NACA 64(4)-421 (naca644421-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(4)-421 (naca644421-il) Reynolds number: 100,000 Max Cl/Cd: 21.9 at α=12.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca644421-il-100000.txt Download as CSV file: xf-naca644421-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(4)-421
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5980 0.09506 0.08930 -0.0768 1.0000 0.0941
-15.000 -0.6382 0.08590 0.08003 -0.0810 1.0000 0.0930
-14.750 -0.6825 0.07776 0.07172 -0.0844 1.0000 0.0917
-14.500 -0.7246 0.07109 0.06484 -0.0865 1.0000 0.0909
-14.250 -0.7597 0.06583 0.05936 -0.0873 1.0000 0.0903
-14.000 -0.7878 0.06168 0.05502 -0.0870 1.0000 0.0900
-13.750 -0.8110 0.05834 0.05151 -0.0858 1.0000 0.0901
-13.500 -0.8317 0.05582 0.04885 -0.0836 1.0000 0.0901
-13.250 -0.8574 0.05439 0.04735 -0.0794 1.0000 0.0902
-13.000 -0.8950 0.05423 0.04717 -0.0725 1.0000 0.0899
-12.750 -0.9301 0.05388 0.04679 -0.0661 1.0000 0.0897
-12.500 -0.9485 0.05269 0.04545 -0.0626 0.9980 0.0901
-12.250 -0.9334 0.04996 0.04238 -0.0653 0.9892 0.0919
-12.000 -0.9188 0.04753 0.03951 -0.0676 0.9803 0.0938
-11.750 -0.8837 0.04489 0.03674 -0.0704 0.9738 0.0964
-11.500 -0.8349 0.04275 0.03457 -0.0747 0.9698 0.1000
-11.250 -0.8010 0.04095 0.03255 -0.0774 0.9628 0.1039
-11.000 -0.7474 0.03901 0.03065 -0.0813 0.9592 0.1095
-10.750 -0.7003 0.03742 0.02895 -0.0852 0.9551 0.1160
-10.500 -0.6424 0.03593 0.02763 -0.0895 0.9532 0.1252
-10.250 -0.6019 0.03480 0.02655 -0.0916 0.9463 0.1350
-10.000 -0.5593 0.03364 0.02552 -0.0943 0.9411 0.1489
-9.750 -0.5174 0.03232 0.02443 -0.0975 0.9369 0.1693
-9.500 -0.4999 0.03128 0.02355 -0.0972 0.9257 0.1911
-9.250 -0.4829 0.02962 0.02225 -0.0980 0.9178 0.2258
-9.000 -0.4897 0.02810 0.02110 -0.0955 0.9044 0.2621
-8.750 -0.5081 0.02691 0.02030 -0.0909 0.8901 0.3012
-8.500 -0.5217 0.02643 0.02034 -0.0856 0.8784 0.3611
-8.250 -0.5188 0.02711 0.02126 -0.0815 0.8675 0.4211
-8.000 -0.5275 0.02726 0.02128 -0.0768 0.8564 0.4523
-7.750 -0.4952 0.02894 0.02290 -0.0756 0.8493 0.4787
-7.500 -0.4393 0.03144 0.02530 -0.0763 0.8454 0.4981
-7.250 -0.4271 0.03255 0.02632 -0.0732 0.8359 0.5124
-7.000 -0.3003 0.03867 0.03230 -0.0777 0.8354 0.5151
-6.750 -0.2094 0.04226 0.03569 -0.0805 0.8316 0.5205
-6.500 -0.1814 0.04288 0.03617 -0.0793 0.8256 0.5328
-6.250 -0.2168 0.04197 0.03528 -0.0730 0.8147 0.5488
-6.000 -0.1039 0.04528 0.03838 -0.0785 0.8124 0.5532
-5.750 -0.1169 0.04448 0.03752 -0.0744 0.8053 0.5686
-5.500 -0.0356 0.04595 0.03880 -0.0779 0.8028 0.5742
-5.250 -0.0672 0.04542 0.03833 -0.0723 0.7922 0.5885
-5.000 0.0056 0.04627 0.03904 -0.0758 0.7885 0.5945
-4.750 -0.0165 0.04532 0.03803 -0.0708 0.7829 0.6084
-4.500 0.0459 0.04605 0.03868 -0.0738 0.7773 0.6141
-4.250 0.0466 0.04587 0.03849 -0.0711 0.7702 0.6237
-4.000 0.0680 0.04545 0.03799 -0.0703 0.7658 0.6318
-3.750 0.1057 0.04523 0.03766 -0.0713 0.7627 0.6393
-3.500 0.0112 0.04556 0.03816 -0.0578 0.7515 0.6485
-3.250 0.1026 0.04541 0.03789 -0.0653 0.7496 0.6533
-3.000 0.1294 0.04514 0.03755 -0.0654 0.7461 0.6596
-2.750 0.0869 0.04464 0.03703 -0.0572 0.7420 0.6666
-2.500 0.0179 0.04612 0.03868 -0.0457 0.7302 0.6710
-2.250 0.0661 0.04606 0.03855 -0.0480 0.7275 0.6750
-2.000 0.0828 0.04576 0.03821 -0.0470 0.7247 0.6800
-1.750 -0.1586 0.04816 0.04087 -0.0162 0.7106 0.6862
-1.500 -0.1565 0.04767 0.04032 -0.0148 0.7073 0.6912
-1.250 -0.1350 0.04793 0.04054 -0.0139 0.7052 0.6943
-1.000 -0.1098 0.04794 0.04050 -0.0142 0.7035 0.6977
-0.750 -0.0767 0.04768 0.04017 -0.0158 0.7021 0.7021
-0.500 -0.1319 0.04870 0.04119 -0.0102 0.6982 0.7075
-0.250 -0.1318 0.04918 0.04162 -0.0095 0.6972 0.7114
0.000 -0.1316 0.04994 0.04240 -0.0070 0.6954 0.7142
0.250 -0.1253 0.05063 0.04308 -0.0059 0.6946 0.7173
0.500 -0.1161 0.05131 0.04374 -0.0055 0.6944 0.7211
0.750 -0.1030 0.05185 0.04425 -0.0061 0.6933 0.7251
1.000 -0.0869 0.05254 0.04487 -0.0078 0.6943 0.7289
1.250 -0.0731 0.05340 0.04572 -0.0083 0.6962 0.7322
1.500 -0.0613 0.05437 0.04672 -0.0076 0.6976 0.7350
1.750 -0.0369 0.05553 0.04787 -0.0087 0.7001 0.7379
2.000 -0.0011 0.05682 0.04914 -0.0112 0.7017 0.7412
2.250 0.0454 0.05575 0.04800 -0.0129 0.6820 0.7452
2.500 -0.0548 0.05944 0.05183 -0.0069 0.7318 0.7487
2.750 -0.0238 0.06034 0.05272 -0.0086 0.7261 0.7526
3.000 0.0188 0.06228 0.05467 -0.0111 0.7226 0.7561
3.250 0.0045 0.06188 0.05430 -0.0078 0.7136 0.7593
3.500 0.0334 0.06278 0.05519 -0.0092 0.7067 0.7635
3.750 0.0801 0.06473 0.05712 -0.0131 0.7030 0.7685
4.000 0.0698 0.06468 0.05709 -0.0107 0.6933 0.7722
4.250 0.0963 0.06563 0.05807 -0.0111 0.6866 0.7762
4.500 0.1428 0.06779 0.06027 -0.0139 0.6828 0.7818
4.750 0.1267 0.06762 0.06012 -0.0112 0.6715 0.7869
5.000 0.1631 0.06893 0.06145 -0.0131 0.6655 0.7927
5.250 0.2057 0.07138 0.06395 -0.0151 0.6623 0.7982
5.500 0.1890 0.07078 0.06339 -0.0121 0.6485 0.8034
5.750 0.3047 0.06737 0.05993 -0.0155 0.6053 0.8119
6.000 0.2882 0.06990 0.06256 -0.0139 0.6064 0.8173
6.250 0.2911 0.07212 0.06484 -0.0139 0.6067 0.8242
6.500 0.3163 0.07032 0.06305 -0.0121 0.5753 0.8315
6.750 0.3879 0.06881 0.06158 -0.0134 0.5678 0.8415
7.000 0.3648 0.07091 0.06376 -0.0114 0.5548 0.8490
7.250 0.4213 0.06975 0.06266 -0.0118 0.5496 0.8601
7.500 0.4040 0.07180 0.06478 -0.0098 0.5362 0.8688
7.750 0.4542 0.07083 0.06387 -0.0103 0.5316 0.8818
8.000 0.4396 0.07274 0.06587 -0.0081 0.5183 0.8923
8.250 0.4837 0.07157 0.06478 -0.0077 0.5137 0.9079
8.500 0.4746 0.07347 0.06677 -0.0062 0.5005 0.9231
8.750 0.5221 0.07208 0.06551 -0.0065 0.4959 0.9462
9.000 0.5332 0.07402 0.06758 -0.0085 0.4817 0.9727
9.250 0.5949 0.07233 0.06596 -0.0114 0.4776 1.0000
9.500 0.6031 0.07440 0.06809 -0.0130 0.4629 1.0000
9.750 0.6674 0.07205 0.06580 -0.0153 0.4596 1.0000
10.000 0.6759 0.07390 0.06770 -0.0165 0.4448 1.0000
10.250 0.7267 0.07195 0.06581 -0.0177 0.4394 1.0000
10.500 0.7487 0.07227 0.06619 -0.0185 0.4274 1.0000
10.750 0.7657 0.07308 0.06706 -0.0190 0.4149 1.0000
11.000 0.8215 0.06959 0.06365 -0.0192 0.4110 1.0000
11.250 0.8841 0.06491 0.05908 -0.0192 0.4090 1.0000
12.000 0.9889 0.05835 0.05277 -0.0179 0.3802 1.0000
12.250 1.0333 0.05501 0.04950 -0.0173 0.3673 1.0000
12.500 1.0807 0.05152 0.04596 -0.0167 0.3471 1.0000
12.750 1.1071 0.05056 0.04482 -0.0158 0.3173 1.0000
13.000 1.1181 0.05137 0.04535 -0.0148 0.2844 1.0000
13.250 1.1208 0.05320 0.04686 -0.0139 0.2539 1.0000
13.500 1.1200 0.05558 0.04893 -0.0131 0.2271 1.0000
13.750 1.1190 0.05821 0.05136 -0.0126 0.2039 1.0000
14.000 1.1194 0.06081 0.05376 -0.0122 0.1839 1.0000
14.250 1.1219 0.06325 0.05602 -0.0118 0.1666 1.0000
14.500 1.1269 0.06551 0.05811 -0.0116 0.1517 1.0000
14.750 1.1337 0.06767 0.06015 -0.0113 0.1386 1.0000
15.000 1.1426 0.06967 0.06206 -0.0111 0.1276 1.0000
15.250 1.1552 0.07130 0.06359 -0.0108 0.1182 1.0000
15.500 1.1745 0.07224 0.06428 -0.0104 0.1095 1.0000
15.750 1.1783 0.07504 0.06728 -0.0106 0.1035 1.0000
16.000 1.2000 0.07590 0.06797 -0.0103 0.0972 1.0000
16.250 1.2045 0.07865 0.07090 -0.0105 0.0927 1.0000
16.500 1.2312 0.07916 0.07119 -0.0102 0.0875 1.0000
16.750 1.2316 0.08243 0.07474 -0.0106 0.0844 1.0000
17.000 1.2423 0.08457 0.07693 -0.0108 0.0811 1.0000
17.250 1.2628 0.08600 0.07830 -0.0107 0.0779 1.0000
17.500 1.2583 0.08992 0.08252 -0.0114 0.0759 1.0000
17.750 1.2605 0.09314 0.08590 -0.0121 0.0738 1.0000
18.000 1.2747 0.09500 0.08775 -0.0124 0.0715 1.0000
18.250 1.2800 0.09818 0.09102 -0.0130 0.0698 1.0000
18.500 1.2612 0.10384 0.09703 -0.0147 0.0691 1.0000
18.750 1.2413 0.10992 0.10343 -0.0169 0.0684 1.0000
19.000 1.2183 0.11672 0.11053 -0.0198 0.0680 1.0000
19.250 1.1903 0.12460 0.11872 -0.0235 0.0678 1.0000
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