NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 500,000 Max Cl/Cd: 91.13 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415-il-500000-n5.txt Download as CSV file: xf-naca652415-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7597 0.07419 0.07127 -0.0715 1.0000 0.0126
-15.250 -0.8016 0.06321 0.06002 -0.0784 1.0000 0.0125
-15.000 -0.8215 0.05723 0.05385 -0.0816 1.0000 0.0127
-14.750 -0.8391 0.05216 0.04860 -0.0837 1.0000 0.0128
-14.500 -0.8519 0.04808 0.04435 -0.0849 1.0000 0.0130
-14.250 -0.8622 0.04454 0.04063 -0.0854 1.0000 0.0131
-14.000 -0.8712 0.04134 0.03724 -0.0854 1.0000 0.0133
-13.750 -0.8772 0.03862 0.03433 -0.0850 1.0000 0.0135
-13.500 -0.8809 0.03626 0.03180 -0.0841 1.0000 0.0137
-13.250 -0.8827 0.03422 0.02959 -0.0829 1.0000 0.0138
-13.000 -0.8823 0.03253 0.02774 -0.0814 1.0000 0.0140
-12.750 -0.8694 0.03087 0.02599 -0.0822 0.9886 0.0144
-12.500 -0.8447 0.02955 0.02461 -0.0848 0.9769 0.0147
-12.250 -0.8168 0.02833 0.02330 -0.0877 0.9658 0.0150
-12.000 -0.7879 0.02714 0.02200 -0.0906 0.9550 0.0154
-11.750 -0.7610 0.02585 0.02056 -0.0929 0.9429 0.0158
-11.500 -0.7385 0.02472 0.01926 -0.0939 0.9287 0.0162
-11.250 -0.7211 0.02372 0.01807 -0.0936 0.9144 0.0166
-11.000 -0.7063 0.02283 0.01701 -0.0926 0.9011 0.0170
-10.750 -0.6918 0.02212 0.01614 -0.0912 0.8894 0.0173
-10.500 -0.6779 0.02130 0.01519 -0.0898 0.8791 0.0176
-10.250 -0.6648 0.02057 0.01439 -0.0881 0.8689 0.0180
-10.000 -0.6508 0.02010 0.01385 -0.0865 0.8593 0.0184
-9.500 -0.6151 0.01904 0.01263 -0.0843 0.8431 0.0192
-9.250 -0.5962 0.01849 0.01198 -0.0833 0.8358 0.0196
-9.000 -0.5765 0.01795 0.01136 -0.0824 0.8288 0.0201
-8.750 -0.5563 0.01747 0.01078 -0.0815 0.8216 0.0206
-8.500 -0.5356 0.01699 0.01020 -0.0807 0.8151 0.0211
-8.250 -0.5138 0.01660 0.00971 -0.0800 0.8083 0.0215
-8.000 -0.4951 0.01590 0.00896 -0.0790 0.8023 0.0220
-7.750 -0.4741 0.01540 0.00842 -0.0783 0.7963 0.0225
-7.500 -0.4521 0.01498 0.00796 -0.0777 0.7902 0.0231
-7.250 -0.4295 0.01461 0.00753 -0.0771 0.7846 0.0236
-7.000 -0.4064 0.01423 0.00711 -0.0767 0.7786 0.0244
-6.750 -0.3830 0.01389 0.00670 -0.0762 0.7729 0.0251
-6.500 -0.3593 0.01354 0.00629 -0.0758 0.7681 0.0257
-6.250 -0.3349 0.01322 0.00591 -0.0755 0.7628 0.0262
-6.000 -0.3116 0.01279 0.00544 -0.0751 0.7575 0.0272
-5.750 -0.2871 0.01247 0.00508 -0.0748 0.7527 0.0283
-5.500 -0.2617 0.01219 0.00477 -0.0746 0.7475 0.0294
-5.250 -0.2360 0.01194 0.00448 -0.0745 0.7426 0.0308
-5.000 -0.2100 0.01173 0.00421 -0.0744 0.7384 0.0323
-4.750 -0.1841 0.01145 0.00393 -0.0744 0.7341 0.0348
-4.500 -0.1576 0.01123 0.00368 -0.0744 0.7294 0.0377
-4.250 -0.1312 0.01102 0.00345 -0.0744 0.7249 0.0420
-4.000 -0.1046 0.01081 0.00324 -0.0744 0.7208 0.0502
-3.750 -0.0781 0.01052 0.00304 -0.0745 0.7166 0.0709
-3.500 -0.0526 0.01008 0.00280 -0.0745 0.7125 0.1253
-3.250 -0.0278 0.00947 0.00253 -0.0747 0.7086 0.2185
-3.000 -0.0033 0.00870 0.00220 -0.0749 0.7049 0.3489
-2.750 0.0219 0.00797 0.00201 -0.0752 0.7009 0.4923
-2.500 0.0496 0.00781 0.00200 -0.0754 0.6968 0.5504
-2.250 0.0775 0.00776 0.00205 -0.0755 0.6931 0.5967
-2.000 0.1056 0.00779 0.00212 -0.0756 0.6899 0.6245
-1.750 0.1344 0.00781 0.00214 -0.0758 0.6865 0.6369
-1.500 0.1632 0.00780 0.00212 -0.0761 0.6828 0.6412
-1.250 0.1921 0.00782 0.00209 -0.0764 0.6790 0.6449
-1.000 0.2210 0.00784 0.00206 -0.0767 0.6756 0.6485
-0.750 0.2498 0.00786 0.00205 -0.0770 0.6726 0.6515
-0.500 0.2786 0.00786 0.00206 -0.0773 0.6694 0.6548
-0.250 0.3074 0.00787 0.00207 -0.0777 0.6659 0.6583
0.000 0.3362 0.00790 0.00208 -0.0780 0.6625 0.6618
0.250 0.3650 0.00794 0.00208 -0.0783 0.6593 0.6653
0.500 0.3937 0.00796 0.00212 -0.0786 0.6564 0.6685
0.750 0.4224 0.00798 0.00217 -0.0789 0.6532 0.6720
1.000 0.4511 0.00801 0.00221 -0.0792 0.6498 0.6756
1.250 0.4797 0.00805 0.00225 -0.0795 0.6465 0.6792
1.500 0.5084 0.00810 0.00229 -0.0798 0.6436 0.6829
1.750 0.5369 0.00814 0.00237 -0.0800 0.6407 0.6864
2.000 0.5654 0.00817 0.00245 -0.0803 0.6373 0.6902
2.250 0.5939 0.00822 0.00253 -0.0805 0.6338 0.6941
2.500 0.6224 0.00828 0.00260 -0.0808 0.6304 0.6980
2.750 0.6504 0.00834 0.00268 -0.0810 0.6261 0.7016
3.000 0.6782 0.00836 0.00278 -0.0811 0.6198 0.7058
3.250 0.7058 0.00842 0.00285 -0.0811 0.6128 0.7102
3.500 0.7329 0.00848 0.00293 -0.0811 0.6025 0.7146
3.750 0.7588 0.00854 0.00300 -0.0808 0.5867 0.7185
4.000 0.7834 0.00865 0.00307 -0.0802 0.5649 0.7227
4.250 0.8065 0.00885 0.00318 -0.0794 0.5322 0.7276
4.750 0.8425 0.00983 0.00370 -0.0762 0.4168 0.7374
5.000 0.8516 0.01087 0.00431 -0.0732 0.3283 0.7428
5.250 0.8621 0.01183 0.00492 -0.0706 0.2529 0.7482
5.500 0.8729 0.01270 0.00550 -0.0680 0.1894 0.7533
5.750 0.8842 0.01348 0.00605 -0.0655 0.1379 0.7591
6.000 0.8943 0.01421 0.00658 -0.0627 0.0971 0.7654
6.250 0.9045 0.01480 0.00709 -0.0599 0.0709 0.7717
6.500 0.9164 0.01542 0.00763 -0.0575 0.0513 0.7788
6.750 0.9300 0.01598 0.00816 -0.0554 0.0406 0.7854
7.000 0.9450 0.01648 0.00868 -0.0536 0.0347 0.7925
7.250 0.9602 0.01701 0.00924 -0.0519 0.0308 0.7997
7.500 0.9752 0.01754 0.00981 -0.0502 0.0280 0.8073
7.750 0.9897 0.01814 0.01044 -0.0485 0.0260 0.8156
8.000 1.0050 0.01867 0.01106 -0.0469 0.0244 0.8243
8.250 1.0193 0.01929 0.01174 -0.0453 0.0231 0.8334
8.500 1.0321 0.02000 0.01250 -0.0435 0.0217 0.8433
8.750 1.0452 0.02071 0.01328 -0.0418 0.0208 0.8533
9.000 1.0585 0.02141 0.01407 -0.0402 0.0201 0.8646
9.250 1.0709 0.02215 0.01489 -0.0385 0.0193 0.8779
9.500 1.0825 0.02291 0.01574 -0.0367 0.0185 0.8937
9.750 1.0923 0.02369 0.01661 -0.0347 0.0179 0.9144
10.000 1.1017 0.02464 0.01764 -0.0328 0.0172 0.9449
10.500 1.1306 0.02661 0.01974 -0.0314 0.0162 1.0000
10.750 1.1429 0.02772 0.02091 -0.0304 0.0158 1.0000
11.000 1.1555 0.02883 0.02207 -0.0295 0.0155 1.0000
11.250 1.1671 0.03004 0.02333 -0.0285 0.0151 1.0000
11.500 1.1787 0.03127 0.02460 -0.0277 0.0148 1.0000
11.750 1.1896 0.03257 0.02595 -0.0268 0.0144 1.0000
12.000 1.1991 0.03401 0.02744 -0.0259 0.0142 1.0000
12.250 1.2074 0.03559 0.02906 -0.0250 0.0139 1.0000
12.500 1.2138 0.03737 0.03090 -0.0240 0.0137 1.0000
12.750 1.2238 0.03887 0.03247 -0.0233 0.0135 1.0000
13.000 1.2329 0.04048 0.03417 -0.0226 0.0133 1.0000
13.250 1.2415 0.04218 0.03595 -0.0220 0.0132 1.0000
13.500 1.2499 0.04394 0.03780 -0.0214 0.0130 1.0000
13.750 1.2576 0.04579 0.03974 -0.0209 0.0129 1.0000
14.000 1.2654 0.04769 0.04172 -0.0204 0.0126 1.0000
14.250 1.2729 0.04965 0.04377 -0.0201 0.0125 1.0000
14.500 1.2797 0.05172 0.04593 -0.0198 0.0123 1.0000
14.750 1.2868 0.05379 0.04808 -0.0196 0.0121 1.0000
15.000 1.2930 0.05600 0.05038 -0.0195 0.0119 1.0000
15.250 1.2983 0.05839 0.05286 -0.0195 0.0118 1.0000
15.500 1.3039 0.06077 0.05533 -0.0196 0.0116 1.0000
15.750 1.3078 0.06340 0.05805 -0.0198 0.0115 1.0000
16.000 1.3111 0.06617 0.06090 -0.0200 0.0113 1.0000
16.250 1.3136 0.06910 0.06393 -0.0204 0.0113 1.0000
16.500 1.3149 0.07225 0.06717 -0.0210 0.0111 1.0000
16.750 1.3152 0.07563 0.07065 -0.0216 0.0110 1.0000
17.000 1.3139 0.07927 0.07441 -0.0224 0.0109 1.0000
17.250 1.3107 0.08327 0.07853 -0.0234 0.0108 1.0000
17.500 1.3084 0.08731 0.08271 -0.0246 0.0107 1.0000
17.750 1.3049 0.09165 0.08721 -0.0261 0.0107 1.0000
18.000 1.3005 0.09622 0.09193 -0.0279 0.0106 1.0000
18.250 1.2938 0.10127 0.09715 -0.0300 0.0106 1.0000
18.500 1.2868 0.10655 0.10259 -0.0324 0.0105 1.0000
18.750 1.2783 0.11225 0.10846 -0.0352 0.0105 1.0000
19.000 1.2683 0.11837 0.11475 -0.0384 0.0104 1.0000
19.250 1.2570 0.12491 0.12146 -0.0420 0.0104 1.0000
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