NACA 65(4)-421 a=0.5 (naca654421a05-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(4)-421 a=0.5 (naca654421a05-il) Reynolds number: 100,000 Max Cl/Cd: 16.51 at α=12.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca654421a05-il-100000-n5.txt Download as CSV file: xf-naca654421a05-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(4)-421 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4035 0.11365 0.10801 -0.0794 0.8626 0.0474
-15.500 -0.5005 0.09000 0.08408 -0.0937 0.8635 0.0462
-15.250 -0.5491 0.07994 0.07374 -0.0994 0.8592 0.0458
-15.000 -0.5817 0.07342 0.06694 -0.1023 0.8540 0.0456
-14.750 -0.6080 0.06831 0.06155 -0.1037 0.8491 0.0457
-14.500 -0.6265 0.06414 0.05713 -0.1047 0.8433 0.0457
-14.250 -0.6416 0.06055 0.05328 -0.1049 0.8374 0.0459
-14.000 -0.6535 0.05747 0.04993 -0.1046 0.8322 0.0462
-13.750 -0.6624 0.05472 0.04691 -0.1040 0.8272 0.0466
-13.500 -0.6689 0.05220 0.04412 -0.1034 0.8215 0.0471
-13.250 -0.6723 0.04995 0.04158 -0.1024 0.8165 0.0476
-13.000 -0.6745 0.04793 0.03924 -0.1010 0.8122 0.0481
-12.750 -0.6646 0.04614 0.03727 -0.1004 0.8075 0.0486
-12.500 -0.6478 0.04463 0.03568 -0.1002 0.8025 0.0491
-12.250 -0.6314 0.04326 0.03419 -0.0997 0.7980 0.0497
-12.000 -0.6148 0.04196 0.03276 -0.0991 0.7942 0.0503
-11.750 -0.5964 0.04073 0.03140 -0.0986 0.7904 0.0511
-11.500 -0.5758 0.03959 0.03015 -0.0986 0.7859 0.0519
-11.250 -0.5561 0.03854 0.02896 -0.0982 0.7818 0.0531
-11.000 -0.5359 0.03756 0.02781 -0.0978 0.7783 0.0543
-10.750 -0.5134 0.03666 0.02682 -0.0974 0.7753 0.0554
-10.500 -0.4912 0.03586 0.02601 -0.0970 0.7724 0.0565
-10.250 -0.4691 0.03511 0.02528 -0.0969 0.7682 0.0577
-10.000 -0.4486 0.03440 0.02454 -0.0964 0.7642 0.0589
-9.750 -0.4296 0.03369 0.02376 -0.0957 0.7606 0.0603
-9.500 -0.4117 0.03299 0.02297 -0.0948 0.7576 0.0618
-9.250 -0.3967 0.03223 0.02217 -0.0937 0.7549 0.0634
-9.000 -0.3822 0.03153 0.02149 -0.0929 0.7515 0.0656
-8.750 -0.3677 0.03089 0.02083 -0.0921 0.7478 0.0682
-8.500 -0.3535 0.03026 0.02014 -0.0911 0.7444 0.0710
-8.250 -0.3428 0.02947 0.01937 -0.0897 0.7413 0.0740
-8.000 -0.3310 0.02877 0.01860 -0.0881 0.7385 0.0777
-7.750 -0.3208 0.02800 0.01780 -0.0864 0.7361 0.0827
-7.500 -0.3109 0.02740 0.01722 -0.0848 0.7324 0.0902
-7.250 -0.3044 0.02677 0.01670 -0.0827 0.7284 0.1020
-7.000 -0.3016 0.02613 0.01619 -0.0799 0.7250 0.1207
-6.750 -0.3033 0.02548 0.01571 -0.0762 0.7221 0.1523
-6.500 -0.3052 0.02473 0.01517 -0.0723 0.7197 0.1976
-6.250 -0.3079 0.02383 0.01457 -0.0683 0.7176 0.2586
-6.000 -0.3133 0.02325 0.01443 -0.0640 0.7136 0.3324
-5.750 -0.3130 0.02305 0.01485 -0.0599 0.7093 0.4275
-5.500 -0.2986 0.02322 0.01519 -0.0575 0.7061 0.4920
-5.250 -0.2809 0.02335 0.01529 -0.0558 0.7036 0.5255
-5.000 -0.2618 0.02359 0.01548 -0.0541 0.7016 0.5561
-4.750 -0.2434 0.02395 0.01576 -0.0521 0.7000 0.5879
-4.500 -0.2158 0.02472 0.01654 -0.0509 0.6986 0.6121
-4.250 -0.2088 0.02557 0.01741 -0.0480 0.6934 0.6267
-4.000 -0.1881 0.02637 0.01821 -0.0464 0.6898 0.6391
-3.750 -0.1662 0.02680 0.01858 -0.0452 0.6871 0.6494
-3.500 -0.1425 0.02703 0.01872 -0.0443 0.6850 0.6576
-3.250 -0.1226 0.02688 0.01843 -0.0435 0.6832 0.6649
-3.000 -0.0943 0.02699 0.01846 -0.0434 0.6818 0.6687
-2.750 -0.0673 0.02699 0.01836 -0.0433 0.6807 0.6732
-2.500 -0.0824 0.02813 0.01954 -0.0383 0.6726 0.6797
-2.250 -0.0675 0.02826 0.01959 -0.0369 0.6692 0.6845
-2.000 -0.0441 0.02839 0.01967 -0.0364 0.6671 0.6876
-1.750 -0.0197 0.02845 0.01966 -0.0360 0.6655 0.6914
-1.500 0.0054 0.02841 0.01953 -0.0359 0.6641 0.6957
-1.250 -0.0216 0.03005 0.02119 -0.0297 0.6552 0.7020
-1.000 -0.0106 0.03056 0.02168 -0.0277 0.6511 0.7055
-0.750 0.0115 0.03074 0.02182 -0.0271 0.6491 0.7091
-0.500 0.0355 0.03083 0.02186 -0.0268 0.6476 0.7130
-0.250 0.0619 0.03082 0.02178 -0.0270 0.6463 0.7173
0.000 0.0227 0.03330 0.02430 -0.0197 0.6350 0.7235
0.250 0.0426 0.03369 0.02468 -0.0190 0.6325 0.7271
0.500 0.0662 0.03392 0.02488 -0.0187 0.6308 0.7313
0.750 0.0925 0.03402 0.02494 -0.0188 0.6294 0.7358
1.000 0.1208 0.03402 0.02487 -0.0192 0.6283 0.7407
1.250 0.1475 0.03411 0.02493 -0.0193 0.6269 0.7447
1.750 0.1391 0.03713 0.02804 -0.0133 0.6135 0.7556
2.000 0.1667 0.03721 0.02807 -0.0136 0.6120 0.7614
2.250 0.1950 0.03727 0.02813 -0.0138 0.6108 0.7656
2.500 0.2239 0.03731 0.02818 -0.0140 0.6098 0.7702
2.750 0.1960 0.04001 0.03095 -0.0092 0.5983 0.7774
3.000 0.2214 0.04024 0.03117 -0.0093 0.5962 0.7835
3.250 0.2472 0.04043 0.03139 -0.0092 0.5946 0.7888
3.500 0.2750 0.04054 0.03152 -0.0093 0.5934 0.7953
4.000 0.2800 0.04316 0.03423 -0.0054 0.5805 0.8097
4.250 0.3062 0.04334 0.03443 -0.0055 0.5785 0.8171
4.500 0.3348 0.04340 0.03452 -0.0057 0.5770 0.8242
4.750 0.3643 0.04339 0.03455 -0.0059 0.5759 0.8318
5.000 0.3461 0.04580 0.03704 -0.0025 0.5643 0.8425
5.250 0.3714 0.04595 0.03726 -0.0023 0.5621 0.8514
5.500 0.3997 0.04598 0.03733 -0.0025 0.5605 0.8615
5.750 0.4295 0.04589 0.03731 -0.0027 0.5592 0.8714
6.000 0.4152 0.04824 0.03976 0.0001 0.5474 0.8851
6.250 0.4436 0.04829 0.03989 -0.0002 0.5452 0.8984
6.500 0.4762 0.04821 0.03989 -0.0010 0.5437 0.9134
7.000 0.5157 0.05062 0.04253 -0.0035 0.5300 0.9513
7.250 0.5589 0.05055 0.04256 -0.0067 0.5280 0.9761
7.750 0.5844 0.05257 0.04462 -0.0063 0.5141 1.0000
8.000 0.6151 0.05234 0.04442 -0.0068 0.5120 1.0000
8.500 0.6411 0.05420 0.04637 -0.0059 0.4976 1.0000
8.750 0.6730 0.05376 0.04597 -0.0064 0.4956 1.0000
9.000 0.6706 0.05581 0.04807 -0.0051 0.4834 1.0000
9.250 0.7017 0.05529 0.04762 -0.0054 0.4808 1.0000
9.750 0.7332 0.05654 0.04899 -0.0045 0.4658 1.0000
10.000 0.7669 0.05558 0.04812 -0.0047 0.4636 1.0000
10.500 0.7779 0.05866 0.05134 -0.0032 0.4411 1.0000
11.000 0.8184 0.05898 0.05183 -0.0025 0.4270 1.0000
11.250 0.8386 0.05909 0.05204 -0.0022 0.4191 1.0000
11.750 0.8853 0.05842 0.05153 -0.0014 0.4003 1.0000
12.000 0.9054 0.05826 0.05139 -0.0009 0.3834 1.0000
12.250 0.9178 0.05901 0.05211 -0.0002 0.3587 1.0000
12.500 0.9437 0.05815 0.05108 0.0005 0.3275 1.0000
12.750 0.9622 0.05828 0.05100 0.0012 0.2961 1.0000
13.250 0.9770 0.06133 0.05369 0.0025 0.2396 1.0000
13.500 0.9790 0.06360 0.05582 0.0030 0.2134 1.0000
13.750 0.9779 0.06628 0.05832 0.0035 0.1863 1.0000
14.000 0.9770 0.06907 0.06098 0.0038 0.1612 1.0000
14.250 0.9753 0.07204 0.06380 0.0040 0.1369 1.0000
14.500 0.9725 0.07521 0.06682 0.0041 0.1137 1.0000
14.750 0.9710 0.07831 0.06980 0.0040 0.0942 1.0000
15.000 0.9695 0.08150 0.07288 0.0039 0.0790 1.0000
15.250 0.9698 0.08452 0.07586 0.0037 0.0686 1.0000
15.500 0.9706 0.08755 0.07886 0.0034 0.0620 1.0000
15.750 0.9722 0.09052 0.08184 0.0031 0.0567 1.0000
16.000 0.9750 0.09339 0.08475 0.0026 0.0530 1.0000
16.250 0.9775 0.09632 0.08771 0.0021 0.0501 1.0000
16.500 0.9805 0.09919 0.09062 0.0015 0.0475 1.0000
16.750 0.9852 0.10183 0.09334 0.0010 0.0455 1.0000
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Polar data table (+)
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