NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.62 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415-il-1000000.txt Download as CSV file: xf-naca652415-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415
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 -0.8295 0.07759 0.07523 -0.0679 1.0000 0.0122
-16.250 -0.8556 0.06891 0.06636 -0.0735 1.0000 0.0122
-16.000 -0.8847 0.06080 0.05805 -0.0783 1.0000 0.0122
-15.750 -0.9015 0.05531 0.05243 -0.0812 1.0000 0.0123
-15.500 -0.9225 0.04981 0.04674 -0.0834 1.0000 0.0123
-15.250 -0.9270 0.04669 0.04354 -0.0844 1.0000 0.0125
-15.000 -0.9313 0.04374 0.04050 -0.0850 1.0000 0.0126
-14.750 -0.9308 0.04147 0.03815 -0.0854 1.0000 0.0127
-14.500 -0.9274 0.03959 0.03622 -0.0855 1.0000 0.0128
-14.250 -0.9244 0.03779 0.03436 -0.0853 1.0000 0.0130
-14.000 -0.9227 0.03592 0.03241 -0.0849 1.0000 0.0131
-13.750 -0.9191 0.03437 0.03079 -0.0843 1.0000 0.0133
-13.500 -0.9142 0.03309 0.02944 -0.0835 1.0000 0.0135
-13.250 -0.9126 0.03158 0.02784 -0.0823 1.0000 0.0137
-13.000 -0.9118 0.03019 0.02636 -0.0805 1.0000 0.0138
-12.750 -0.8997 0.02916 0.02527 -0.0803 0.9933 0.0142
-12.500 -0.8783 0.02742 0.02335 -0.0824 0.9846 0.0146
-12.250 -0.8509 0.02602 0.02180 -0.0852 0.9774 0.0149
-12.000 -0.8176 0.02508 0.02073 -0.0887 0.9710 0.0151
-11.750 -0.7934 0.02231 0.01776 -0.0912 0.9614 0.0158
-11.500 -0.7636 0.02143 0.01682 -0.0934 0.9485 0.0161
-11.250 -0.7430 0.02077 0.01605 -0.0935 0.9320 0.0164
-11.000 -0.7295 0.02026 0.01543 -0.0918 0.9162 0.0168
-10.750 -0.7173 0.01974 0.01479 -0.0898 0.9029 0.0171
-10.500 -0.7023 0.01921 0.01415 -0.0882 0.8922 0.0175
-10.250 -0.6847 0.01875 0.01359 -0.0870 0.8823 0.0179
-10.000 -0.6659 0.01836 0.01310 -0.0859 0.8735 0.0183
-9.750 -0.6462 0.01799 0.01263 -0.0849 0.8647 0.0186
-9.500 -0.6289 0.01675 0.01127 -0.0838 0.8569 0.0191
-9.250 -0.6102 0.01603 0.01049 -0.0828 0.8489 0.0196
-9.000 -0.5895 0.01558 0.01000 -0.0820 0.8420 0.0201
-8.750 -0.5679 0.01518 0.00955 -0.0813 0.8346 0.0205
-8.500 -0.5458 0.01483 0.00914 -0.0807 0.8280 0.0211
-8.250 -0.5232 0.01444 0.00870 -0.0801 0.8210 0.0217
-8.000 -0.5006 0.01408 0.00826 -0.0795 0.8144 0.0222
-7.750 -0.4773 0.01370 0.00783 -0.0790 0.8084 0.0226
-7.500 -0.4530 0.01344 0.00751 -0.0786 0.8022 0.0230
-7.250 -0.4353 0.01252 0.00652 -0.0774 0.7961 0.0238
-7.000 -0.4121 0.01210 0.00607 -0.0769 0.7901 0.0246
-6.750 -0.3878 0.01181 0.00574 -0.0766 0.7842 0.0254
-6.500 -0.3630 0.01151 0.00541 -0.0763 0.7788 0.0261
-6.250 -0.3378 0.01122 0.00508 -0.0761 0.7733 0.0270
-6.000 -0.3124 0.01097 0.00477 -0.0759 0.7681 0.0276
-5.750 -0.2867 0.01071 0.00447 -0.0758 0.7631 0.0282
-5.500 -0.2623 0.01024 0.00396 -0.0755 0.7578 0.0299
-5.250 -0.2362 0.01002 0.00371 -0.0755 0.7527 0.0314
-5.000 -0.2094 0.00983 0.00349 -0.0755 0.7480 0.0330
-4.750 -0.1822 0.00965 0.00329 -0.0756 0.7433 0.0342
-4.500 -0.1558 0.00936 0.00297 -0.0755 0.7387 0.0379
-4.250 -0.1287 0.00921 0.00278 -0.0756 0.7341 0.0413
-4.000 -0.1016 0.00894 0.00257 -0.0757 0.7299 0.0518
-3.750 -0.0759 0.00844 0.00231 -0.0758 0.7253 0.1099
-3.500 -0.0516 0.00768 0.00199 -0.0759 0.7209 0.2371
-3.250 -0.0276 0.00667 0.00163 -0.0762 0.7169 0.4187
-3.000 -0.0004 0.00620 0.00153 -0.0766 0.7131 0.5244
-2.750 0.0282 0.00612 0.00150 -0.0769 0.7090 0.5573
-2.500 0.0569 0.00610 0.00148 -0.0772 0.7050 0.5778
-2.250 0.0859 0.00609 0.00147 -0.0775 0.7012 0.5907
-2.000 0.1149 0.00607 0.00147 -0.0779 0.6976 0.6065
-1.750 0.1438 0.00608 0.00151 -0.0781 0.6939 0.6253
-1.500 0.1726 0.00614 0.00156 -0.0784 0.6903 0.6420
-1.250 0.2016 0.00620 0.00158 -0.0787 0.6866 0.6505
-1.000 0.2307 0.00618 0.00159 -0.0790 0.6834 0.6548
-0.750 0.2599 0.00618 0.00158 -0.0794 0.6798 0.6582
-0.500 0.2890 0.00621 0.00158 -0.0798 0.6764 0.6616
-0.250 0.3181 0.00626 0.00158 -0.0801 0.6731 0.6648
0.000 0.3470 0.00626 0.00160 -0.0805 0.6698 0.6684
0.250 0.3761 0.00626 0.00162 -0.0808 0.6666 0.6717
0.500 0.4052 0.00627 0.00164 -0.0812 0.6633 0.6754
0.750 0.4342 0.00631 0.00166 -0.0816 0.6601 0.6789
1.000 0.4631 0.00637 0.00169 -0.0819 0.6567 0.6823
1.250 0.4920 0.00638 0.00174 -0.0822 0.6537 0.6859
1.500 0.5210 0.00639 0.00178 -0.0826 0.6505 0.6898
1.750 0.5499 0.00642 0.00183 -0.0829 0.6472 0.6937
2.000 0.5787 0.00648 0.00187 -0.0832 0.6430 0.6971
2.250 0.6070 0.00650 0.00192 -0.0835 0.6381 0.7011
2.500 0.6355 0.00650 0.00197 -0.0837 0.6329 0.7052
2.750 0.6637 0.00656 0.00201 -0.0839 0.6268 0.7095
3.000 0.6919 0.00659 0.00206 -0.0841 0.6190 0.7134
3.250 0.7190 0.00663 0.00210 -0.0840 0.6087 0.7178
3.500 0.7463 0.00666 0.00214 -0.0840 0.5957 0.7222
3.750 0.7736 0.00673 0.00220 -0.0840 0.5818 0.7267
4.000 0.8007 0.00682 0.00228 -0.0840 0.5672 0.7312
4.250 0.8273 0.00691 0.00238 -0.0839 0.5518 0.7361
4.500 0.8528 0.00707 0.00250 -0.0836 0.5306 0.7411
4.750 0.8766 0.00736 0.00266 -0.0830 0.4947 0.7459
5.000 0.8937 0.00799 0.00300 -0.0813 0.4222 0.7510
5.250 0.9045 0.00904 0.00360 -0.0786 0.3248 0.7567
5.500 0.9153 0.01007 0.00419 -0.0759 0.2375 0.7624
5.750 0.9259 0.01099 0.00477 -0.0732 0.1646 0.7685
6.000 0.9369 0.01184 0.00533 -0.0706 0.1060 0.7751
6.250 0.9493 0.01255 0.00586 -0.0682 0.0665 0.7813
6.500 0.9613 0.01312 0.00632 -0.0656 0.0440 0.7881
7.000 0.9909 0.01396 0.00716 -0.0613 0.0314 0.8022
7.250 1.0050 0.01446 0.00766 -0.0592 0.0281 0.8103
7.500 1.0210 0.01486 0.00813 -0.0574 0.0263 0.8183
8.000 1.0491 0.01591 0.00926 -0.0534 0.0226 0.8361
8.250 1.0637 0.01643 0.00986 -0.0516 0.0217 0.8455
8.500 1.0791 0.01692 0.01041 -0.0500 0.0208 0.8559
8.750 1.0931 0.01747 0.01103 -0.0482 0.0199 0.8671
9.000 1.1062 0.01807 0.01169 -0.0463 0.0193 0.8799
9.250 1.1151 0.01889 0.01259 -0.0438 0.0184 0.8958
9.500 1.1206 0.01986 0.01367 -0.0410 0.0179 0.9163
9.750 1.1313 0.02040 0.01433 -0.0387 0.0176 0.9451
10.000 1.1483 0.02115 0.01517 -0.0381 0.0172 1.0000
10.250 1.1627 0.02200 0.01605 -0.0371 0.0168 1.0000
10.500 1.1767 0.02288 0.01697 -0.0360 0.0162 1.0000
10.750 1.1893 0.02388 0.01800 -0.0348 0.0159 1.0000
11.000 1.2026 0.02483 0.01898 -0.0338 0.0155 1.0000
11.250 1.2137 0.02597 0.02015 -0.0326 0.0151 1.0000
11.500 1.2191 0.02757 0.02179 -0.0309 0.0146 1.0000
11.750 1.2224 0.02939 0.02369 -0.0292 0.0143 1.0000
12.000 1.2340 0.03059 0.02494 -0.0282 0.0142 1.0000
12.250 1.2472 0.03167 0.02608 -0.0275 0.0140 1.0000
12.500 1.2578 0.03299 0.02746 -0.0265 0.0138 1.0000
12.750 1.2675 0.03443 0.02896 -0.0256 0.0137 1.0000
13.000 1.2777 0.03585 0.03044 -0.0248 0.0134 1.0000
13.250 1.2868 0.03739 0.03204 -0.0240 0.0133 1.0000
13.500 1.2967 0.03889 0.03360 -0.0233 0.0130 1.0000
13.750 1.3055 0.04053 0.03531 -0.0226 0.0128 1.0000
14.000 1.3134 0.04230 0.03715 -0.0220 0.0126 1.0000
14.250 1.3224 0.04398 0.03888 -0.0215 0.0124 1.0000
14.500 1.3295 0.04589 0.04086 -0.0210 0.0123 1.0000
14.750 1.3372 0.04778 0.04281 -0.0206 0.0121 1.0000
15.000 1.3440 0.04981 0.04489 -0.0203 0.0120 1.0000
15.250 1.3488 0.05209 0.04724 -0.0200 0.0118 1.0000
15.500 1.3531 0.05448 0.04971 -0.0197 0.0117 1.0000
15.750 1.3516 0.05767 0.05302 -0.0192 0.0114 1.0000
16.000 1.3530 0.06060 0.05608 -0.0191 0.0112 1.0000
16.250 1.3559 0.06334 0.05892 -0.0193 0.0112 1.0000
16.500 1.3581 0.06625 0.06194 -0.0196 0.0111 1.0000
16.750 1.3592 0.06937 0.06518 -0.0200 0.0110 1.0000
17.000 1.3596 0.07266 0.06859 -0.0206 0.0110 1.0000
17.250 1.3589 0.07619 0.07224 -0.0215 0.0109 1.0000
17.500 1.3561 0.08010 0.07628 -0.0225 0.0108 1.0000
17.750 1.3519 0.08437 0.08068 -0.0237 0.0107 1.0000
18.000 1.3468 0.08889 0.08533 -0.0252 0.0106 1.0000
18.250 1.3400 0.09379 0.09038 -0.0270 0.0106 1.0000
18.500 1.3317 0.09905 0.09579 -0.0292 0.0105 1.0000
18.750 1.3213 0.10489 0.10177 -0.0319 0.0104 1.0000
19.000 1.3111 0.11087 0.10790 -0.0348 0.0104 1.0000
19.250 1.2971 0.11773 0.11493 -0.0384 0.0103 1.0000
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