NACA 65(4)-421 a=0.5 (naca654421a05-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(4)-421 a=0.5 (naca654421a05-il) Reynolds number: 500,000 Max Cl/Cd: 96.51 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca654421a05-il-500000.txt Download as CSV file: xf-naca654421a05-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6881 0.08792 0.08440 -0.0847 0.8489 0.0296
-17.500 -0.7354 0.07759 0.07378 -0.0905 0.8451 0.0295
-17.250 -0.7678 0.07041 0.06635 -0.0938 0.8400 0.0295
-17.000 -0.7814 0.06616 0.06192 -0.0955 0.8341 0.0297
-16.750 -0.7983 0.06178 0.05732 -0.0967 0.8289 0.0298
-16.500 -0.8120 0.05788 0.05325 -0.0977 0.8235 0.0300
-16.250 -0.8214 0.05479 0.04999 -0.0981 0.8178 0.0303
-16.000 -0.8308 0.05177 0.04675 -0.0981 0.8124 0.0305
-15.750 -0.8383 0.04907 0.04388 -0.0980 0.8072 0.0308
-15.500 -0.8445 0.04665 0.04127 -0.0975 0.8016 0.0311
-15.250 -0.8487 0.04438 0.03879 -0.0968 0.7963 0.0314
-15.000 -0.8549 0.04255 0.03675 -0.0957 0.7912 0.0317
-14.750 -0.8614 0.04082 0.03483 -0.0944 0.7860 0.0319
-14.500 -0.8664 0.03945 0.03328 -0.0928 0.7809 0.0321
-14.250 -0.8360 0.03714 0.03093 -0.0937 0.7771 0.0329
-14.000 -0.8226 0.03600 0.02970 -0.0932 0.7726 0.0333
-13.750 -0.8086 0.03481 0.02846 -0.0927 0.7685 0.0336
-13.500 -0.7933 0.03382 0.02742 -0.0922 0.7641 0.0340
-13.250 -0.7782 0.03276 0.02627 -0.0916 0.7599 0.0344
-13.000 -0.7646 0.03183 0.02522 -0.0909 0.7557 0.0349
-12.750 -0.7509 0.03089 0.02418 -0.0901 0.7517 0.0355
-12.500 -0.7357 0.02995 0.02315 -0.0894 0.7476 0.0359
-12.250 -0.7184 0.02905 0.02215 -0.0888 0.7437 0.0362
-12.000 -0.7015 0.02825 0.02122 -0.0881 0.7401 0.0365
-11.750 -0.6848 0.02752 0.02036 -0.0874 0.7364 0.0368
-11.500 -0.6544 0.02655 0.01939 -0.0878 0.7334 0.0374
-11.250 -0.6297 0.02580 0.01865 -0.0878 0.7302 0.0379
-11.000 -0.6091 0.02510 0.01795 -0.0873 0.7269 0.0383
-10.750 -0.5899 0.02443 0.01725 -0.0868 0.7237 0.0388
-10.500 -0.5719 0.02380 0.01658 -0.0861 0.7206 0.0393
-10.250 -0.5542 0.02320 0.01591 -0.0853 0.7173 0.0399
-10.000 -0.5364 0.02255 0.01524 -0.0845 0.7146 0.0403
-9.750 -0.5194 0.02189 0.01456 -0.0837 0.7115 0.0407
-9.500 -0.5029 0.02124 0.01387 -0.0827 0.7084 0.0411
-9.250 -0.4867 0.02063 0.01322 -0.0818 0.7056 0.0416
-9.000 -0.4708 0.02004 0.01257 -0.0807 0.7029 0.0420
-8.750 -0.4550 0.01950 0.01195 -0.0796 0.7002 0.0423
-8.500 -0.4453 0.01866 0.01110 -0.0777 0.6976 0.0429
-8.250 -0.4344 0.01792 0.01036 -0.0760 0.6953 0.0437
-8.000 -0.4217 0.01730 0.00974 -0.0743 0.6928 0.0444
-7.750 -0.4082 0.01677 0.00919 -0.0727 0.6902 0.0453
-7.500 -0.3946 0.01630 0.00868 -0.0709 0.6877 0.0462
-7.250 -0.3815 0.01593 0.00827 -0.0688 0.6853 0.0472
-7.000 -0.3675 0.01567 0.00793 -0.0668 0.6829 0.0482
-6.750 -0.3551 0.01529 0.00752 -0.0646 0.6803 0.0500
-6.500 -0.3371 0.01493 0.00718 -0.0633 0.6786 0.0522
-6.250 -0.3169 0.01465 0.00688 -0.0623 0.6766 0.0548
-6.000 -0.2982 0.01427 0.00654 -0.0612 0.6744 0.0597
-5.750 -0.2795 0.01385 0.00620 -0.0600 0.6723 0.0730
-5.500 -0.2691 0.01298 0.00569 -0.0577 0.6703 0.1431
-5.250 -0.2584 0.01202 0.00518 -0.0555 0.6683 0.2395
-5.000 -0.2493 0.01089 0.00461 -0.0531 0.6663 0.3670
-4.750 -0.2336 0.01024 0.00440 -0.0514 0.6643 0.4798
-4.500 -0.2081 0.01021 0.00443 -0.0512 0.6621 0.5169
-4.250 -0.1811 0.01017 0.00443 -0.0512 0.6606 0.5384
-4.000 -0.1534 0.01017 0.00444 -0.0514 0.6589 0.5540
-3.750 -0.1253 0.01022 0.00445 -0.0515 0.6570 0.5677
-3.500 -0.0973 0.01024 0.00450 -0.0517 0.6552 0.5792
-3.250 -0.0691 0.01029 0.00453 -0.0519 0.6534 0.5906
-3.000 -0.0407 0.01037 0.00459 -0.0521 0.6517 0.6015
-2.750 -0.0123 0.01042 0.00464 -0.0523 0.6500 0.6115
-2.500 0.0160 0.01057 0.00475 -0.0524 0.6482 0.6230
-2.250 0.0446 0.01066 0.00484 -0.0526 0.6465 0.6319
-2.000 0.0735 0.01083 0.00499 -0.0530 0.6446 0.6383
-1.750 0.1022 0.01085 0.00499 -0.0534 0.6433 0.6420
-1.500 0.1309 0.01086 0.00498 -0.0538 0.6418 0.6449
-1.250 0.1597 0.01082 0.00497 -0.0543 0.6401 0.6481
-1.000 0.1886 0.01084 0.00499 -0.0547 0.6385 0.6510
-0.750 0.2176 0.01085 0.00501 -0.0552 0.6367 0.6540
-0.500 0.2467 0.01087 0.00501 -0.0557 0.6349 0.6573
-0.250 0.2759 0.01090 0.00500 -0.0562 0.6332 0.6608
0.000 0.3052 0.01094 0.00499 -0.0567 0.6317 0.6638
0.250 0.3346 0.01093 0.00499 -0.0573 0.6303 0.6672
0.500 0.3639 0.01100 0.00506 -0.0578 0.6289 0.6704
0.750 0.3930 0.01117 0.00523 -0.0583 0.6271 0.6737
1.000 0.4210 0.01121 0.00530 -0.0587 0.6258 0.6774
1.250 0.4489 0.01127 0.00538 -0.0590 0.6241 0.6813
1.500 0.4769 0.01131 0.00545 -0.0594 0.6223 0.6850
1.750 0.5050 0.01135 0.00555 -0.0597 0.6206 0.6887
2.000 0.5333 0.01142 0.00565 -0.0601 0.6190 0.6925
2.250 0.5619 0.01149 0.00574 -0.0605 0.6173 0.6966
2.500 0.5908 0.01154 0.00579 -0.0611 0.6156 0.7008
2.750 0.6200 0.01157 0.00583 -0.0616 0.6141 0.7048
3.000 0.6492 0.01163 0.00592 -0.0621 0.6126 0.7090
3.250 0.6785 0.01176 0.00607 -0.0627 0.6111 0.7137
3.500 0.7067 0.01197 0.00630 -0.0631 0.6093 0.7187
3.750 0.7328 0.01206 0.00645 -0.0632 0.6076 0.7235
4.000 0.7588 0.01213 0.00663 -0.0632 0.6057 0.7282
4.250 0.7852 0.01223 0.00680 -0.0633 0.6036 0.7333
4.500 0.8125 0.01231 0.00692 -0.0635 0.6015 0.7387
4.750 0.8406 0.01236 0.00700 -0.0639 0.5994 0.7439
5.000 0.8692 0.01236 0.00706 -0.0643 0.5974 0.7492
5.250 0.8990 0.01238 0.00710 -0.0649 0.5954 0.7550
5.500 0.9298 0.01252 0.00722 -0.0657 0.5929 0.7611
5.750 0.9517 0.01253 0.00738 -0.0650 0.5897 0.7672
6.000 0.9754 0.01251 0.00746 -0.0645 0.5859 0.7738
6.250 1.0028 0.01243 0.00740 -0.0646 0.5821 0.7807
6.500 1.0333 0.01220 0.00717 -0.0652 0.5776 0.7867
6.750 1.0542 0.01215 0.00721 -0.0641 0.5718 0.7938
7.000 1.0764 0.01201 0.00712 -0.0633 0.5653 0.8014
7.250 1.1041 0.01185 0.00695 -0.0633 0.5592 0.8081
7.500 1.1157 0.01185 0.00709 -0.0606 0.5517 0.8171
7.750 1.1350 0.01176 0.00700 -0.0592 0.5436 0.8254
8.000 1.1435 0.01187 0.00725 -0.0559 0.5363 0.8354
8.250 1.1508 0.01193 0.00735 -0.0523 0.5282 0.8457
8.500 1.1539 0.01224 0.00775 -0.0483 0.5192 0.8580
8.750 1.1571 0.01257 0.00813 -0.0444 0.5085 0.8707
9.000 1.1593 0.01304 0.00867 -0.0406 0.4967 0.8857
9.250 1.1597 0.01363 0.00934 -0.0366 0.4829 0.9045
9.500 1.1571 0.01443 0.01017 -0.0325 0.4651 0.9316
9.750 1.1706 0.01605 0.01174 -0.0334 0.4308 0.9705
10.000 1.1605 0.01816 0.01368 -0.0304 0.3969 1.0000
10.250 1.1416 0.02061 0.01595 -0.0261 0.3654 1.0000
10.500 1.1263 0.02304 0.01822 -0.0225 0.3364 1.0000
10.750 1.1104 0.02572 0.02074 -0.0191 0.3064 1.0000
11.000 1.0971 0.02840 0.02327 -0.0162 0.2779 1.0000
11.250 1.0859 0.03106 0.02578 -0.0136 0.2504 1.0000
11.500 1.0779 0.03358 0.02816 -0.0115 0.2222 1.0000
11.750 1.0700 0.03621 0.03062 -0.0095 0.1934 1.0000
12.000 1.0640 0.03876 0.03301 -0.0078 0.1662 1.0000
12.250 1.0589 0.04130 0.03537 -0.0063 0.1380 1.0000
12.500 1.0528 0.04399 0.03786 -0.0048 0.1076 1.0000
12.750 1.0453 0.04685 0.04050 -0.0034 0.0763 1.0000
13.000 1.0409 0.04954 0.04301 -0.0022 0.0527 1.0000
13.250 1.0420 0.05184 0.04522 -0.0014 0.0420 1.0000
13.500 1.0464 0.05391 0.04726 -0.0008 0.0376 1.0000
13.750 1.0525 0.05586 0.04922 -0.0003 0.0340 1.0000
14.000 1.0574 0.05798 0.05136 0.0001 0.0322 1.0000
14.250 1.0650 0.05987 0.05330 0.0004 0.0308 1.0000
14.500 1.0708 0.06194 0.05539 0.0007 0.0293 1.0000
14.750 1.0733 0.06441 0.05788 0.0009 0.0283 1.0000
15.000 1.0810 0.06637 0.05990 0.0011 0.0273 1.0000
15.250 1.0876 0.06848 0.06206 0.0011 0.0265 1.0000
15.500 1.0930 0.07075 0.06438 0.0012 0.0260 1.0000
15.750 1.0977 0.07310 0.06676 0.0012 0.0253 1.0000
16.000 1.1011 0.07563 0.06932 0.0011 0.0249 1.0000
16.250 1.1007 0.07859 0.07231 0.0011 0.0243 1.0000
16.500 1.1082 0.08073 0.07452 0.0009 0.0239 1.0000
16.750 1.1135 0.08315 0.07700 0.0007 0.0237 1.0000
17.000 1.1197 0.08547 0.07938 0.0004 0.0233 1.0000
17.250 1.1256 0.08785 0.08181 0.0000 0.0228 1.0000
17.500 1.1305 0.09034 0.08435 -0.0003 0.0224 1.0000
17.750 1.1367 0.09267 0.08673 -0.0008 0.0221 1.0000
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