NACA 65(4)-421 a=0.5 (naca654421a05-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(4)-421 a=0.5 (naca654421a05-il) Reynolds number: 200,000 Max Cl/Cd: 31.7 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca654421a05-il-200000.txt Download as CSV file: xf-naca654421a05-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7089 0.06241 0.05697 -0.1039 0.8433 0.0550
-14.000 -0.7134 0.05887 0.05328 -0.1033 0.8378 0.0548
-13.750 -0.7234 0.05585 0.05006 -0.1019 0.8328 0.0546
-13.500 -0.7365 0.05324 0.04721 -0.0999 0.8282 0.0546
-13.250 -0.7483 0.05095 0.04471 -0.0978 0.8223 0.0547
-13.000 -0.7602 0.04896 0.04246 -0.0949 0.8171 0.0548
-12.750 -0.7697 0.04719 0.04042 -0.0915 0.8128 0.0549
-12.500 -0.7723 0.04544 0.03844 -0.0888 0.8085 0.0549
-12.250 -0.7682 0.04363 0.03641 -0.0868 0.8035 0.0549
-12.000 -0.7506 0.04075 0.03335 -0.0867 0.7995 0.0554
-11.750 -0.7241 0.03843 0.03092 -0.0876 0.7962 0.0561
-11.500 -0.7002 0.03696 0.02937 -0.0877 0.7932 0.0570
-11.250 -0.6779 0.03552 0.02780 -0.0877 0.7895 0.0575
-11.000 -0.6532 0.03413 0.02629 -0.0880 0.7856 0.0580
-10.750 -0.6285 0.03294 0.02497 -0.0882 0.7820 0.0588
-10.500 -0.6044 0.03186 0.02376 -0.0881 0.7789 0.0598
-10.250 -0.5771 0.03080 0.02254 -0.0883 0.7762 0.0605
-10.000 -0.5482 0.02987 0.02146 -0.0885 0.7738 0.0611
-9.750 -0.5193 0.02909 0.02058 -0.0890 0.7706 0.0619
-9.500 -0.4868 0.02828 0.01973 -0.0898 0.7669 0.0627
-9.250 -0.4522 0.02744 0.01900 -0.0907 0.7638 0.0641
-9.000 -0.4289 0.02682 0.01841 -0.0904 0.7608 0.0657
-8.750 -0.4079 0.02623 0.01780 -0.0898 0.7583 0.0674
-8.500 -0.3886 0.02568 0.01719 -0.0889 0.7560 0.0691
-8.250 -0.3702 0.02521 0.01664 -0.0879 0.7536 0.0708
-8.000 -0.3560 0.02446 0.01601 -0.0869 0.7502 0.0727
-7.750 -0.3435 0.02385 0.01544 -0.0856 0.7468 0.0751
-7.500 -0.3313 0.02327 0.01484 -0.0840 0.7436 0.0779
-7.250 -0.3216 0.02266 0.01419 -0.0818 0.7408 0.0811
-7.000 -0.3173 0.02204 0.01358 -0.0788 0.7383 0.0853
-6.750 -0.3117 0.02166 0.01314 -0.0756 0.7362 0.0919
-6.500 -0.3093 0.02131 0.01291 -0.0723 0.7332 0.1043
-6.250 -0.3128 0.02063 0.01261 -0.0684 0.7295 0.1496
-6.000 -0.3260 0.01943 0.01211 -0.0630 0.7260 0.2684
-5.750 -0.3373 0.01825 0.01183 -0.0573 0.7231 0.4291
-5.500 -0.3219 0.01822 0.01205 -0.0550 0.7209 0.5194
-5.250 -0.2989 0.01836 0.01215 -0.0539 0.7191 0.5527
-5.000 -0.2737 0.01861 0.01235 -0.0531 0.7175 0.5751
-4.750 -0.2546 0.01925 0.01299 -0.0520 0.7142 0.5912
-4.500 -0.2375 0.01995 0.01367 -0.0508 0.7102 0.6047
-4.250 -0.2146 0.02052 0.01428 -0.0500 0.7074 0.6171
-4.000 -0.1902 0.02103 0.01479 -0.0491 0.7052 0.6320
-3.750 -0.1643 0.02142 0.01514 -0.0484 0.7034 0.6470
-3.500 -0.1357 0.02189 0.01561 -0.0478 0.7018 0.6598
-3.250 -0.1058 0.02244 0.01618 -0.0472 0.7004 0.6716
-3.000 -0.0799 0.02282 0.01649 -0.0465 0.6992 0.6842
-2.750 -0.0884 0.02483 0.01870 -0.0423 0.6916 0.6890
-2.500 -0.0745 0.02548 0.01934 -0.0407 0.6879 0.6943
-2.250 -0.0508 0.02545 0.01922 -0.0404 0.6858 0.7002
-2.000 -0.0231 0.02529 0.01898 -0.0406 0.6844 0.7045
-1.750 0.0068 0.02526 0.01890 -0.0409 0.6833 0.7076
-1.500 -0.0754 0.02954 0.02336 -0.0279 0.6688 0.7128
-1.250 -0.0507 0.02961 0.02336 -0.0279 0.6670 0.7171
-1.000 -0.0220 0.02957 0.02321 -0.0285 0.6658 0.7218
-0.750 0.0103 0.02947 0.02308 -0.0293 0.6649 0.7248
-0.500 -0.0605 0.03335 0.02706 -0.0181 0.6529 0.7293
-0.250 -0.0411 0.03381 0.02749 -0.0175 0.6506 0.7331
0.000 -0.0153 0.03402 0.02764 -0.0177 0.6489 0.7377
0.250 0.0154 0.03403 0.02756 -0.0185 0.6477 0.7424
0.500 0.0497 0.03385 0.02737 -0.0193 0.6467 0.7454
0.750 0.0847 0.03369 0.02720 -0.0203 0.6459 0.7486
1.000 0.1210 0.03350 0.02699 -0.0214 0.6452 0.7525
1.250 0.1579 0.03332 0.02677 -0.0227 0.6447 0.7572
1.500 0.0854 0.03761 0.03110 -0.0129 0.6304 0.7639
1.750 0.1164 0.03767 0.03118 -0.0134 0.6293 0.7677
2.000 0.0972 0.03987 0.03342 -0.0092 0.6213 0.7730
2.250 0.1089 0.04072 0.03425 -0.0081 0.6170 0.7787
2.500 0.1354 0.04094 0.03445 -0.0083 0.6147 0.7838
2.750 0.1663 0.04095 0.03450 -0.0087 0.6130 0.7883
3.000 0.1997 0.04089 0.03445 -0.0093 0.6118 0.7940
3.250 0.2369 0.04069 0.03423 -0.0105 0.6109 0.8003
3.500 0.2719 0.04059 0.03415 -0.0113 0.6101 0.8054
3.750 0.2304 0.04357 0.03721 -0.0053 0.5966 0.8131
4.000 0.2630 0.04354 0.03717 -0.0059 0.5952 0.8202
4.250 0.2961 0.04342 0.03710 -0.0064 0.5941 0.8261
4.500 0.3317 0.04320 0.03692 -0.0071 0.5933 0.8331
4.750 0.3013 0.04580 0.03957 -0.0024 0.5800 0.8432
5.000 0.3320 0.04566 0.03949 -0.0025 0.5784 0.8515
5.250 0.3666 0.04535 0.03921 -0.0030 0.5773 0.8608
5.500 0.4002 0.04506 0.03898 -0.0033 0.5764 0.8697
5.750 0.3755 0.04743 0.04144 0.0009 0.5631 0.8831
6.000 0.4073 0.04712 0.04118 0.0008 0.5616 0.8956
6.250 0.4032 0.04876 0.04292 0.0030 0.5518 0.9118
6.500 0.4317 0.04885 0.04309 0.0025 0.5482 0.9286
6.750 0.4753 0.04860 0.04293 -0.0002 0.5463 0.9456
7.000 0.5284 0.04826 0.04268 -0.0045 0.5451 0.9610
7.250 0.5835 0.04788 0.04238 -0.0093 0.5441 0.9785
7.500 0.6289 0.04725 0.04179 -0.0120 0.5434 1.0000
7.750 0.6176 0.04956 0.04409 -0.0103 0.5298 1.0000
8.000 0.6560 0.04878 0.04333 -0.0115 0.5287 1.0000
8.250 0.6965 0.04775 0.04233 -0.0126 0.5278 1.0000
8.500 0.7377 0.04656 0.04117 -0.0137 0.5271 1.0000
8.750 0.7286 0.04880 0.04343 -0.0117 0.5135 1.0000
9.000 0.7702 0.04738 0.04207 -0.0126 0.5127 1.0000
9.250 0.8107 0.04599 0.04072 -0.0134 0.5119 1.0000
9.500 0.8529 0.04436 0.03917 -0.0142 0.5113 1.0000
9.750 0.8988 0.04203 0.03690 -0.0150 0.5104 1.0000
10.000 0.9650 0.03727 0.03221 -0.0165 0.5100 1.0000
10.250 0.9704 0.03797 0.03294 -0.0148 0.4975 1.0000
10.500 0.9812 0.03834 0.03335 -0.0135 0.4855 1.0000
10.750 1.0495 0.03393 0.02898 -0.0155 0.4802 1.0000
11.000 1.0561 0.03496 0.03003 -0.0141 0.4651 1.0000
11.250 1.0786 0.03474 0.02982 -0.0136 0.4482 1.0000
11.500 1.0888 0.03560 0.03066 -0.0125 0.4270 1.0000
11.750 1.1136 0.03513 0.03001 -0.0119 0.3960 1.0000
12.000 1.1215 0.03600 0.03061 -0.0103 0.3569 1.0000
12.250 1.1173 0.03800 0.03234 -0.0082 0.3208 1.0000
12.500 1.1083 0.04060 0.03471 -0.0062 0.2876 1.0000
12.750 1.0967 0.04358 0.03748 -0.0043 0.2543 1.0000
13.000 1.0858 0.04668 0.04038 -0.0027 0.2224 1.0000
13.250 1.0728 0.05011 0.04357 -0.0012 0.1883 1.0000
13.500 1.0597 0.05371 0.04693 0.0000 0.1522 1.0000
13.750 1.0417 0.05792 0.05079 0.0013 0.1094 1.0000
14.000 1.0279 0.06186 0.05445 0.0022 0.0815 1.0000
14.250 1.0227 0.06509 0.05756 0.0028 0.0678 1.0000
14.500 1.0205 0.06812 0.06055 0.0032 0.0607 1.0000
14.750 1.0215 0.07085 0.06327 0.0034 0.0569 1.0000
15.000 1.0236 0.07350 0.06594 0.0035 0.0530 1.0000
15.250 1.0266 0.07607 0.06851 0.0036 0.0503 1.0000
15.500 1.0298 0.07857 0.07098 0.0036 0.0486 1.0000
15.750 1.0369 0.08070 0.07318 0.0036 0.0466 1.0000
16.000 1.0448 0.08269 0.07519 0.0036 0.0452 1.0000
16.250 1.0532 0.08455 0.07702 0.0037 0.0438 1.0000
16.500 1.0648 0.08591 0.07835 0.0039 0.0424 1.0000
16.750 1.0773 0.08734 0.07985 0.0040 0.0414 1.0000
17.000 1.0890 0.08889 0.08144 0.0039 0.0402 1.0000
17.250 1.1022 0.09017 0.08273 0.0039 0.0391 1.0000
17.500 1.1215 0.09051 0.08295 0.0043 0.0379 1.0000
17.750 1.1414 0.09092 0.08337 0.0047 0.0372 1.0000
18.000 1.1549 0.09232 0.08490 0.0047 0.0367 1.0000
18.250 1.1678 0.09381 0.08650 0.0046 0.0360 1.0000
18.500 1.1807 0.09533 0.08813 0.0046 0.0355 1.0000
18.750 1.1937 0.09684 0.08975 0.0045 0.0350 1.0000
19.000 1.2062 0.09846 0.09145 0.0043 0.0346 1.0000
19.250 1.2173 0.10025 0.09336 0.0040 0.0343 1.0000
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Polar data table (+)
Polar graphs
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