NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.9 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65410-il-1000000-n5.txt Download as CSV file: xf-naca65410-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7535 0.02223 0.01883 -0.0763 0.9753 0.0045
-10.000 -0.7284 0.02034 0.01667 -0.0774 0.9690 0.0048
-9.750 -0.7018 0.01852 0.01457 -0.0786 0.9633 0.0050
-9.500 -0.6757 0.01727 0.01310 -0.0793 0.9553 0.0051
-9.250 -0.6495 0.01625 0.01189 -0.0798 0.9471 0.0052
-9.000 -0.6253 0.01507 0.01051 -0.0799 0.9378 0.0056
-8.750 -0.6010 0.01431 0.00962 -0.0798 0.9281 0.0058
-8.500 -0.5755 0.01387 0.00909 -0.0797 0.9196 0.0062
-8.250 -0.5503 0.01343 0.00854 -0.0795 0.9106 0.0065
-8.000 -0.5252 0.01296 0.00797 -0.0793 0.9020 0.0069
-7.750 -0.5000 0.01252 0.00743 -0.0791 0.8939 0.0073
-7.500 -0.4745 0.01209 0.00690 -0.0790 0.8855 0.0076
-7.250 -0.4489 0.01170 0.00641 -0.0788 0.8780 0.0080
-7.000 -0.4232 0.01131 0.00596 -0.0787 0.8700 0.0087
-6.750 -0.3966 0.01113 0.00574 -0.0787 0.8626 0.0092
-6.500 -0.3701 0.01089 0.00544 -0.0786 0.8550 0.0099
-6.250 -0.3437 0.01058 0.00506 -0.0786 0.8482 0.0105
-6.000 -0.3171 0.01031 0.00472 -0.0785 0.8408 0.0110
-5.750 -0.2906 0.00999 0.00432 -0.0785 0.8338 0.0115
-5.500 -0.2642 0.00963 0.00390 -0.0784 0.8264 0.0125
-5.250 -0.2370 0.00949 0.00374 -0.0785 0.8200 0.0134
-5.000 -0.2097 0.00930 0.00352 -0.0786 0.8133 0.0143
-4.750 -0.1826 0.00908 0.00324 -0.0786 0.8070 0.0150
-4.500 -0.1551 0.00889 0.00299 -0.0787 0.8002 0.0156
-4.250 -0.1277 0.00877 0.00283 -0.0787 0.7938 0.0160
-4.000 -0.1005 0.00839 0.00237 -0.0788 0.7872 0.0176
-3.750 -0.0729 0.00820 0.00215 -0.0789 0.7811 0.0188
-3.500 -0.0451 0.00805 0.00197 -0.0791 0.7754 0.0200
-3.250 -0.0172 0.00793 0.00182 -0.0792 0.7691 0.0216
-3.000 0.0107 0.00782 0.00167 -0.0793 0.7633 0.0227
-2.750 0.0387 0.00769 0.00149 -0.0795 0.7569 0.0243
-2.500 0.0665 0.00756 0.00135 -0.0796 0.7512 0.0283
-2.250 0.0947 0.00746 0.00124 -0.0798 0.7456 0.0317
-2.000 0.1228 0.00737 0.00114 -0.0799 0.7397 0.0381
-1.750 0.1508 0.00720 0.00105 -0.0802 0.7342 0.0664
-1.500 0.1788 0.00685 0.00095 -0.0806 0.7282 0.1578
-1.250 0.2064 0.00625 0.00083 -0.0811 0.7227 0.3264
-1.000 0.2340 0.00541 0.00076 -0.0819 0.7172 0.5778
-0.750 0.2620 0.00528 0.00078 -0.0821 0.7114 0.6366
-0.500 0.2902 0.00525 0.00080 -0.0822 0.7061 0.6627
-0.250 0.3184 0.00522 0.00083 -0.0823 0.7002 0.6885
0.250 0.3752 0.00526 0.00086 -0.0827 0.6893 0.7032
0.750 0.4317 0.00532 0.00092 -0.0830 0.6783 0.7154
1.000 0.4596 0.00537 0.00095 -0.0831 0.6668 0.7219
1.250 0.4870 0.00545 0.00099 -0.0830 0.6493 0.7278
1.500 0.5146 0.00552 0.00103 -0.0831 0.6357 0.7342
1.750 0.5421 0.00560 0.00109 -0.0831 0.6200 0.7403
2.000 0.5687 0.00575 0.00116 -0.0829 0.5918 0.7468
2.500 0.6109 0.00714 0.00165 -0.0809 0.3685 0.7596
2.750 0.6316 0.00798 0.00202 -0.0799 0.2531 0.7667
3.000 0.6523 0.00881 0.00240 -0.0790 0.1420 0.7736
3.250 0.6749 0.00944 0.00273 -0.0784 0.0675 0.7809
3.500 0.6998 0.00979 0.00298 -0.0780 0.0386 0.7877
3.750 0.7260 0.01001 0.00319 -0.0778 0.0313 0.7951
4.000 0.7519 0.01022 0.00341 -0.0776 0.0268 0.8026
4.250 0.7781 0.01043 0.00364 -0.0774 0.0237 0.8107
4.500 0.8041 0.01061 0.00387 -0.0772 0.0219 0.8185
4.750 0.8297 0.01086 0.00413 -0.0770 0.0192 0.8263
5.000 0.8547 0.01114 0.00444 -0.0766 0.0163 0.8344
5.250 0.8801 0.01137 0.00471 -0.0763 0.0154 0.8426
5.500 0.9051 0.01163 0.00502 -0.0759 0.0143 0.8518
5.750 0.9295 0.01191 0.00535 -0.0754 0.0134 0.8610
6.000 0.9535 0.01223 0.00570 -0.0748 0.0126 0.8705
6.250 0.9765 0.01262 0.00616 -0.0741 0.0118 0.8812
6.500 0.9979 0.01312 0.00675 -0.0730 0.0112 0.8928
6.750 1.0204 0.01346 0.00717 -0.0722 0.0111 0.9053
7.000 1.0420 0.01384 0.00763 -0.0711 0.0109 0.9182
7.250 1.0629 0.01421 0.00807 -0.0700 0.0106 0.9325
7.500 1.0827 0.01454 0.00848 -0.0686 0.0102 0.9518
7.750 1.1057 0.01493 0.00894 -0.0680 0.0099 1.0000
8.000 1.1281 0.01544 0.00950 -0.0673 0.0095 1.0000
8.250 1.1504 0.01594 0.01004 -0.0667 0.0092 1.0000
8.500 1.1727 0.01639 0.01053 -0.0660 0.0088 1.0000
8.750 1.1942 0.01691 0.01108 -0.0653 0.0085 1.0000
9.000 1.2137 0.01762 0.01183 -0.0642 0.0080 1.0000
9.250 1.2288 0.01876 0.01308 -0.0625 0.0076 1.0000
9.500 1.2487 0.01936 0.01374 -0.0615 0.0075 1.0000
9.750 1.2688 0.01989 0.01434 -0.0606 0.0074 1.0000
10.000 1.2872 0.02049 0.01502 -0.0593 0.0072 1.0000
10.250 1.3045 0.02106 0.01566 -0.0579 0.0070 1.0000
10.500 1.3214 0.02160 0.01626 -0.0565 0.0067 1.0000
10.750 1.3371 0.02224 0.01696 -0.0549 0.0064 1.0000
11.000 1.3525 0.02288 0.01767 -0.0534 0.0062 1.0000
11.250 1.3673 0.02357 0.01843 -0.0518 0.0060 1.0000
11.500 1.3825 0.02420 0.01911 -0.0503 0.0057 1.0000
11.750 1.3964 0.02497 0.01994 -0.0488 0.0056 1.0000
12.000 1.4097 0.02579 0.02081 -0.0473 0.0053 1.0000
12.250 1.4188 0.02703 0.02217 -0.0454 0.0051 1.0000
12.500 1.4288 0.02819 0.02344 -0.0437 0.0050 1.0000
12.750 1.4391 0.02935 0.02470 -0.0421 0.0049 1.0000
13.000 1.4483 0.03062 0.02609 -0.0405 0.0048 1.0000
13.250 1.4572 0.03193 0.02751 -0.0390 0.0046 1.0000
13.500 1.4660 0.03327 0.02896 -0.0377 0.0044 1.0000
13.750 1.4729 0.03481 0.03061 -0.0363 0.0043 1.0000
14.000 1.4813 0.03623 0.03212 -0.0352 0.0041 1.0000
14.250 1.4876 0.03790 0.03389 -0.0341 0.0040 1.0000
14.500 1.4954 0.03944 0.03550 -0.0332 0.0038 1.0000
14.750 1.5004 0.04132 0.03748 -0.0323 0.0037 1.0000
15.000 1.5051 0.04329 0.03953 -0.0316 0.0035 1.0000
15.250 1.5074 0.04559 0.04194 -0.0310 0.0034 1.0000
15.500 1.5062 0.04839 0.04487 -0.0305 0.0033 1.0000
15.750 1.5023 0.05162 0.04824 -0.0302 0.0032 1.0000
16.000 1.4944 0.05549 0.05226 -0.0303 0.0031 1.0000
16.250 1.4878 0.05941 0.05634 -0.0308 0.0031 1.0000
16.500 1.4776 0.06404 0.06114 -0.0317 0.0031 1.0000
16.750 1.4657 0.06922 0.06648 -0.0332 0.0030 1.0000
17.000 1.4515 0.07514 0.07257 -0.0354 0.0030 1.0000
17.250 1.4333 0.08218 0.07979 -0.0385 0.0030 1.0000
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Polar data table (+)
Polar graphs
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