NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 500,000 Max Cl/Cd: 101.44 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca642415-il-500000.txt Download as CSV file: xf-naca642415-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7417 0.06913 0.06597 -0.0710 1.0000 0.0210
-14.250 -0.7726 0.06183 0.05847 -0.0754 1.0000 0.0210
-14.000 -0.7920 0.05674 0.05321 -0.0780 1.0000 0.0210
-13.750 -0.8136 0.05172 0.04800 -0.0799 1.0000 0.0210
-13.500 -0.8324 0.04733 0.04342 -0.0808 1.0000 0.0211
-13.250 -0.8452 0.04380 0.03973 -0.0810 1.0000 0.0212
-13.000 -0.8460 0.04171 0.03761 -0.0807 1.0000 0.0215
-12.750 -0.8447 0.04008 0.03593 -0.0801 1.0000 0.0218
-12.500 -0.8450 0.03845 0.03424 -0.0791 1.0000 0.0220
-12.250 -0.8506 0.03647 0.03213 -0.0773 1.0000 0.0221
-12.000 -0.8475 0.03579 0.03147 -0.0754 1.0000 0.0226
-11.750 -0.8590 0.03458 0.03017 -0.0714 1.0000 0.0227
-11.500 -0.8654 0.03340 0.02890 -0.0681 0.9984 0.0230
-11.250 -0.8412 0.03094 0.02618 -0.0707 0.9912 0.0235
-11.000 -0.8155 0.02872 0.02368 -0.0729 0.9849 0.0241
-10.750 -0.7878 0.02697 0.02167 -0.0749 0.9785 0.0247
-10.500 -0.7581 0.02524 0.01968 -0.0771 0.9726 0.0253
-10.250 -0.7276 0.02342 0.01783 -0.0790 0.9669 0.0261
-10.000 -0.6959 0.02251 0.01687 -0.0809 0.9590 0.0269
-9.750 -0.6659 0.02154 0.01582 -0.0822 0.9497 0.0277
-9.500 -0.6372 0.02059 0.01474 -0.0831 0.9398 0.0285
-9.250 -0.6141 0.01982 0.01384 -0.0827 0.9270 0.0292
-9.000 -0.5917 0.01922 0.01311 -0.0821 0.9150 0.0298
-8.750 -0.5714 0.01804 0.01185 -0.0813 0.9044 0.0308
-8.500 -0.5508 0.01736 0.01114 -0.0805 0.8936 0.0317
-8.250 -0.5292 0.01688 0.01062 -0.0797 0.8833 0.0328
-7.750 -0.4851 0.01586 0.00944 -0.0782 0.8644 0.0348
-7.500 -0.4617 0.01548 0.00894 -0.0776 0.8562 0.0357
-7.250 -0.4427 0.01457 0.00800 -0.0767 0.8469 0.0372
-7.000 -0.4196 0.01413 0.00753 -0.0762 0.8392 0.0388
-6.750 -0.3955 0.01375 0.00710 -0.0758 0.8307 0.0407
-6.500 -0.3708 0.01344 0.00669 -0.0754 0.8234 0.0423
-6.250 -0.3483 0.01277 0.00601 -0.0749 0.8150 0.0449
-6.000 -0.3231 0.01243 0.00561 -0.0747 0.8080 0.0476
-5.750 -0.2971 0.01215 0.00528 -0.0745 0.8005 0.0507
-5.500 -0.2720 0.01169 0.00481 -0.0743 0.7934 0.0563
-5.250 -0.2459 0.01134 0.00444 -0.0743 0.7866 0.0633
-5.000 -0.2199 0.01093 0.00408 -0.0742 0.7793 0.0778
-4.750 -0.1945 0.01038 0.00369 -0.0743 0.7728 0.1219
-4.500 -0.1700 0.00950 0.00326 -0.0745 0.7653 0.2241
-4.250 -0.1461 0.00838 0.00279 -0.0749 0.7587 0.3929
-4.000 -0.1185 0.00810 0.00273 -0.0752 0.7518 0.4753
-3.750 -0.0901 0.00803 0.00267 -0.0753 0.7452 0.5050
-3.500 -0.0615 0.00802 0.00262 -0.0755 0.7392 0.5249
-3.250 -0.0327 0.00801 0.00259 -0.0757 0.7324 0.5402
-3.000 -0.0041 0.00801 0.00255 -0.0758 0.7263 0.5527
-2.750 0.0246 0.00801 0.00254 -0.0759 0.7201 0.5639
-2.500 0.0534 0.00804 0.00254 -0.0761 0.7137 0.5777
-2.000 0.1106 0.00819 0.00264 -0.0763 0.7016 0.6075
-1.750 0.1390 0.00821 0.00267 -0.0763 0.6955 0.6160
-1.500 0.1681 0.00825 0.00263 -0.0766 0.6899 0.6213
-1.250 0.1969 0.00822 0.00261 -0.0768 0.6838 0.6265
-1.000 0.2256 0.00824 0.00260 -0.0770 0.6784 0.6317
-0.750 0.2546 0.00828 0.00259 -0.0772 0.6732 0.6366
-0.500 0.2836 0.00828 0.00258 -0.0775 0.6676 0.6415
-0.250 0.3123 0.00829 0.00259 -0.0777 0.6625 0.6459
0.000 0.3412 0.00834 0.00261 -0.0780 0.6577 0.6509
0.250 0.3703 0.00836 0.00263 -0.0783 0.6524 0.6561
0.500 0.3989 0.00837 0.00265 -0.0785 0.6474 0.6609
0.750 0.4277 0.00845 0.00269 -0.0787 0.6428 0.6662
1.000 0.4567 0.00847 0.00275 -0.0790 0.6382 0.6723
1.250 0.4853 0.00849 0.00280 -0.0792 0.6336 0.6777
1.500 0.5140 0.00855 0.00286 -0.0794 0.6294 0.6834
1.750 0.5431 0.00864 0.00294 -0.0797 0.6253 0.6898
2.000 0.5714 0.00865 0.00302 -0.0798 0.6202 0.6954
2.250 0.5999 0.00869 0.00309 -0.0800 0.6151 0.7017
2.500 0.6287 0.00881 0.00317 -0.0803 0.6103 0.7085
2.750 0.6568 0.00883 0.00329 -0.0803 0.6058 0.7146
3.000 0.6853 0.00889 0.00339 -0.0805 0.6011 0.7219
3.250 0.7134 0.00896 0.00346 -0.0806 0.5953 0.7286
3.500 0.7409 0.00897 0.00355 -0.0805 0.5873 0.7360
3.750 0.7684 0.00905 0.00359 -0.0805 0.5781 0.7433
4.000 0.7952 0.00903 0.00367 -0.0803 0.5680 0.7503
4.500 0.8485 0.00916 0.00383 -0.0798 0.5456 0.7653
4.750 0.8755 0.00922 0.00394 -0.0797 0.5339 0.7735
5.000 0.9020 0.00929 0.00408 -0.0795 0.5241 0.7808
5.250 0.9284 0.00941 0.00422 -0.0792 0.5126 0.7893
5.500 0.9538 0.00952 0.00437 -0.0788 0.4981 0.7972
5.750 0.9792 0.00966 0.00454 -0.0784 0.4796 0.8064
6.000 1.0022 0.00988 0.00473 -0.0776 0.4515 0.8146
6.750 1.0374 0.01280 0.00655 -0.0703 0.2192 0.8439
7.000 1.0471 0.01383 0.00729 -0.0677 0.1603 0.8555
7.250 1.0563 0.01472 0.00797 -0.0648 0.1170 0.8674
7.500 1.0654 0.01549 0.00862 -0.0619 0.0872 0.8811
7.750 1.0709 0.01615 0.00923 -0.0582 0.0681 0.8979
8.000 1.0752 0.01677 0.00984 -0.0543 0.0569 0.9203
8.250 1.0820 0.01723 0.01037 -0.0509 0.0503 0.9694
8.500 1.0972 0.01801 0.01114 -0.0497 0.0448 1.0000
8.750 1.1098 0.01891 0.01201 -0.0482 0.0406 1.0000
9.000 1.1229 0.01977 0.01291 -0.0467 0.0379 1.0000
9.250 1.1358 0.02066 0.01382 -0.0453 0.0355 1.0000
9.500 1.1414 0.02203 0.01519 -0.0433 0.0332 1.0000
9.750 1.1553 0.02293 0.01615 -0.0421 0.0317 1.0000
10.000 1.1667 0.02401 0.01727 -0.0408 0.0301 1.0000
10.250 1.1758 0.02529 0.01857 -0.0395 0.0288 1.0000
10.500 1.1794 0.02703 0.02035 -0.0377 0.0275 1.0000
10.750 1.1912 0.02821 0.02159 -0.0367 0.0265 1.0000
11.000 1.2019 0.02951 0.02294 -0.0358 0.0255 1.0000
11.250 1.2113 0.03093 0.02440 -0.0348 0.0246 1.0000
11.500 1.2192 0.03252 0.02602 -0.0338 0.0240 1.0000
11.750 1.2221 0.03458 0.02812 -0.0325 0.0233 1.0000
12.000 1.2289 0.03638 0.02998 -0.0315 0.0227 1.0000
12.250 1.2387 0.03794 0.03162 -0.0308 0.0223 1.0000
12.500 1.2484 0.03953 0.03329 -0.0302 0.0217 1.0000
12.750 1.2571 0.04125 0.03507 -0.0295 0.0213 1.0000
13.000 1.2661 0.04297 0.03686 -0.0290 0.0208 1.0000
13.250 1.2748 0.04476 0.03870 -0.0284 0.0204 1.0000
13.500 1.2833 0.04659 0.04058 -0.0280 0.0200 1.0000
13.750 1.2916 0.04848 0.04250 -0.0276 0.0196 1.0000
14.000 1.2998 0.05049 0.04454 -0.0270 0.0192 1.0000
14.250 1.3084 0.05254 0.04669 -0.0264 0.0188 1.0000
14.500 1.3155 0.05467 0.04894 -0.0263 0.0186 1.0000
14.750 1.3224 0.05689 0.05128 -0.0262 0.0183 1.0000
15.000 1.3289 0.05921 0.05372 -0.0261 0.0180 1.0000
15.250 1.3344 0.06171 0.05634 -0.0261 0.0178 1.0000
15.500 1.3395 0.06431 0.05905 -0.0261 0.0176 1.0000
15.750 1.3432 0.06711 0.06197 -0.0264 0.0173 1.0000
16.000 1.3461 0.07005 0.06503 -0.0267 0.0171 1.0000
16.250 1.3480 0.07321 0.06833 -0.0272 0.0170 1.0000
16.500 1.3482 0.07664 0.07188 -0.0279 0.0168 1.0000
16.750 1.3472 0.08028 0.07566 -0.0288 0.0166 1.0000
17.000 1.3452 0.08418 0.07968 -0.0299 0.0165 1.0000
17.250 1.3419 0.08835 0.08399 -0.0312 0.0164 1.0000
17.500 1.3373 0.09279 0.08857 -0.0328 0.0163 1.0000
17.750 1.3318 0.09747 0.09338 -0.0346 0.0162 1.0000
18.000 1.3241 0.10266 0.09872 -0.0368 0.0161 1.0000
18.250 1.3153 0.10815 0.10437 -0.0394 0.0160 1.0000
18.500 1.3045 0.11416 0.11054 -0.0424 0.0160 1.0000
18.750 1.2903 0.12097 0.11753 -0.0461 0.0159 1.0000
19.000 1.2742 0.12844 0.12519 -0.0504 0.0159 1.0000
19.250 1.2546 0.13698 0.13394 -0.0558 0.0160 1.0000
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Polar data table (+)
Polar graphs
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