NACA 63(4)-421 (naca634421-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(4)-421 (naca634421-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.06 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca634421-il-1000000.txt Download as CSV file: xf-naca634421-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(4)-421
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0779 0.08309 0.07897 -0.0563 1.0000 0.0260
-19.500 -1.0835 0.07923 0.07507 -0.0578 1.0000 0.0267
-19.250 -1.0828 0.07621 0.07201 -0.0590 1.0000 0.0273
-19.000 -1.0825 0.07315 0.06890 -0.0601 1.0000 0.0277
-18.750 -1.0768 0.07080 0.06650 -0.0609 1.0000 0.0286
-18.500 -1.0728 0.06825 0.06389 -0.0618 1.0000 0.0291
-18.250 -1.0658 0.06608 0.06166 -0.0625 1.0000 0.0296
-18.000 -1.0692 0.06275 0.05829 -0.0636 1.0000 0.0303
-17.750 -1.0668 0.06012 0.05564 -0.0644 1.0000 0.0309
-17.500 -1.0618 0.05780 0.05329 -0.0651 1.0000 0.0317
-17.250 -1.0549 0.05574 0.05118 -0.0656 1.0000 0.0323
-17.000 -1.0485 0.05360 0.04900 -0.0662 1.0000 0.0328
-16.750 -1.0383 0.05191 0.04725 -0.0666 1.0000 0.0335
-16.500 -1.0333 0.04973 0.04503 -0.0670 1.0000 0.0339
-16.250 -1.0319 0.04721 0.04249 -0.0675 1.0000 0.0347
-16.000 -1.0264 0.04514 0.04040 -0.0679 1.0000 0.0354
-15.750 -1.0187 0.04333 0.03856 -0.0681 1.0000 0.0360
-15.500 -1.0099 0.04163 0.03683 -0.0684 1.0000 0.0367
-15.250 -1.0006 0.04001 0.03518 -0.0685 1.0000 0.0373
-15.000 -0.9909 0.03846 0.03359 -0.0686 1.0000 0.0378
-14.750 -0.9620 0.03625 0.03132 -0.0732 0.9594 0.0387
-14.500 -0.9132 0.03387 0.02890 -0.0823 0.9449 0.0403
-14.250 -0.8646 0.03205 0.02695 -0.0902 0.9181 0.0417
-14.000 -0.8474 0.03095 0.02567 -0.0910 0.8831 0.0424
-13.750 -0.8378 0.02989 0.02446 -0.0903 0.8615 0.0429
-13.500 -0.8342 0.02843 0.02292 -0.0893 0.8452 0.0438
-13.250 -0.8284 0.02713 0.02154 -0.0884 0.8317 0.0446
-13.000 -0.8209 0.02598 0.02032 -0.0874 0.8201 0.0457
-12.750 -0.8108 0.02494 0.01923 -0.0867 0.8106 0.0468
-12.500 -0.8005 0.02399 0.01819 -0.0858 0.8011 0.0476
-12.250 -0.7884 0.02308 0.01723 -0.0850 0.7934 0.0484
-12.000 -0.7828 0.02186 0.01597 -0.0838 0.7849 0.0501
-11.750 -0.7737 0.02087 0.01494 -0.0827 0.7774 0.0517
-11.500 -0.7621 0.02001 0.01404 -0.0817 0.7700 0.0531
-11.250 -0.7512 0.01918 0.01314 -0.0806 0.7623 0.0547
-11.000 -0.7431 0.01819 0.01215 -0.0792 0.7557 0.0573
-10.750 -0.7317 0.01740 0.01133 -0.0780 0.7489 0.0600
-10.500 -0.7228 0.01656 0.01045 -0.0764 0.7421 0.0634
-10.250 -0.7122 0.01580 0.00969 -0.0750 0.7363 0.0674
-10.000 -0.7049 0.01496 0.00886 -0.0730 0.7302 0.0730
-9.750 -0.6996 0.01422 0.00811 -0.0706 0.7239 0.0789
-9.500 -0.6951 0.01368 0.00753 -0.0678 0.7179 0.0853
-9.250 -0.6806 0.01314 0.00703 -0.0664 0.7128 0.0945
-9.000 -0.6637 0.01265 0.00657 -0.0653 0.7070 0.1058
-8.750 -0.6450 0.01220 0.00615 -0.0644 0.7011 0.1190
-8.500 -0.6241 0.01175 0.00577 -0.0638 0.6961 0.1336
-8.250 -0.6018 0.01133 0.00541 -0.0634 0.6907 0.1489
-8.000 -0.5788 0.01095 0.00506 -0.0630 0.6848 0.1653
-7.750 -0.5554 0.01056 0.00472 -0.0628 0.6789 0.1849
-7.500 -0.5316 0.01006 0.00436 -0.0627 0.6742 0.2122
-7.250 -0.5073 0.00957 0.00400 -0.0626 0.6690 0.2447
-7.000 -0.4820 0.00917 0.00369 -0.0627 0.6638 0.2758
-6.750 -0.4557 0.00881 0.00343 -0.0628 0.6589 0.3059
-6.500 -0.4284 0.00844 0.00319 -0.0631 0.6549 0.3358
-6.250 -0.4003 0.00820 0.00302 -0.0635 0.6503 0.3616
-6.000 -0.3716 0.00804 0.00289 -0.0638 0.6456 0.3812
-5.750 -0.3426 0.00797 0.00279 -0.0642 0.6406 0.3962
-5.500 -0.3130 0.00785 0.00271 -0.0646 0.6372 0.4090
-5.250 -0.2833 0.00776 0.00263 -0.0651 0.6330 0.4199
-5.000 -0.2536 0.00772 0.00257 -0.0655 0.6286 0.4307
-4.750 -0.2242 0.00767 0.00252 -0.0659 0.6240 0.4411
-4.500 -0.1942 0.00766 0.00248 -0.0663 0.6199 0.4485
-4.250 -0.1642 0.00759 0.00243 -0.0668 0.6162 0.4559
-4.000 -0.1343 0.00756 0.00239 -0.0672 0.6118 0.4624
-3.750 -0.1043 0.00758 0.00235 -0.0676 0.6073 0.4670
-3.500 -0.0748 0.00759 0.00231 -0.0680 0.6023 0.4717
-3.250 -0.0446 0.00753 0.00228 -0.0685 0.5993 0.4774
-3.000 -0.0143 0.00752 0.00226 -0.0690 0.5956 0.4830
-2.750 0.0159 0.00755 0.00224 -0.0695 0.5916 0.4874
-2.500 0.0454 0.00752 0.00222 -0.0699 0.5875 0.4935
-2.250 0.0751 0.00754 0.00222 -0.0703 0.5830 0.4980
-2.000 0.1055 0.00753 0.00221 -0.0708 0.5801 0.5018
-1.750 0.1358 0.00754 0.00219 -0.0713 0.5766 0.5050
-1.500 0.1657 0.00753 0.00217 -0.0717 0.5727 0.5090
-1.250 0.1953 0.00753 0.00217 -0.0721 0.5687 0.5135
-1.000 0.2249 0.00758 0.00219 -0.0725 0.5643 0.5176
-0.750 0.2552 0.00758 0.00220 -0.0730 0.5614 0.5215
-0.500 0.2854 0.00760 0.00220 -0.0735 0.5578 0.5248
-0.250 0.3152 0.00758 0.00221 -0.0739 0.5538 0.5297
0.000 0.3447 0.00761 0.00223 -0.0743 0.5497 0.5340
0.250 0.3741 0.00767 0.00227 -0.0747 0.5455 0.5379
0.500 0.4043 0.00769 0.00229 -0.0752 0.5427 0.5416
0.750 0.4344 0.00772 0.00232 -0.0756 0.5392 0.5446
1.000 0.4640 0.00772 0.00234 -0.0760 0.5353 0.5495
1.250 0.4932 0.00776 0.00239 -0.0764 0.5311 0.5535
1.500 0.5225 0.00783 0.00244 -0.0767 0.5264 0.5574
1.750 0.5524 0.00785 0.00248 -0.0772 0.5227 0.5611
2.000 0.5820 0.00790 0.00252 -0.0776 0.5181 0.5642
2.250 0.6110 0.00793 0.00257 -0.0779 0.5137 0.5694
2.500 0.6397 0.00803 0.00265 -0.0782 0.5088 0.5739
2.750 0.6695 0.00805 0.00271 -0.0786 0.5057 0.5781
3.000 0.6990 0.00810 0.00277 -0.0790 0.5017 0.5818
3.250 0.7280 0.00816 0.00284 -0.0793 0.4974 0.5854
3.500 0.7563 0.00824 0.00293 -0.0795 0.4928 0.5903
3.750 0.7853 0.00831 0.00302 -0.0798 0.4890 0.5948
4.000 0.8146 0.00835 0.00310 -0.0802 0.4853 0.5991
4.250 0.8434 0.00843 0.00318 -0.0805 0.4809 0.6029
4.500 0.8711 0.00853 0.00328 -0.0806 0.4753 0.6078
4.750 0.8995 0.00860 0.00338 -0.0808 0.4697 0.6129
5.000 0.9280 0.00866 0.00347 -0.0811 0.4638 0.6176
5.250 0.9555 0.00879 0.00359 -0.0811 0.4586 0.6218
5.500 0.9830 0.00891 0.00371 -0.0812 0.4538 0.6259
5.750 1.0114 0.00896 0.00383 -0.0815 0.4492 0.6312
6.000 1.0387 0.00908 0.00396 -0.0815 0.4436 0.6361
6.250 1.0646 0.00926 0.00412 -0.0813 0.4372 0.6407
6.500 1.0925 0.00935 0.00424 -0.0815 0.4317 0.6447
6.750 1.1181 0.00949 0.00441 -0.0813 0.4240 0.6507
7.000 1.1439 0.00965 0.00458 -0.0811 0.4168 0.6561
7.250 1.1692 0.00982 0.00476 -0.0808 0.4079 0.6612
7.500 1.1935 0.01003 0.00495 -0.0804 0.3988 0.6653
7.750 1.2169 0.01023 0.00517 -0.0798 0.3877 0.6712
8.000 1.2406 0.01043 0.00538 -0.0793 0.3777 0.6768
8.250 1.2614 0.01072 0.00564 -0.0783 0.3643 0.6824
8.500 1.2794 0.01108 0.00594 -0.0769 0.3458 0.6875
8.750 1.2917 0.01149 0.00631 -0.0744 0.3270 0.6935
9.000 1.2970 0.01206 0.00680 -0.0708 0.3066 0.6994
9.250 1.3019 0.01274 0.00741 -0.0674 0.2881 0.7050
9.500 1.3066 0.01349 0.00810 -0.0642 0.2703 0.7113
9.750 1.3093 0.01438 0.00894 -0.0609 0.2520 0.7180
10.000 1.3117 0.01541 0.00989 -0.0579 0.2342 0.7243
10.250 1.3136 0.01653 0.01097 -0.0551 0.2166 0.7307
10.500 1.3144 0.01782 0.01220 -0.0524 0.1986 0.7378
10.750 1.3162 0.01916 0.01349 -0.0500 0.1836 0.7448
11.000 1.3182 0.02056 0.01487 -0.0478 0.1703 0.7519
11.250 1.3208 0.02201 0.01630 -0.0458 0.1586 0.7596
11.500 1.3246 0.02347 0.01774 -0.0441 0.1478 0.7666
11.750 1.3275 0.02502 0.01930 -0.0424 0.1377 0.7748
12.000 1.3295 0.02671 0.02098 -0.0408 0.1280 0.7833
12.250 1.3319 0.02842 0.02270 -0.0393 0.1189 0.7919
12.500 1.3354 0.03011 0.02440 -0.0381 0.1106 0.8016
12.750 1.3374 0.03199 0.02630 -0.0368 0.1027 0.8113
13.000 1.3384 0.03402 0.02833 -0.0357 0.0949 0.8220
13.250 1.3411 0.03595 0.03029 -0.0347 0.0876 0.8339
13.500 1.3430 0.03800 0.03239 -0.0338 0.0810 0.8483
13.750 1.3441 0.04013 0.03457 -0.0328 0.0751 0.8669
14.000 1.3433 0.04221 0.03675 -0.0315 0.0692 0.9019
14.250 1.3468 0.04440 0.03906 -0.0314 0.0634 1.0000
14.500 1.3504 0.04671 0.04136 -0.0312 0.0586 1.0000
14.750 1.3523 0.04923 0.04388 -0.0310 0.0538 1.0000
15.000 1.3551 0.05171 0.04636 -0.0310 0.0501 1.0000
15.250 1.3592 0.05412 0.04878 -0.0310 0.0467 1.0000
15.500 1.3618 0.05674 0.05142 -0.0311 0.0442 1.0000
15.750 1.3669 0.05913 0.05383 -0.0312 0.0421 1.0000
16.000 1.3702 0.06176 0.05649 -0.0315 0.0402 1.0000
16.250 1.3731 0.06448 0.05922 -0.0318 0.0386 1.0000
16.500 1.3781 0.06702 0.06182 -0.0322 0.0373 1.0000
16.750 1.3828 0.06962 0.06446 -0.0326 0.0362 1.0000
17.000 1.3854 0.07250 0.06737 -0.0332 0.0350 1.0000
17.250 1.3868 0.07559 0.07049 -0.0338 0.0340 1.0000
17.500 1.3921 0.07821 0.07318 -0.0344 0.0333 1.0000
17.750 1.3962 0.08106 0.07608 -0.0351 0.0325 1.0000
18.000 1.4002 0.08391 0.07897 -0.0359 0.0318 1.0000
18.250 1.4011 0.08722 0.08233 -0.0368 0.0310 1.0000
18.500 1.4023 0.09052 0.08567 -0.0378 0.0303 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(4)-421 (naca634421-il)