1.0184 0.02927 0.02521 -0.1040 0.9949 0.0144
-14.250 -1.0048 0.02746 0.02329 -0.1056 0.9925 0.0146
-14.000 -0.9920 0.02610 0.02184 -0.1056 0.9887 0.0148
-13.750 -0.9733 0.02498 0.02063 -0.1060 0.9859 0.0151
-13.500 -0.9512 0.02391 0.01948 -0.1068 0.9840 0.0153
-13.250 -0.9245 0.02288 0.01835 -0.1082 0.9829 0.0156
-13.000 -0.9100 0.02206 0.01746 -0.1065 0.9772 0.0158
-12.750 -0.8837 0.02125 0.01657 -0.1072 0.9749 0.0161
-12.500 -0.8600 0.01997 0.01521 -0.1080 0.9729 0.0165
-12.250 -0.8324 0.01899 0.01418 -0.1090 0.9717 0.0170
-12.000 -0.8121 0.01834 0.01348 -0.1081 0.9676 0.0174
-11.750 -0.7880 0.01768 0.01277 -0.1080 0.9641 0.0177
-11.500 -0.7592 0.01704 0.01208 -0.1087 0.9622 0.0183
-11.250 -0.7290 0.01640 0.01138 -0.1096 0.9608 0.0187
-11.000 -0.6970 0.01583 0.01074 -0.1108 0.9596 0.0191
-10.750 -0.6659 0.01496 0.00983 -0.1121 0.9582 0.0200
-10.500 -0.6468 0.01450 0.00934 -0.1105 0.9520 0.0206
-10.250 -0.6155 0.01401 0.00880 -0.1115 0.9490 0.0214
-10.000 -0.5811 0.01357 0.00831 -0.1131 0.9468 0.0225
-9.750 -0.5458 0.01294 0.00767 -0.1150 0.9447 0.0239
-9.500 -0.5198 0.01258 0.00727 -0.1147 0.9389 0.0253
-9.250 -0.4913 0.01211 0.00677 -0.1150 0.9334 0.0268
-9.000 -0.4561 0.01168 0.00631 -0.1168 0.9297 0.0288
-8.750 -0.4324 0.01134 0.00593 -0.1160 0.9223 0.0308
-8.500 -0.4028 0.01100 0.00556 -0.1164 0.9160 0.0334
-8.250 -0.3752 0.01065 0.00519 -0.1164 0.9094 0.0363
-8.000 -0.3502 0.01039 0.00490 -0.1158 0.9013 0.0392
-7.750 -0.3223 0.01010 0.00459 -0.1158 0.8943 0.0435
-7.500 -0.2994 0.00983 0.00432 -0.1148 0.8853 0.0485
-7.250 -0.2727 0.00959 0.00407 -0.1145 0.8777 0.0552
-7.000 -0.2495 0.00938 0.00387 -0.1135 0.8687 0.0621
-6.750 -0.2237 0.00919 0.00366 -0.1130 0.8605 0.0690
-6.500 -0.2001 0.00902 0.00350 -0.1120 0.8513 0.0753
-6.250 -0.1743 0.00890 0.00334 -0.1115 0.8431 0.0807
-6.000 -0.1506 0.00875 0.00319 -0.1105 0.8338 0.0867
-5.750 -0.1256 0.00865 0.00305 -0.1098 0.8250 0.0922
-5.500 -0.1015 0.00853 0.00293 -0.1088 0.8155 0.0981
-5.250 -0.0770 0.00843 0.00280 -0.1080 0.8067 0.1044
-5.000 -0.0529 0.00834 0.00270 -0.1071 0.7968 0.1103
-4.750 -0.0287 0.00824 0.00258 -0.1062 0.7876 0.1166
-4.500 -0.0047 0.00816 0.00248 -0.1052 0.7776 0.1228
-4.250 0.0193 0.00808 0.00238 -0.1042 0.7678 0.1296
-4.000 0.0430 0.00802 0.00229 -0.1032 0.7574 0.1369
-3.750 0.0670 0.00793 0.00220 -0.1022 0.7472 0.1450
-3.500 0.0906 0.00789 0.00213 -0.1012 0.7366 0.1536
-3.250 0.1140 0.00780 0.00206 -0.1001 0.7258 0.1651
-3.000 0.1377 0.00776 0.00199 -0.0991 0.7155 0.1746
-2.500 0.1842 0.00766 0.00188 -0.0969 0.6930 0.1964
-2.250 0.2074 0.00763 0.00183 -0.0957 0.6825 0.2087
-1.750 0.2539 0.00756 0.00177 -0.0935 0.6602 0.2364
-1.500 0.2763 0.00755 0.00175 -0.0922 0.6490 0.2522
-1.250 0.2997 0.00751 0.00173 -0.0912 0.6382 0.2685
-1.000 0.3225 0.00750 0.00172 -0.0900 0.6277 0.2849
-0.750 0.3449 0.00749 0.00172 -0.0887 0.6168 0.3027
-0.500 0.3681 0.00746 0.00171 -0.0876 0.6067 0.3221
-0.250 0.3897 0.00746 0.00172 -0.0862 0.5965 0.3452
0.000 0.4126 0.00741 0.00173 -0.0850 0.5868 0.3731
0.250 0.4333 0.00735 0.00175 -0.0835 0.5774 0.4124
0.500 0.4538 0.00722 0.00177 -0.0818 0.5683 0.4721
0.750 0.4718 0.00708 0.00182 -0.0797 0.5596 0.5474
1.000 0.4892 0.00693 0.00187 -0.0774 0.5512 0.6234
1.250 0.5050 0.00685 0.00192 -0.0747 0.5427 0.6827
1.500 0.5212 0.00672 0.00197 -0.0720 0.5349 0.7462
1.750 0.5341 0.00659 0.00206 -0.0686 0.5265 0.8279
2.000 0.6481 0.00672 0.00241 -0.0877 0.5139 0.9364
2.250 0.7151 0.00699 0.00263 -0.0963 0.5038 0.9585
2.500 0.7486 0.00719 0.00278 -0.0974 0.4953 0.9744
2.750 0.7821 0.00737 0.00292 -0.0986 0.4871 0.9846
3.000 0.8209 0.00758 0.00305 -0.1010 0.4761 0.9909
3.250 0.8611 0.00775 0.00317 -0.1038 0.4652 0.9951
3.500 0.9034 0.00792 0.00327 -0.1070 0.4549 0.9984
3.750 0.9405 0.00803 0.00335 -0.1091 0.4460 1.0000
4.000 0.9571 0.00816 0.00344 -0.1067 0.4384 1.0000
4.250 0.9761 0.00824 0.00351 -0.1049 0.4315 1.0000
4.500 0.9928 0.00838 0.00361 -0.1026 0.4237 1.0000
4.750 1.0113 0.00849 0.00370 -0.1006 0.4165 1.0000
5.000 1.0270 0.00862 0.00380 -0.0980 0.4085 1.0000
5.250 1.0420 0.00874 0.00390 -0.0953 0.4012 1.0000
5.500 1.0576 0.00886 0.00400 -0.0927 0.3936 1.0000
5.750 1.0730 0.00901 0.00412 -0.0901 0.3858 1.0000
6.000 1.0903 0.00915 0.00424 -0.0880 0.3775 1.0000
6.250 1.1061 0.00933 0.00439 -0.0855 0.3685 1.0000
6.500 1.1232 0.00951 0.00454 -0.0833 0.3594 1.0000
6.750 1.1403 0.00970 0.00471 -0.0812 0.3505 1.0000
7.000 1.1572 0.00992 0.00490 -0.0790 0.3407 1.0000
7.250 1.1745 0.01014 0.00509 -0.0770 0.3304 1.0000
7.500 1.1908 0.01041 0.00531 -0.0748 0.3196 1.0000
7.750 1.2073 0.01070 0.00555 -0.0728 0.3070 1.0000
8.000 1.2236 0.01101 0.00581 -0.0707 0.2935 1.0000
8.250 1.2385 0.01139 0.00612 -0.0684 0.2779 1.0000
8.500 1.2537 0.01178 0.00645 -0.0662 0.2630 1.0000
8.750 1.2671 0.01226 0.00683 -0.0638 0.2460 1.0000
9.000 1.2816 0.01271 0.00722 -0.0616 0.2314 1.0000
9.250 1.2960 0.01318 0.00764 -0.0595 0.2183 1.0000
9.500 1.3097 0.01370 0.00809 -0.0573 0.2051 1.0000
9.750 1.3236 0.01423 0.00857 -0.0552 0.1938 1.0000
10.000 1.3374 0.01478 0.00907 -0.0531 0.1827 1.0000
10.250 1.3519 0.01531 0.00958 -0.0512 0.1730 1.0000
10.500 1.3649 0.01592 0.01015 -0.0492 0.1635 1.0000
10.750 1.3786 0.01653 0.01073 -0.0473 0.1557 1.0000
11.000 1.3925 0.01713 0.01134 -0.0455 0.1489 1.0000
11.250 1.4054 0.01781 0.01199 -0.0437 0.1422 1.0000
11.500 1.4188 0.01849 0.01267 -0.0420 0.1363 1.0000
11.750 1.4320 0.01919 0.01337 -0.0403 0.1308 1.0000
12.000 1.4434 0.02001 0.01418 -0.0385 0.1251 1.0000
12.250 1.4568 0.02074 0.01493 -0.0370 0.1205 1.0000
12.500 1.4675 0.02166 0.01584 -0.0352 0.1151 1.0000
12.750 1.4798 0.02250 0.01671 -0.0338 0.1107 1.0000
13.000 1.4905 0.02346 0.01768 -0.0322 0.1057 1.0000
13.250 1.4998 0.02455 0.01877 -0.0306 0.1004 1.0000
13.500 1.5095 0.02565 0.01987 -0.0291 0.0951 1.0000
13.750 1.5168 0.02696 0.02117 -0.0276 0.0893 1.0000
14.000 1.5230 0.02837 0.02258 -0.0260 0.0828 1.0000
14.250 1.5290 0.02986 0.02407 -0.0246 0.0768 1.0000
14.500 1.5324 0.03161 0.02581 -0.0231 0.0707 1.0000
14.750 1.5343 0.03353 0.02772 -0.0216 0.0646 1.0000
15.000 1.5372 0.03544 0.02964 -0.0204 0.0597 1.0000
15.250 1.5382 0.03759 0.03180 -0.0192 0.0554 1.0000
15.500 1.5397 0.03977 0.03402 -0.0182 0.0518 1.0000
15.750 1.5401 0.04210 0.03637 -0.0173 0.0490 1.0000
16.000 1.5418 0.04438 0.03871 -0.0166 0.0467 1.0000
16.250 1.5405 0.04702 0.04138 -0.0159 0.0447 1.0000
16.500 1.5404 0.04962 0.04404 -0.0154 0.0430 1.0000
16.750 1.5425 0.05202 0.04650 -0.0151 0.0417 1.0000
17.000 1.5411 0.05484 0.04938 -0.0147 0.0404 1.0000
17.250 1.5371 0.05802 0.05261 -0.0145 0.0390 1.0000
17.500 1.5326 0.06134 0.05599 -0.0145 0.0378 1.0000
17.750 1.5334 0.06407 0.05881 -0.0145 0.0371 1.0000
18.000 1.5317 0.06713 0.06195 -0.0146 0.0363 1.0000
18.250 1.5284 0.07045 0.06534 -0.0148 0.0356 1.0000
18.500 1.5237 0.07399 0.06894 -0.0151 0.0349 1.0000
18.750 1.5167 0.07784 0.07286 -0.0156 0.0342 1.0000
19.000 1.5073 0.08207 0.07717 -0.0162 0.0335 1.0000
19.250 1.4995 0.08616 0.08134 -0.0170 0.0329 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 4415 (naca4415-il)