NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 500,000 Max Cl/Cd: 100.89 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415a05-il-500000-n5.txt Download as CSV file: xf-naca652415a05-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7104 0.06579 0.06286 -0.0723 0.8708 0.0124
-14.250 -0.7635 0.05398 0.05071 -0.0801 0.8601 0.0122
-14.000 -0.7927 0.04761 0.04406 -0.0829 0.8499 0.0123
-13.750 -0.8170 0.04269 0.03886 -0.0840 0.8404 0.0123
-13.500 -0.8316 0.03912 0.03503 -0.0839 0.8312 0.0126
-13.250 -0.8439 0.03603 0.03167 -0.0830 0.8230 0.0127
-13.000 -0.8525 0.03336 0.02870 -0.0816 0.8146 0.0130
-12.750 -0.8536 0.03144 0.02652 -0.0800 0.8076 0.0132
-12.500 -0.8511 0.02999 0.02492 -0.0782 0.8002 0.0134
-12.250 -0.8466 0.02875 0.02353 -0.0763 0.7939 0.0135
-12.000 -0.8364 0.02809 0.02283 -0.0747 0.7878 0.0137
-11.750 -0.8264 0.02745 0.02209 -0.0728 0.7818 0.0140
-11.500 -0.8146 0.02694 0.02150 -0.0710 0.7767 0.0142
-11.250 -0.8011 0.02601 0.02044 -0.0697 0.7714 0.0145
-11.000 -0.7861 0.02512 0.01941 -0.0684 0.7662 0.0148
-10.750 -0.7701 0.02418 0.01829 -0.0673 0.7614 0.0152
-10.500 -0.7527 0.02319 0.01711 -0.0663 0.7566 0.0157
-10.250 -0.7344 0.02222 0.01594 -0.0654 0.7517 0.0161
-10.000 -0.7151 0.02137 0.01492 -0.0645 0.7473 0.0165
-9.750 -0.6947 0.02076 0.01425 -0.0638 0.7434 0.0169
-9.500 -0.6726 0.02028 0.01374 -0.0633 0.7392 0.0173
-9.250 -0.6502 0.01982 0.01320 -0.0629 0.7351 0.0177
-9.000 -0.6275 0.01933 0.01261 -0.0624 0.7313 0.0183
-8.750 -0.6048 0.01873 0.01190 -0.0619 0.7277 0.0188
-8.500 -0.5817 0.01812 0.01118 -0.0614 0.7237 0.0194
-8.250 -0.5581 0.01758 0.01052 -0.0610 0.7197 0.0199
-8.000 -0.5353 0.01695 0.00980 -0.0605 0.7160 0.0204
-7.750 -0.5115 0.01651 0.00933 -0.0601 0.7127 0.0210
-7.500 -0.4867 0.01613 0.00892 -0.0599 0.7093 0.0216
-7.250 -0.4621 0.01571 0.00845 -0.0596 0.7059 0.0222
-7.000 -0.4376 0.01528 0.00795 -0.0593 0.7026 0.0228
-6.750 -0.4130 0.01487 0.00747 -0.0590 0.6995 0.0234
-6.500 -0.3876 0.01456 0.00706 -0.0587 0.6967 0.0242
-6.250 -0.3633 0.01407 0.00656 -0.0584 0.6937 0.0249
-6.000 -0.3385 0.01366 0.00613 -0.0581 0.6905 0.0256
-5.750 -0.3131 0.01333 0.00576 -0.0579 0.6873 0.0264
-5.500 -0.2874 0.01303 0.00541 -0.0578 0.6843 0.0272
-5.250 -0.2615 0.01276 0.00510 -0.0576 0.6816 0.0282
-5.000 -0.2351 0.01251 0.00480 -0.0575 0.6791 0.0292
-4.750 -0.2091 0.01220 0.00447 -0.0574 0.6764 0.0302
-4.500 -0.1830 0.01189 0.00415 -0.0573 0.6737 0.0316
-4.250 -0.1564 0.01166 0.00389 -0.0573 0.6711 0.0330
-4.000 -0.1295 0.01147 0.00366 -0.0573 0.6687 0.0347
-3.750 -0.1025 0.01129 0.00344 -0.0573 0.6663 0.0366
-3.500 -0.0755 0.01108 0.00323 -0.0573 0.6640 0.0402
-3.250 -0.0481 0.01091 0.00306 -0.0574 0.6614 0.0441
-3.000 -0.0209 0.01071 0.00290 -0.0574 0.6588 0.0523
-2.750 0.0059 0.01047 0.00273 -0.0575 0.6565 0.0746
-2.500 0.0316 0.01008 0.00256 -0.0574 0.6543 0.1350
-2.250 0.0559 0.00951 0.00236 -0.0573 0.6522 0.2419
-2.000 0.0786 0.00877 0.00213 -0.0570 0.6502 0.3936
-1.750 0.1030 0.00829 0.00206 -0.0567 0.6481 0.5136
-1.500 0.1291 0.00806 0.00207 -0.0565 0.6457 0.5825
-1.250 0.1552 0.00789 0.00212 -0.0562 0.6434 0.6453
-1.000 0.1823 0.00784 0.00217 -0.0561 0.6413 0.6808
-0.750 0.2104 0.00783 0.00218 -0.0562 0.6393 0.6973
-0.500 0.2389 0.00784 0.00218 -0.0564 0.6373 0.7076
-0.250 0.2675 0.00786 0.00217 -0.0567 0.6354 0.7149
0.000 0.2962 0.00789 0.00218 -0.0569 0.6334 0.7215
0.250 0.3248 0.00789 0.00221 -0.0572 0.6315 0.7285
0.500 0.3536 0.00792 0.00224 -0.0575 0.6295 0.7358
0.750 0.3821 0.00793 0.00228 -0.0578 0.6274 0.7423
1.000 0.4106 0.00795 0.00232 -0.0580 0.6252 0.7496
1.250 0.4391 0.00798 0.00236 -0.0583 0.6231 0.7567
1.500 0.4675 0.00801 0.00240 -0.0585 0.6213 0.7642
1.750 0.4960 0.00806 0.00245 -0.0588 0.6195 0.7714
2.000 0.5243 0.00811 0.00253 -0.0590 0.6176 0.7786
2.250 0.5527 0.00814 0.00261 -0.0593 0.6155 0.7866
2.500 0.5807 0.00818 0.00271 -0.0594 0.6133 0.7941
2.750 0.6090 0.00822 0.00280 -0.0597 0.6111 0.8022
3.000 0.6370 0.00826 0.00290 -0.0598 0.6088 0.8094
3.250 0.6650 0.00832 0.00299 -0.0600 0.6066 0.8179
3.500 0.6928 0.00838 0.00308 -0.0601 0.6043 0.8257
3.750 0.7205 0.00843 0.00319 -0.0602 0.6011 0.8341
4.000 0.7477 0.00846 0.00331 -0.0603 0.5964 0.8421
4.250 0.7746 0.00848 0.00337 -0.0602 0.5905 0.8510
4.500 0.8012 0.00852 0.00347 -0.0601 0.5843 0.8593
4.750 0.8276 0.00855 0.00356 -0.0599 0.5767 0.8685
5.000 0.8524 0.00857 0.00362 -0.0594 0.5618 0.8776
5.250 0.8747 0.00867 0.00366 -0.0584 0.5313 0.8878
5.500 0.8939 0.00893 0.00381 -0.0570 0.4899 0.8989
5.750 0.9049 0.00959 0.00419 -0.0542 0.4259 0.9126
6.000 0.9068 0.01066 0.00490 -0.0501 0.3484 0.9313
6.250 0.9131 0.01170 0.00565 -0.0470 0.2835 0.9539
6.500 0.9302 0.01295 0.00658 -0.0469 0.2147 0.9925
6.750 0.9283 0.01395 0.00737 -0.0427 0.1727 1.0000
7.000 0.9299 0.01500 0.00823 -0.0394 0.1359 1.0000
7.250 0.9336 0.01609 0.00916 -0.0366 0.1044 1.0000
7.500 0.9383 0.01723 0.01015 -0.0341 0.0760 1.0000
8.000 0.9573 0.01919 0.01195 -0.0305 0.0457 1.0000
8.250 0.9684 0.02014 0.01286 -0.0290 0.0367 1.0000
8.500 0.9806 0.02105 0.01375 -0.0277 0.0315 1.0000
8.750 0.9934 0.02194 0.01464 -0.0265 0.0281 1.0000
9.000 1.0063 0.02286 0.01558 -0.0253 0.0256 1.0000
9.250 1.0195 0.02376 0.01650 -0.0242 0.0237 1.0000
9.500 1.0307 0.02482 0.01757 -0.0230 0.0217 1.0000
9.750 1.0441 0.02576 0.01854 -0.0220 0.0207 1.0000
10.000 1.0569 0.02675 0.01957 -0.0210 0.0196 1.0000
10.250 1.0687 0.02782 0.02067 -0.0200 0.0186 1.0000
10.500 1.0788 0.02904 0.02191 -0.0189 0.0177 1.0000
10.750 1.0905 0.03016 0.02308 -0.0180 0.0171 1.0000
11.000 1.1025 0.03127 0.02425 -0.0171 0.0167 1.0000
11.250 1.1133 0.03250 0.02553 -0.0162 0.0161 1.0000
11.500 1.1239 0.03378 0.02685 -0.0153 0.0157 1.0000
11.750 1.1348 0.03505 0.02816 -0.0146 0.0152 1.0000
12.000 1.1445 0.03646 0.02962 -0.0137 0.0149 1.0000
12.250 1.1534 0.03796 0.03116 -0.0130 0.0146 1.0000
12.500 1.1604 0.03966 0.03291 -0.0121 0.0142 1.0000
12.750 1.1683 0.04131 0.03461 -0.0114 0.0140 1.0000
13.000 1.1774 0.04289 0.03627 -0.0108 0.0137 1.0000
13.250 1.1858 0.04457 0.03801 -0.0102 0.0136 1.0000
13.500 1.1949 0.04621 0.03972 -0.0097 0.0133 1.0000
13.750 1.2042 0.04784 0.04143 -0.0093 0.0129 1.0000
14.000 1.2106 0.04979 0.04345 -0.0088 0.0128 1.0000
14.250 1.2181 0.05169 0.04541 -0.0085 0.0126 1.0000
14.500 1.2252 0.05364 0.04743 -0.0082 0.0123 1.0000
14.750 1.2330 0.05556 0.04941 -0.0080 0.0121 1.0000
15.000 1.2388 0.05772 0.05164 -0.0078 0.0120 1.0000
15.250 1.2447 0.05991 0.05390 -0.0076 0.0118 1.0000
15.500 1.2497 0.06225 0.05632 -0.0076 0.0117 1.0000
15.750 1.2547 0.06461 0.05874 -0.0076 0.0115 1.0000
16.000 1.2573 0.06729 0.06149 -0.0077 0.0113 1.0000
16.250 1.2597 0.07001 0.06429 -0.0077 0.0112 1.0000
16.500 1.2626 0.07276 0.06712 -0.0079 0.0111 1.0000
16.750 1.2665 0.07546 0.06994 -0.0083 0.0111 1.0000
17.000 1.2689 0.07839 0.07298 -0.0087 0.0110 1.0000
17.250 1.2715 0.08136 0.07606 -0.0092 0.0109 1.0000
17.500 1.2726 0.08457 0.07939 -0.0099 0.0108 1.0000
17.750 1.2735 0.08792 0.08288 -0.0107 0.0107 1.0000
18.000 1.2730 0.09150 0.08659 -0.0117 0.0106 1.0000
18.250 1.2725 0.09516 0.09037 -0.0128 0.0105 1.0000
18.500 1.2699 0.09919 0.09453 -0.0141 0.0104 1.0000
18.750 1.2667 0.10342 0.09890 -0.0157 0.0103 1.0000
19.000 1.2633 0.10778 0.10339 -0.0174 0.0103 1.0000
19.250 1.2587 0.11243 0.10818 -0.0194 0.0102 1.0000
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Polar data table (+)
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