NACA 63 (naca633418-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63 (naca633418-il) Reynolds number: 200,000 Max Cl/Cd: 69.31 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633418-il-200000.txt Download as CSV file: xf-naca633418-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6517 0.10280 0.09862 -0.0575 1.0000 0.0490
-15.750 -0.6982 0.09056 0.08622 -0.0650 1.0000 0.0484
-15.500 -0.7383 0.08088 0.07635 -0.0708 1.0000 0.0477
-15.250 -0.7759 0.07285 0.06809 -0.0753 1.0000 0.0474
-15.000 -0.8048 0.06664 0.06166 -0.0783 1.0000 0.0472
-14.750 -0.8287 0.06146 0.05626 -0.0803 1.0000 0.0472
-14.500 -0.8479 0.05704 0.05161 -0.0814 1.0000 0.0472
-14.250 -0.8627 0.05333 0.04769 -0.0819 1.0000 0.0474
-14.000 -0.8737 0.05006 0.04421 -0.0820 1.0000 0.0476
-13.750 -0.8832 0.04718 0.04111 -0.0816 1.0000 0.0481
-13.500 -0.8889 0.04469 0.03840 -0.0809 1.0000 0.0484
-13.250 -0.8945 0.04248 0.03598 -0.0797 1.0000 0.0489
-13.000 -0.9007 0.04067 0.03395 -0.0781 1.0000 0.0493
-12.750 -0.8796 0.03862 0.03193 -0.0778 1.0000 0.0506
-12.500 -0.8690 0.03743 0.03077 -0.0767 1.0000 0.0517
-12.250 -0.8629 0.03623 0.02953 -0.0750 1.0000 0.0527
-12.000 -0.8621 0.03526 0.02852 -0.0725 1.0000 0.0537
-11.750 -0.8904 0.03523 0.02850 -0.0656 0.9991 0.0538
-11.500 -0.8568 0.03343 0.02647 -0.0688 0.9921 0.0556
-11.250 -0.8207 0.03164 0.02457 -0.0711 0.9869 0.0576
-11.000 -0.7824 0.03036 0.02336 -0.0741 0.9823 0.0603
-10.750 -0.7483 0.02910 0.02199 -0.0768 0.9748 0.0633
-10.500 -0.7097 0.02768 0.02054 -0.0794 0.9705 0.0666
-10.250 -0.6745 0.02655 0.01945 -0.0819 0.9634 0.0701
-10.000 -0.6390 0.02547 0.01821 -0.0849 0.9556 0.0743
-9.750 -0.6080 0.02423 0.01711 -0.0866 0.9467 0.0793
-9.500 -0.5762 0.02326 0.01601 -0.0887 0.9376 0.0849
-9.250 -0.5587 0.02217 0.01502 -0.0884 0.9242 0.0904
-9.000 -0.5430 0.02150 0.01423 -0.0875 0.9113 0.0962
-8.750 -0.5359 0.02064 0.01343 -0.0853 0.8990 0.1023
-8.500 -0.5234 0.02001 0.01273 -0.0836 0.8880 0.1105
-8.250 -0.5133 0.01929 0.01205 -0.0817 0.8774 0.1202
-8.000 -0.5011 0.01852 0.01131 -0.0800 0.8685 0.1341
-7.750 -0.4889 0.01777 0.01065 -0.0783 0.8586 0.1540
-7.500 -0.4759 0.01685 0.00988 -0.0769 0.8509 0.1861
-7.250 -0.4632 0.01587 0.00922 -0.0756 0.8421 0.2381
-7.000 -0.4475 0.01495 0.00864 -0.0746 0.8347 0.3089
-6.750 -0.4269 0.01449 0.00842 -0.0739 0.8278 0.3726
-6.500 -0.4028 0.01435 0.00835 -0.0734 0.8202 0.4146
-6.250 -0.3765 0.01433 0.00829 -0.0731 0.8147 0.4433
-6.000 -0.3504 0.01440 0.00834 -0.0728 0.8076 0.4653
-5.750 -0.3236 0.01448 0.00835 -0.0724 0.8008 0.4836
-5.500 -0.2958 0.01459 0.00838 -0.0721 0.7957 0.4991
-5.250 -0.2691 0.01473 0.00849 -0.0719 0.7887 0.5127
-5.000 -0.2417 0.01482 0.00849 -0.0717 0.7824 0.5259
-4.750 -0.2135 0.01497 0.00859 -0.0713 0.7776 0.5368
-4.500 -0.1866 0.01512 0.00872 -0.0710 0.7707 0.5472
-4.250 -0.1589 0.01525 0.00877 -0.0709 0.7647 0.5586
-4.000 -0.1308 0.01540 0.00892 -0.0704 0.7599 0.5671
-3.750 -0.1034 0.01553 0.00894 -0.0704 0.7537 0.5781
-3.500 -0.0763 0.01569 0.00917 -0.0698 0.7475 0.5847
-3.250 -0.0476 0.01573 0.00911 -0.0698 0.7427 0.5935
-3.000 -0.0199 0.01579 0.00914 -0.0696 0.7377 0.5997
-2.750 0.0071 0.01588 0.00925 -0.0694 0.7312 0.6056
-2.500 0.0361 0.01581 0.00904 -0.0697 0.7261 0.6134
-2.250 0.0648 0.01582 0.00900 -0.0696 0.7220 0.6180
-2.000 0.0912 0.01590 0.00915 -0.0693 0.7155 0.6231
-1.750 0.1198 0.01587 0.00904 -0.0696 0.7102 0.6298
-1.500 0.1488 0.01581 0.00890 -0.0698 0.7060 0.6350
-1.250 0.1760 0.01588 0.00900 -0.0696 0.7007 0.6394
-1.000 0.2036 0.01591 0.00902 -0.0697 0.6947 0.6451
-0.750 0.2333 0.01583 0.00884 -0.0702 0.6902 0.6515
-0.500 0.2620 0.01586 0.00884 -0.0702 0.6865 0.6554
-0.250 0.2880 0.01596 0.00902 -0.0700 0.6805 0.6604
0.000 0.3166 0.01596 0.00898 -0.0703 0.6751 0.6666
0.250 0.3460 0.01590 0.00887 -0.0706 0.6709 0.6716
0.500 0.3736 0.01601 0.00899 -0.0705 0.6667 0.6761
0.750 0.4002 0.01611 0.00915 -0.0704 0.6609 0.6817
1.000 0.4299 0.01609 0.00907 -0.0710 0.6561 0.6882
1.250 0.4583 0.01610 0.00908 -0.0709 0.6522 0.6922
1.500 0.4847 0.01625 0.00929 -0.0708 0.6472 0.6975
1.750 0.5124 0.01633 0.00939 -0.0710 0.6417 0.7041
2.000 0.5409 0.01633 0.00939 -0.0711 0.6372 0.7090
2.250 0.5702 0.01639 0.00942 -0.0712 0.6336 0.7138
2.500 0.5955 0.01657 0.00970 -0.0711 0.6277 0.7203
2.750 0.6233 0.01662 0.00978 -0.0712 0.6224 0.7265
3.000 0.6514 0.01665 0.00983 -0.0711 0.6183 0.7313
3.250 0.6796 0.01677 0.00996 -0.0712 0.6137 0.7374
3.500 0.7055 0.01691 0.01018 -0.0712 0.6076 0.7441
3.750 0.7322 0.01695 0.01028 -0.0708 0.6027 0.7493
4.000 0.7626 0.01699 0.01028 -0.0712 0.5987 0.7560
4.250 0.7869 0.01718 0.01059 -0.0709 0.5924 0.7626
4.500 0.8124 0.01724 0.01073 -0.0704 0.5867 0.7680
4.750 0.8427 0.01724 0.01070 -0.0708 0.5822 0.7752
5.000 0.8668 0.01740 0.01097 -0.0703 0.5758 0.7818
5.250 0.8918 0.01741 0.01108 -0.0697 0.5691 0.7882
5.500 0.9243 0.01734 0.01091 -0.0704 0.5636 0.7960
5.750 0.9438 0.01743 0.01120 -0.0689 0.5553 0.8020
6.000 0.9719 0.01735 0.01112 -0.0688 0.5487 0.8098
6.250 0.9956 0.01740 0.01127 -0.0681 0.5409 0.8172
6.500 1.0203 0.01728 0.01119 -0.0673 0.5323 0.8246
6.750 1.0437 0.01721 0.01119 -0.0665 0.5220 0.8329
7.000 1.0685 0.01701 0.01096 -0.0655 0.5121 0.8406
7.250 1.0879 0.01702 0.01111 -0.0641 0.5007 0.8499
7.500 1.1085 0.01699 0.01115 -0.0627 0.4910 0.8585
7.750 1.1290 0.01698 0.01120 -0.0613 0.4801 0.8681
8.000 1.1453 0.01703 0.01137 -0.0593 0.4683 0.8789
8.250 1.1612 0.01705 0.01144 -0.0570 0.4560 0.8900
8.500 1.1755 0.01708 0.01151 -0.0546 0.4423 0.9031
8.750 1.1865 0.01715 0.01162 -0.0516 0.4271 0.9190
9.000 1.1940 0.01724 0.01177 -0.0482 0.4103 0.9413
9.250 1.2087 0.01744 0.01206 -0.0467 0.3876 1.0000
9.500 1.2212 0.01812 0.01263 -0.0456 0.3614 1.0000
9.750 1.2283 0.01909 0.01348 -0.0439 0.3310 1.0000
10.000 1.2295 0.02042 0.01463 -0.0416 0.3000 1.0000
10.250 1.2271 0.02207 0.01610 -0.0392 0.2697 1.0000
10.500 1.2222 0.02401 0.01788 -0.0369 0.2404 1.0000
10.750 1.2155 0.02624 0.01994 -0.0347 0.2127 1.0000
11.000 1.2082 0.02870 0.02223 -0.0328 0.1870 1.0000
11.250 1.2019 0.03125 0.02464 -0.0311 0.1639 1.0000
11.500 1.1958 0.03391 0.02718 -0.0298 0.1447 1.0000
11.750 1.1906 0.03663 0.02980 -0.0286 0.1293 1.0000
12.000 1.1876 0.03926 0.03236 -0.0277 0.1168 1.0000
12.250 1.1862 0.04186 0.03492 -0.0270 0.1067 1.0000
12.500 1.1838 0.04461 0.03760 -0.0264 0.0992 1.0000
12.750 1.1866 0.04699 0.04000 -0.0260 0.0921 1.0000
13.000 1.1876 0.04959 0.04256 -0.0256 0.0865 1.0000
13.250 1.1924 0.05188 0.04488 -0.0254 0.0814 1.0000
13.500 1.1947 0.05439 0.04731 -0.0250 0.0773 1.0000
13.750 1.2019 0.05653 0.04954 -0.0249 0.0733 1.0000
14.000 1.2075 0.05883 0.05183 -0.0249 0.0699 1.0000
14.250 1.2152 0.06086 0.05385 -0.0245 0.0668 1.0000
14.500 1.2232 0.06300 0.05607 -0.0246 0.0639 1.0000
14.750 1.2311 0.06512 0.05818 -0.0246 0.0613 1.0000
15.000 1.2437 0.06661 0.05960 -0.0241 0.0589 1.0000
15.250 1.2516 0.06888 0.06201 -0.0242 0.0568 1.0000
15.500 1.2606 0.07098 0.06417 -0.0243 0.0548 1.0000
15.750 1.2718 0.07276 0.06592 -0.0243 0.0530 1.0000
16.000 1.2871 0.07411 0.06725 -0.0239 0.0511 1.0000
16.250 1.2929 0.07672 0.07004 -0.0242 0.0498 1.0000
16.500 1.3001 0.07918 0.07262 -0.0246 0.0484 1.0000
16.750 1.3085 0.08145 0.07496 -0.0249 0.0471 1.0000
17.000 1.3206 0.08323 0.07671 -0.0250 0.0458 1.0000
17.250 1.3357 0.08484 0.07834 -0.0247 0.0444 1.0000
17.500 1.3335 0.08859 0.08231 -0.0257 0.0436 1.0000
17.750 1.3333 0.09215 0.08607 -0.0267 0.0428 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63 (naca633418-il)