NACA 65(4)-421 a=0.5 (naca654421a05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(4)-421 a=0.5 (naca654421a05-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.64 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca654421a05-il-1000000-n5.txt Download as CSV file: xf-naca654421a05-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0026 0.07077 0.06626 -0.0834 0.7999 0.0184
-19.500 -0.9996 0.06795 0.06335 -0.0847 0.7936 0.0187
-19.250 -0.9988 0.06496 0.06026 -0.0859 0.7885 0.0187
-19.000 -0.9968 0.06217 0.05738 -0.0871 0.7828 0.0188
-18.750 -0.9950 0.05944 0.05455 -0.0880 0.7775 0.0190
-18.500 -0.9878 0.05735 0.05239 -0.0888 0.7723 0.0193
-18.250 -0.9852 0.05483 0.04978 -0.0896 0.7680 0.0193
-18.000 -0.9809 0.05255 0.04741 -0.0902 0.7632 0.0195
-17.750 -0.9727 0.05071 0.04549 -0.0907 0.7581 0.0197
-17.500 -0.9665 0.04873 0.04342 -0.0911 0.7536 0.0199
-17.250 -0.9604 0.04678 0.04140 -0.0914 0.7495 0.0200
-17.000 -0.9531 0.04499 0.03953 -0.0916 0.7448 0.0201
-16.750 -0.9443 0.04339 0.03784 -0.0917 0.7399 0.0202
-16.500 -0.9370 0.04170 0.03606 -0.0918 0.7350 0.0203
-16.250 -0.9275 0.04021 0.03451 -0.0918 0.7313 0.0204
-16.000 -0.9235 0.03833 0.03257 -0.0916 0.7268 0.0207
-15.750 -0.9158 0.03681 0.03098 -0.0914 0.7226 0.0208
-15.500 -0.9064 0.03545 0.02958 -0.0912 0.7184 0.0210
-15.250 -0.8984 0.03400 0.02807 -0.0908 0.7151 0.0211
-15.000 -0.8864 0.03289 0.02693 -0.0906 0.7116 0.0214
-14.750 -0.8755 0.03172 0.02571 -0.0902 0.7078 0.0216
-14.500 -0.8642 0.03063 0.02456 -0.0897 0.7039 0.0217
-14.250 -0.8530 0.02956 0.02343 -0.0892 0.7002 0.0219
-14.000 -0.8414 0.02854 0.02235 -0.0886 0.6970 0.0221
-13.750 -0.8298 0.02752 0.02129 -0.0880 0.6937 0.0223
-13.500 -0.8176 0.02656 0.02029 -0.0874 0.6901 0.0224
-13.250 -0.8038 0.02573 0.01941 -0.0868 0.6862 0.0227
-13.000 -0.7902 0.02492 0.01854 -0.0861 0.6825 0.0229
-12.750 -0.7753 0.02419 0.01775 -0.0855 0.6794 0.0233
-12.500 -0.7626 0.02332 0.01685 -0.0847 0.6769 0.0234
-12.250 -0.7481 0.02259 0.01607 -0.0840 0.6740 0.0236
-12.000 -0.7336 0.02187 0.01530 -0.0832 0.6709 0.0237
-11.750 -0.7186 0.02120 0.01458 -0.0824 0.6679 0.0239
-11.500 -0.7069 0.02038 0.01371 -0.0812 0.6649 0.0240
-11.250 -0.6953 0.01958 0.01287 -0.0800 0.6621 0.0243
-11.000 -0.6815 0.01889 0.01215 -0.0789 0.6599 0.0244
-10.750 -0.6673 0.01824 0.01147 -0.0778 0.6573 0.0247
-10.500 -0.6525 0.01765 0.01085 -0.0767 0.6546 0.0249
-10.250 -0.6372 0.01710 0.01027 -0.0755 0.6517 0.0251
-10.000 -0.6216 0.01659 0.00973 -0.0744 0.6489 0.0253
-9.750 -0.6058 0.01612 0.00922 -0.0732 0.6463 0.0256
-9.500 -0.5896 0.01567 0.00874 -0.0720 0.6441 0.0259
-9.250 -0.5732 0.01523 0.00828 -0.0708 0.6423 0.0261
-9.000 -0.5566 0.01483 0.00786 -0.0695 0.6403 0.0264
-8.750 -0.5402 0.01444 0.00744 -0.0681 0.6382 0.0267
-8.500 -0.5237 0.01409 0.00707 -0.0666 0.6361 0.0270
-8.250 -0.5079 0.01378 0.00673 -0.0650 0.6339 0.0273
-8.000 -0.4920 0.01356 0.00647 -0.0632 0.6317 0.0275
-7.750 -0.4745 0.01335 0.00622 -0.0617 0.6294 0.0278
-7.500 -0.4551 0.01308 0.00592 -0.0606 0.6271 0.0284
-7.250 -0.4340 0.01281 0.00566 -0.0597 0.6256 0.0289
-7.000 -0.4117 0.01258 0.00542 -0.0590 0.6239 0.0296
-6.750 -0.3887 0.01236 0.00520 -0.0585 0.6222 0.0302
-6.500 -0.3649 0.01217 0.00499 -0.0580 0.6205 0.0311
-6.250 -0.3406 0.01199 0.00480 -0.0577 0.6187 0.0319
-6.000 -0.3165 0.01178 0.00459 -0.0573 0.6169 0.0330
-5.750 -0.2921 0.01159 0.00439 -0.0570 0.6152 0.0345
-5.500 -0.2670 0.01143 0.00422 -0.0568 0.6134 0.0360
-5.250 -0.2418 0.01127 0.00405 -0.0566 0.6114 0.0380
-5.000 -0.2165 0.01110 0.00388 -0.0564 0.6095 0.0415
-4.500 -0.1673 0.01059 0.00351 -0.0559 0.6069 0.0696
-4.250 -0.1434 0.01027 0.00331 -0.0555 0.6054 0.0971
-4.000 -0.1201 0.00990 0.00311 -0.0551 0.6039 0.1359
-3.750 -0.0962 0.00955 0.00292 -0.0548 0.6024 0.1776
-3.500 -0.0737 0.00908 0.00269 -0.0543 0.6009 0.2389
-3.250 -0.0525 0.00850 0.00243 -0.0536 0.5993 0.3230
-3.000 -0.0322 0.00782 0.00215 -0.0529 0.5978 0.4278
-2.750 -0.0071 0.00753 0.00207 -0.0527 0.5962 0.4914
-2.500 0.0209 0.00746 0.00205 -0.0529 0.5943 0.5142
-2.250 0.0492 0.00742 0.00204 -0.0532 0.5925 0.5326
-2.000 0.0778 0.00737 0.00204 -0.0536 0.5914 0.5522
-1.750 0.1068 0.00734 0.00206 -0.0540 0.5903 0.5658
-1.500 0.1360 0.00732 0.00206 -0.0544 0.5891 0.5736
-1.250 0.1654 0.00732 0.00206 -0.0549 0.5878 0.5781
-1.000 0.1949 0.00732 0.00205 -0.0555 0.5864 0.5809
-0.750 0.2244 0.00733 0.00205 -0.0560 0.5849 0.5834
-0.500 0.2539 0.00735 0.00205 -0.0565 0.5834 0.5857
-0.250 0.2832 0.00737 0.00205 -0.0570 0.5817 0.5883
0.000 0.3122 0.00738 0.00206 -0.0574 0.5801 0.5914
0.250 0.3412 0.00740 0.00208 -0.0579 0.5786 0.5943
0.500 0.3702 0.00743 0.00210 -0.0583 0.5770 0.5972
0.750 0.3993 0.00747 0.00214 -0.0588 0.5756 0.6000
1.000 0.4287 0.00748 0.00216 -0.0594 0.5746 0.6027
1.250 0.4582 0.00751 0.00220 -0.0599 0.5733 0.6053
1.500 0.4873 0.00752 0.00223 -0.0604 0.5719 0.6085
1.750 0.5163 0.00753 0.00227 -0.0609 0.5704 0.6119
2.000 0.5453 0.00755 0.00232 -0.0613 0.5690 0.6153
2.250 0.5742 0.00758 0.00237 -0.0618 0.5675 0.6186
2.500 0.6031 0.00762 0.00242 -0.0622 0.5659 0.6217
2.750 0.6318 0.00767 0.00247 -0.0627 0.5642 0.6245
3.000 0.6601 0.00771 0.00253 -0.0630 0.5625 0.6278
3.250 0.6883 0.00776 0.00259 -0.0634 0.5609 0.6315
3.500 0.7165 0.00782 0.00267 -0.0637 0.5591 0.6353
3.750 0.7451 0.00786 0.00275 -0.0642 0.5578 0.6393
4.000 0.7736 0.00790 0.00283 -0.0646 0.5562 0.6431
4.250 0.8018 0.00793 0.00291 -0.0650 0.5543 0.6470
4.500 0.8297 0.00796 0.00299 -0.0653 0.5518 0.6514
4.750 0.8571 0.00801 0.00307 -0.0655 0.5487 0.6558
5.000 0.8834 0.00809 0.00315 -0.0655 0.5446 0.6600
5.500 0.9368 0.00820 0.00334 -0.0657 0.5353 0.6684
5.750 0.9606 0.00830 0.00344 -0.0653 0.5281 0.6733
6.000 0.9849 0.00839 0.00356 -0.0649 0.5186 0.6783
6.250 1.0058 0.00855 0.00370 -0.0640 0.5064 0.6829
6.500 1.0234 0.00875 0.00389 -0.0624 0.4920 0.6887
6.750 1.0306 0.00907 0.00416 -0.0589 0.4698 0.6950
7.000 1.0269 0.00964 0.00464 -0.0536 0.4472 0.7012
7.250 1.0187 0.01055 0.00544 -0.0480 0.4170 0.7076
7.500 1.0004 0.01197 0.00670 -0.0414 0.3781 0.7150
7.750 0.9824 0.01367 0.00823 -0.0353 0.3400 0.7218
8.000 0.9789 0.01493 0.00944 -0.0316 0.3180 0.7289
8.250 0.9698 0.01655 0.01095 -0.0274 0.2888 0.7369
8.500 0.9614 0.01825 0.01255 -0.0235 0.2612 0.7442
9.000 0.9483 0.02172 0.01583 -0.0168 0.2084 0.7618
9.250 0.9425 0.02354 0.01756 -0.0138 0.1826 0.7714
9.500 0.9369 0.02546 0.01938 -0.0111 0.1561 0.7821
9.750 0.9399 0.02691 0.02080 -0.0091 0.1393 0.7932
10.000 0.9435 0.02838 0.02223 -0.0074 0.1223 0.8037
10.250 0.9435 0.03011 0.02390 -0.0054 0.1026 0.8161
10.500 0.9491 0.03150 0.02527 -0.0039 0.0889 0.8284
10.750 0.9520 0.03311 0.02685 -0.0023 0.0731 0.8425
11.000 0.9558 0.03464 0.02836 -0.0008 0.0587 0.8601
11.250 0.9593 0.03614 0.02989 0.0009 0.0456 0.8846
11.500 0.9678 0.03761 0.03144 0.0016 0.0360 0.9238
11.750 1.0026 0.03950 0.03337 -0.0037 0.0280 0.9557
12.250 1.0381 0.04243 0.03632 -0.0057 0.0227 1.0000
12.500 1.0496 0.04375 0.03764 -0.0053 0.0213 1.0000
12.750 1.0618 0.04501 0.03891 -0.0049 0.0200 1.0000
13.000 1.0733 0.04635 0.04027 -0.0045 0.0189 1.0000
13.250 1.0839 0.04780 0.04172 -0.0041 0.0181 1.0000
13.500 1.0954 0.04916 0.04310 -0.0038 0.0176 1.0000
13.750 1.1073 0.05051 0.04447 -0.0035 0.0166 1.0000
14.000 1.1179 0.05200 0.04598 -0.0032 0.0161 1.0000
14.250 1.1281 0.05353 0.04753 -0.0029 0.0157 1.0000
14.500 1.1379 0.05509 0.04911 -0.0026 0.0150 1.0000
14.750 1.1483 0.05663 0.05067 -0.0024 0.0148 1.0000
15.000 1.1582 0.05825 0.05233 -0.0022 0.0143 1.0000
15.250 1.1679 0.05988 0.05399 -0.0020 0.0140 1.0000
15.500 1.1784 0.06146 0.05560 -0.0019 0.0139 1.0000
15.750 1.1869 0.06325 0.05742 -0.0018 0.0134 1.0000
16.000 1.1953 0.06504 0.05925 -0.0017 0.0133 1.0000
16.250 1.2040 0.06684 0.06107 -0.0016 0.0130 1.0000
16.500 1.2112 0.06882 0.06309 -0.0016 0.0127 1.0000
16.750 1.2184 0.07083 0.06514 -0.0016 0.0126 1.0000
17.000 1.2249 0.07292 0.06726 -0.0016 0.0124 1.0000
17.250 1.2314 0.07505 0.06944 -0.0017 0.0121 1.0000
17.500 1.2374 0.07724 0.07168 -0.0019 0.0120 1.0000
17.750 1.2447 0.07930 0.07378 -0.0021 0.0120 1.0000
18.000 1.2508 0.08154 0.07607 -0.0023 0.0117 1.0000
18.250 1.2559 0.08392 0.07851 -0.0026 0.0116 1.0000
18.500 1.2617 0.08623 0.08088 -0.0030 0.0114 1.0000
18.750 1.2652 0.08887 0.08357 -0.0034 0.0113 1.0000
19.000 1.2710 0.09122 0.08596 -0.0038 0.0111 1.0000
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Polar data table (+)
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