NACA 64(3)-618 (naca643618-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(3)-618 (naca643618-il) Reynolds number: 500,000 Max Cl/Cd: 109.89 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca643618-il-500000.txt Download as CSV file: xf-naca643618-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-618
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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7238 0.08136 0.07810 -0.0841 1.0000 0.0255
-16.500 -0.7582 0.07250 0.06902 -0.0895 1.0000 0.0255
-16.250 -0.7775 0.06665 0.06301 -0.0927 1.0000 0.0256
-16.000 -0.7938 0.06163 0.05784 -0.0951 1.0000 0.0258
-15.750 -0.8059 0.05747 0.05354 -0.0969 1.0000 0.0259
-15.500 -0.8152 0.05398 0.04993 -0.0980 1.0000 0.0262
-15.250 -0.8252 0.05059 0.04640 -0.0988 1.0000 0.0264
-15.000 -0.8338 0.04755 0.04322 -0.0992 1.0000 0.0267
-14.750 -0.8403 0.04490 0.04044 -0.0991 1.0000 0.0269
-14.500 -0.8474 0.04245 0.03785 -0.0986 1.0000 0.0272
-14.250 -0.8537 0.04038 0.03564 -0.0976 1.0000 0.0274
-14.000 -0.8633 0.03873 0.03389 -0.0955 1.0000 0.0277
-13.750 -0.8566 0.03662 0.03160 -0.0969 0.9975 0.0279
-13.500 -0.8342 0.03430 0.02921 -0.0990 0.9918 0.0286
-13.250 -0.8087 0.03291 0.02782 -0.1015 0.9853 0.0292
-13.000 -0.7844 0.03148 0.02633 -0.1041 0.9777 0.0299
-12.750 -0.7572 0.02996 0.02471 -0.1068 0.9711 0.0305
-12.500 -0.7276 0.02851 0.02314 -0.1101 0.9642 0.0313
-12.250 -0.6950 0.02708 0.02153 -0.1138 0.9567 0.0321
-12.000 -0.6615 0.02562 0.01996 -0.1164 0.9487 0.0329
-11.750 -0.6258 0.02453 0.01887 -0.1195 0.9395 0.0339
-11.500 -0.5964 0.02363 0.01790 -0.1216 0.9258 0.0347
-11.250 -0.5733 0.02284 0.01700 -0.1222 0.9112 0.0356
-11.000 -0.5545 0.02215 0.01618 -0.1219 0.8975 0.0364
-10.500 -0.5219 0.02079 0.01459 -0.1198 0.8732 0.0376
-10.250 -0.5072 0.01997 0.01375 -0.1185 0.8631 0.0387
-10.000 -0.4933 0.01936 0.01309 -0.1172 0.8526 0.0395
-9.750 -0.4796 0.01879 0.01247 -0.1157 0.8431 0.0404
-9.500 -0.4667 0.01826 0.01186 -0.1140 0.8338 0.0414
-9.250 -0.4546 0.01780 0.01132 -0.1121 0.8253 0.0422
-9.000 -0.4382 0.01736 0.01077 -0.1109 0.8170 0.0429
-8.750 -0.4260 0.01653 0.00992 -0.1094 0.8093 0.0442
-8.500 -0.4082 0.01604 0.00941 -0.1084 0.8014 0.0456
-8.250 -0.3879 0.01565 0.00894 -0.1076 0.7946 0.0472
-8.000 -0.3667 0.01527 0.00851 -0.1070 0.7874 0.0487
-7.750 -0.3477 0.01468 0.00788 -0.1061 0.7805 0.0505
-7.500 -0.3259 0.01425 0.00742 -0.1056 0.7743 0.0527
-7.250 -0.3026 0.01390 0.00703 -0.1053 0.7676 0.0551
-7.000 -0.2797 0.01345 0.00654 -0.1049 0.7612 0.0583
-6.750 -0.2552 0.01311 0.00617 -0.1048 0.7553 0.0624
-6.500 -0.2309 0.01270 0.00576 -0.1046 0.7487 0.0678
-6.250 -0.2055 0.01236 0.00539 -0.1046 0.7427 0.0753
-6.000 -0.1803 0.01194 0.00502 -0.1046 0.7367 0.0888
-5.750 -0.1549 0.01147 0.00466 -0.1047 0.7302 0.1138
-5.500 -0.1293 0.01093 0.00428 -0.1050 0.7243 0.1589
-5.250 -0.1037 0.01021 0.00386 -0.1055 0.7185 0.2342
-5.000 -0.0778 0.00920 0.00337 -0.1065 0.7124 0.3613
-4.750 -0.0493 0.00887 0.00329 -0.1070 0.7069 0.4494
-4.500 -0.0200 0.00886 0.00325 -0.1074 0.7015 0.4764
-4.250 0.0091 0.00885 0.00323 -0.1077 0.6957 0.4938
-4.000 0.0382 0.00887 0.00321 -0.1080 0.6903 0.5073
-3.750 0.0674 0.00891 0.00320 -0.1083 0.6852 0.5180
-3.500 0.0967 0.00895 0.00319 -0.1086 0.6797 0.5281
-3.250 0.1257 0.00898 0.00320 -0.1088 0.6745 0.5374
-3.000 0.1552 0.00910 0.00321 -0.1091 0.6696 0.5469
-2.750 0.1840 0.00910 0.00325 -0.1093 0.6647 0.5545
-2.500 0.2132 0.00922 0.00332 -0.1096 0.6595 0.5651
-2.250 0.2417 0.00931 0.00342 -0.1096 0.6547 0.5755
-2.000 0.2709 0.00941 0.00346 -0.1099 0.6500 0.5817
-1.750 0.3003 0.00942 0.00343 -0.1103 0.6452 0.5849
-1.500 0.3291 0.00937 0.00338 -0.1105 0.6406 0.5882
-1.250 0.3581 0.00941 0.00338 -0.1108 0.6364 0.5916
-1.000 0.3872 0.00947 0.00341 -0.1111 0.6324 0.5955
-0.750 0.4163 0.00948 0.00342 -0.1115 0.6282 0.5989
-0.500 0.4456 0.00951 0.00341 -0.1119 0.6241 0.6020
-0.250 0.4748 0.00954 0.00340 -0.1122 0.6203 0.6053
0.000 0.5039 0.00961 0.00344 -0.1126 0.6167 0.6085
0.250 0.5327 0.00962 0.00349 -0.1129 0.6131 0.6117
0.500 0.5617 0.00965 0.00353 -0.1132 0.6095 0.6153
0.750 0.5908 0.00970 0.00356 -0.1136 0.6059 0.6190
1.000 0.6201 0.00978 0.00359 -0.1140 0.6024 0.6225
1.250 0.6492 0.00986 0.00368 -0.1143 0.5991 0.6263
1.500 0.6777 0.00990 0.00378 -0.1146 0.5961 0.6304
1.750 0.7066 0.00996 0.00387 -0.1149 0.5930 0.6349
2.000 0.7357 0.01004 0.00394 -0.1153 0.5900 0.6393
2.250 0.7645 0.01009 0.00402 -0.1156 0.5871 0.6436
2.500 0.7935 0.01020 0.00413 -0.1160 0.5841 0.6480
2.750 0.8222 0.01031 0.00427 -0.1162 0.5807 0.6529
3.000 0.8504 0.01036 0.00436 -0.1165 0.5772 0.6580
3.250 0.8786 0.01041 0.00447 -0.1167 0.5737 0.6629
3.500 0.9070 0.01049 0.00459 -0.1169 0.5708 0.6680
3.750 0.9359 0.01061 0.00472 -0.1172 0.5679 0.6737
4.000 0.9653 0.01080 0.00489 -0.1177 0.5649 0.6793
4.250 0.9924 0.01084 0.00506 -0.1177 0.5620 0.6848
4.500 1.0196 0.01090 0.00518 -0.1177 0.5577 0.6912
4.750 1.0469 0.01095 0.00523 -0.1177 0.5522 0.6976
5.000 1.0739 0.01105 0.00537 -0.1177 0.5467 0.7036
5.250 1.0991 0.01106 0.00547 -0.1172 0.5401 0.7102
5.500 1.1254 0.01113 0.00553 -0.1171 0.5334 0.7168
5.750 1.1513 0.01122 0.00571 -0.1168 0.5282 0.7231
6.000 1.1767 0.01127 0.00584 -0.1165 0.5219 0.7303
6.250 1.2013 0.01139 0.00594 -0.1160 0.5136 0.7370
6.500 1.2242 0.01141 0.00609 -0.1151 0.5039 0.7440
6.750 1.2483 0.01157 0.00624 -0.1146 0.4960 0.7518
7.000 1.2716 0.01165 0.00643 -0.1139 0.4874 0.7586
7.250 1.2941 0.01182 0.00663 -0.1130 0.4785 0.7666
7.500 1.3154 0.01197 0.00684 -0.1120 0.4671 0.7743
7.750 1.3354 0.01216 0.00709 -0.1107 0.4535 0.7827
8.000 1.3519 0.01242 0.00736 -0.1088 0.4345 0.7912
8.250 1.3600 0.01281 0.00770 -0.1053 0.4040 0.8004
8.500 1.3544 0.01367 0.00836 -0.0997 0.3625 0.8103
8.750 1.3472 0.01483 0.00933 -0.0943 0.3237 0.8215
9.000 1.3388 0.01617 0.01052 -0.0891 0.2863 0.8327
9.250 1.3311 0.01766 0.01187 -0.0845 0.2509 0.8453
9.500 1.3236 0.01929 0.01339 -0.0803 0.2192 0.8595
9.750 1.3174 0.02095 0.01497 -0.0765 0.1932 0.8762
10.000 1.3124 0.02252 0.01651 -0.0729 0.1707 0.8986
10.250 1.3057 0.02407 0.01806 -0.0691 0.1511 0.9444
10.500 1.3056 0.02601 0.01991 -0.0673 0.1304 1.0000
10.750 1.3076 0.02797 0.02179 -0.0658 0.1133 1.0000
11.000 1.3094 0.03000 0.02375 -0.0644 0.0988 1.0000
11.250 1.3117 0.03205 0.02574 -0.0631 0.0863 1.0000
11.500 1.3138 0.03418 0.02781 -0.0619 0.0750 1.0000
11.750 1.3165 0.03633 0.02993 -0.0609 0.0655 1.0000
12.000 1.3199 0.03848 0.03206 -0.0600 0.0580 1.0000
12.250 1.3238 0.04067 0.03424 -0.0592 0.0520 1.0000
12.500 1.3275 0.04292 0.03649 -0.0585 0.0474 1.0000
12.750 1.3320 0.04515 0.03873 -0.0580 0.0436 1.0000
13.000 1.3368 0.04742 0.04104 -0.0575 0.0407 1.0000
13.250 1.3415 0.04973 0.04337 -0.0571 0.0380 1.0000
13.500 1.3449 0.05224 0.04591 -0.0567 0.0360 1.0000
13.750 1.3511 0.05452 0.04825 -0.0565 0.0341 1.0000
14.000 1.3540 0.05719 0.05093 -0.0564 0.0324 1.0000
14.250 1.3570 0.05991 0.05371 -0.0563 0.0309 1.0000
14.500 1.3628 0.06234 0.05620 -0.0562 0.0295 1.0000
14.750 1.3664 0.06508 0.05898 -0.0563 0.0283 1.0000
15.000 1.3638 0.06862 0.06255 -0.0564 0.0272 1.0000
15.250 1.3707 0.07106 0.06509 -0.0566 0.0263 1.0000
15.500 1.3751 0.07383 0.06793 -0.0569 0.0254 1.0000
15.750 1.3788 0.07673 0.07088 -0.0573 0.0246 1.0000
16.000 1.3798 0.08002 0.07420 -0.0577 0.0239 1.0000
16.250 1.3788 0.08358 0.07781 -0.0582 0.0232 1.0000
16.500 1.3841 0.08643 0.08075 -0.0588 0.0226 1.0000
16.750 1.3882 0.08941 0.08382 -0.0594 0.0219 1.0000
17.000 1.3916 0.09253 0.08700 -0.0601 0.0214 1.0000
17.250 1.3944 0.09576 0.09029 -0.0609 0.0209 1.0000
17.500 1.3966 0.09909 0.09367 -0.0618 0.0205 1.0000
17.750 1.3971 0.10262 0.09722 -0.0627 0.0201 1.0000
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