NACA 63 (naca633418-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63 (naca633418-il) Reynolds number: 100,000 Max Cl/Cd: 44.68 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633418-il-100000-n5.txt Download as CSV file: xf-naca633418-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7092 0.09247 0.08617 -0.0628 1.0000 0.0430
-15.500 -0.7555 0.07844 0.07177 -0.0708 1.0000 0.0433
-15.250 -0.7631 0.07424 0.06747 -0.0728 1.0000 0.0437
-15.000 -0.7706 0.07027 0.06338 -0.0745 1.0000 0.0441
-14.750 -0.7764 0.06670 0.05970 -0.0759 1.0000 0.0446
-14.500 -0.7815 0.06340 0.05628 -0.0770 1.0000 0.0453
-14.250 -0.7870 0.06012 0.05287 -0.0780 1.0000 0.0461
-14.000 -0.7914 0.05700 0.04958 -0.0787 1.0000 0.0468
-13.750 -0.7953 0.05407 0.04645 -0.0792 1.0000 0.0478
-13.500 -0.7964 0.05138 0.04356 -0.0793 1.0000 0.0486
-13.250 -0.7953 0.04898 0.04096 -0.0791 1.0000 0.0496
-13.000 -0.7843 0.04746 0.03949 -0.0787 1.0000 0.0505
-12.750 -0.7754 0.04589 0.03789 -0.0782 1.0000 0.0516
-12.500 -0.7684 0.04429 0.03624 -0.0777 1.0000 0.0529
-12.250 -0.7615 0.04272 0.03457 -0.0770 1.0000 0.0545
-12.000 -0.7547 0.04120 0.03289 -0.0761 1.0000 0.0562
-11.750 -0.7455 0.03997 0.03169 -0.0750 1.0000 0.0577
-11.500 -0.7387 0.03887 0.03065 -0.0736 1.0000 0.0592
-11.250 -0.7353 0.03787 0.02966 -0.0716 1.0000 0.0608
-11.000 -0.7342 0.03698 0.02875 -0.0695 0.9979 0.0626
-10.750 -0.7061 0.03557 0.02724 -0.0716 0.9825 0.0658
-10.500 -0.6783 0.03420 0.02589 -0.0741 0.9705 0.0692
-10.250 -0.6495 0.03296 0.02453 -0.0762 0.9590 0.0735
-10.000 -0.6230 0.03163 0.02323 -0.0783 0.9476 0.0777
-9.500 -0.5732 0.02920 0.02071 -0.0816 0.9245 0.0889
-9.250 -0.5523 0.02817 0.01959 -0.0823 0.9125 0.0958
-9.000 -0.5365 0.02702 0.01845 -0.0824 0.9008 0.1026
-8.750 -0.5241 0.02611 0.01749 -0.0815 0.8883 0.1108
-8.500 -0.5159 0.02524 0.01661 -0.0800 0.8764 0.1195
-8.250 -0.5036 0.02435 0.01572 -0.0789 0.8670 0.1311
-8.000 -0.4937 0.02357 0.01497 -0.0773 0.8560 0.1455
-7.750 -0.4800 0.02272 0.01416 -0.0762 0.8479 0.1659
-7.500 -0.4684 0.02189 0.01344 -0.0748 0.8382 0.1918
-7.250 -0.4535 0.02099 0.01268 -0.0739 0.8312 0.2283
-7.000 -0.4403 0.02024 0.01215 -0.0726 0.8220 0.2718
-6.750 -0.4224 0.01960 0.01174 -0.0716 0.8153 0.3233
-6.500 -0.4022 0.01930 0.01158 -0.0708 0.8079 0.3698
-6.250 -0.3795 0.01917 0.01149 -0.0700 0.8008 0.4060
-6.000 -0.3541 0.01908 0.01133 -0.0696 0.7954 0.4345
-5.750 -0.3304 0.01911 0.01132 -0.0690 0.7878 0.4565
-5.500 -0.3047 0.01916 0.01130 -0.0685 0.7815 0.4754
-5.250 -0.2776 0.01920 0.01123 -0.0682 0.7766 0.4926
-5.000 -0.2533 0.01930 0.01126 -0.0677 0.7690 0.5081
-4.750 -0.2269 0.01942 0.01130 -0.0672 0.7631 0.5219
-4.500 -0.1991 0.01958 0.01139 -0.0666 0.7586 0.5335
-4.250 -0.1743 0.01967 0.01142 -0.0662 0.7512 0.5451
-4.000 -0.1477 0.01978 0.01146 -0.0657 0.7454 0.5546
-3.750 -0.1199 0.01975 0.01131 -0.0655 0.7409 0.5633
-3.500 -0.0945 0.01985 0.01139 -0.0650 0.7343 0.5704
-3.250 -0.0679 0.01975 0.01116 -0.0651 0.7283 0.5790
-3.000 -0.0401 0.01978 0.01114 -0.0647 0.7238 0.5841
-2.750 -0.0138 0.01978 0.01108 -0.0646 0.7180 0.5909
-2.500 0.0126 0.01972 0.01093 -0.0646 0.7119 0.5977
-2.250 0.0401 0.01972 0.01090 -0.0643 0.7071 0.6024
-2.000 0.0678 0.01968 0.01078 -0.0643 0.7025 0.6085
-1.750 0.0938 0.01965 0.01069 -0.0644 0.6962 0.6152
-1.500 0.1206 0.01968 0.01071 -0.0641 0.6912 0.6194
-1.250 0.1492 0.01964 0.01059 -0.0641 0.6872 0.6248
-1.000 0.1755 0.01963 0.01053 -0.0643 0.6811 0.6316
-0.750 0.2016 0.01968 0.01060 -0.0640 0.6756 0.6359
-0.500 0.2293 0.01969 0.01058 -0.0639 0.6714 0.6407
-0.250 0.2579 0.01967 0.01049 -0.0641 0.6674 0.6468
0.000 0.2830 0.01976 0.01059 -0.0641 0.6610 0.6524
0.250 0.3094 0.01981 0.01067 -0.0637 0.6561 0.6568
0.500 0.3381 0.01981 0.01062 -0.0639 0.6523 0.6624
0.750 0.3654 0.01988 0.01067 -0.0642 0.6473 0.6692
1.000 0.3897 0.02002 0.01088 -0.0637 0.6417 0.6732
1.250 0.4169 0.02007 0.01094 -0.0635 0.6372 0.6784
1.500 0.4469 0.02005 0.01087 -0.0639 0.6337 0.6849
1.750 0.4705 0.02028 0.01117 -0.0636 0.6279 0.6904
2.000 0.4954 0.02042 0.01137 -0.0631 0.6226 0.6952
2.250 0.5238 0.02045 0.01141 -0.0633 0.6185 0.7013
2.500 0.5529 0.02050 0.01143 -0.0636 0.6147 0.7078
2.750 0.5739 0.02080 0.01188 -0.0627 0.6084 0.7128
3.000 0.6002 0.02092 0.01204 -0.0625 0.6035 0.7190
3.250 0.6302 0.02093 0.01203 -0.0630 0.5997 0.7256
3.500 0.6526 0.02118 0.01239 -0.0621 0.5943 0.7309
3.750 0.6759 0.02141 0.01271 -0.0616 0.5884 0.7376
4.000 0.7041 0.02147 0.01279 -0.0618 0.5839 0.7443
4.250 0.7312 0.02152 0.01290 -0.0615 0.5797 0.7499
4.500 0.7509 0.02191 0.01342 -0.0606 0.5726 0.7572
4.750 0.7770 0.02200 0.01358 -0.0603 0.5675 0.7639
5.000 0.8067 0.02196 0.01356 -0.0603 0.5635 0.7704
5.250 0.8247 0.02242 0.01418 -0.0593 0.5557 0.7787
5.500 0.8487 0.02250 0.01435 -0.0585 0.5501 0.7849
5.750 0.8777 0.02248 0.01437 -0.0586 0.5451 0.7927
6.000 0.8936 0.02289 0.01495 -0.0570 0.5368 0.8004
6.250 0.9213 0.02280 0.01492 -0.0567 0.5307 0.8082
6.500 0.9391 0.02309 0.01534 -0.0553 0.5222 0.8168
6.750 0.9633 0.02303 0.01535 -0.0544 0.5144 0.8253
7.000 0.9808 0.02326 0.01571 -0.0529 0.5054 0.8346
7.250 1.0039 0.02319 0.01571 -0.0519 0.4967 0.8443
7.500 1.0167 0.02345 0.01613 -0.0496 0.4862 0.8549
7.750 1.0374 0.02338 0.01610 -0.0482 0.4755 0.8666
8.000 1.0495 0.02349 0.01633 -0.0457 0.4629 0.8799
8.250 1.0565 0.02374 0.01670 -0.0425 0.4495 0.8965
8.500 1.0634 0.02394 0.01699 -0.0393 0.4357 0.9183
8.750 1.0759 0.02423 0.01737 -0.0375 0.4195 0.9546
9.000 1.0885 0.02481 0.01798 -0.0365 0.4017 1.0000
9.250 1.0996 0.02563 0.01879 -0.0354 0.3827 1.0000
9.500 1.1093 0.02656 0.01966 -0.0342 0.3619 1.0000
9.750 1.1155 0.02780 0.02085 -0.0328 0.3389 1.0000
10.000 1.1201 0.02918 0.02211 -0.0314 0.3144 1.0000
10.250 1.1223 0.03085 0.02367 -0.0300 0.2894 1.0000
10.500 1.1219 0.03279 0.02547 -0.0286 0.2652 1.0000
10.750 1.1208 0.03495 0.02751 -0.0274 0.2414 1.0000
11.000 1.1181 0.03733 0.02977 -0.0263 0.2190 1.0000
11.250 1.1153 0.03985 0.03219 -0.0254 0.1985 1.0000
11.500 1.1132 0.04244 0.03469 -0.0247 0.1796 1.0000
11.750 1.1111 0.04511 0.03729 -0.0242 0.1627 1.0000
12.000 1.1096 0.04783 0.03995 -0.0238 0.1476 1.0000
12.250 1.1089 0.05057 0.04265 -0.0236 0.1345 1.0000
12.500 1.1086 0.05337 0.04541 -0.0234 0.1231 1.0000
12.750 1.1084 0.05624 0.04823 -0.0234 0.1134 1.0000
13.000 1.1110 0.05890 0.05091 -0.0235 0.1045 1.0000
13.250 1.1129 0.06168 0.05368 -0.0236 0.0976 1.0000
13.500 1.1154 0.06445 0.05648 -0.0239 0.0913 1.0000
13.750 1.1184 0.06720 0.05923 -0.0241 0.0861 1.0000
14.000 1.1225 0.06989 0.06198 -0.0244 0.0811 1.0000
14.250 1.1249 0.07279 0.06484 -0.0248 0.0773 1.0000
14.500 1.1312 0.07528 0.06743 -0.0251 0.0731 1.0000
14.750 1.1352 0.07806 0.07025 -0.0256 0.0699 1.0000
15.000 1.1402 0.08072 0.07292 -0.0260 0.0670 1.0000
15.250 1.1464 0.08333 0.07564 -0.0265 0.0638 1.0000
15.500 1.1514 0.08608 0.07843 -0.0271 0.0613 1.0000
15.750 1.1573 0.08862 0.08092 -0.0276 0.0592 1.0000
16.000 1.1640 0.09126 0.08373 -0.0281 0.0569 1.0000
16.250 1.1697 0.09402 0.08659 -0.0288 0.0548 1.0000
16.500 1.1750 0.09682 0.08943 -0.0296 0.0530 1.0000
16.750 1.1823 0.09923 0.09181 -0.0302 0.0514 1.0000
17.000 1.1863 0.10238 0.09517 -0.0311 0.0499 1.0000
17.250 1.1899 0.10561 0.09855 -0.0322 0.0484 1.0000
17.500 1.1933 0.10883 0.10187 -0.0334 0.0470 1.0000
17.750 1.1982 0.11175 0.10482 -0.0345 0.0458 1.0000
18.000 1.2056 0.11420 0.10726 -0.0354 0.0446 1.0000
18.250 1.2021 0.11880 0.11213 -0.0375 0.0436 1.0000
18.500 1.1988 0.12339 0.11692 -0.0397 0.0427 1.0000
18.750 1.1953 0.12808 0.12180 -0.0421 0.0418 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63 (naca633418-il)