NACA 63 (naca633418-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63 (naca633418-il) Reynolds number: 50,000 Max Cl/Cd: 16.59 at α=11.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633418-il-50000-n5.txt Download as CSV file: xf-naca633418-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5081 0.10500 0.09710 -0.0556 1.0000 0.0809
-13.500 -0.5741 0.08837 0.08036 -0.0655 1.0000 0.0798
-13.250 -0.6276 0.07726 0.06903 -0.0720 1.0000 0.0789
-13.000 -0.6565 0.07084 0.06243 -0.0749 1.0000 0.0792
-12.750 -0.6754 0.06608 0.05749 -0.0765 1.0000 0.0799
-12.500 -0.6897 0.06209 0.05330 -0.0773 1.0000 0.0810
-12.250 -0.7011 0.05863 0.04962 -0.0774 1.0000 0.0822
-12.000 -0.7104 0.05557 0.04633 -0.0770 1.0000 0.0836
-11.750 -0.7139 0.05306 0.04365 -0.0761 1.0000 0.0853
-11.500 -0.7010 0.05170 0.04238 -0.0750 1.0000 0.0880
-11.250 -0.6975 0.05012 0.04076 -0.0736 1.0000 0.0907
-11.000 -0.6982 0.04854 0.03908 -0.0716 1.0000 0.0934
-10.750 -0.7018 0.04717 0.03755 -0.0690 1.0000 0.0958
-10.500 -0.6982 0.04630 0.03677 -0.0662 1.0000 0.0987
-10.250 -0.7045 0.04569 0.03621 -0.0625 1.0000 0.1010
-10.000 -0.7169 0.04515 0.03566 -0.0580 1.0000 0.1031
-9.750 -0.7078 0.04409 0.03442 -0.0567 0.9960 0.1079
-9.500 -0.6750 0.04280 0.03319 -0.0586 0.9877 0.1154
-9.250 -0.6452 0.04145 0.03172 -0.0604 0.9789 0.1246
-9.000 -0.6187 0.04012 0.03038 -0.0622 0.9698 0.1353
-8.750 -0.5971 0.03877 0.02910 -0.0634 0.9595 0.1468
-8.500 -0.5761 0.03733 0.02771 -0.0648 0.9499 0.1616
-8.250 -0.5568 0.03581 0.02626 -0.0662 0.9401 0.1799
-8.000 -0.5423 0.03433 0.02492 -0.0667 0.9294 0.2026
-7.750 -0.5235 0.03273 0.02357 -0.0681 0.9210 0.2363
-7.500 -0.5154 0.03171 0.02283 -0.0669 0.9094 0.2725
-7.250 -0.4931 0.03110 0.02258 -0.0670 0.9021 0.3261
-7.000 -0.4781 0.03110 0.02271 -0.0653 0.8915 0.3700
-6.750 -0.4463 0.03145 0.02305 -0.0656 0.8855 0.4124
-6.500 -0.4333 0.03168 0.02317 -0.0634 0.8748 0.4398
-6.250 -0.4026 0.03222 0.02356 -0.0633 0.8687 0.4672
-6.000 -0.3884 0.03250 0.02371 -0.0612 0.8588 0.4882
-5.750 -0.3592 0.03313 0.02419 -0.0605 0.8524 0.5078
-5.500 -0.3381 0.03361 0.02455 -0.0590 0.8447 0.5247
-5.250 -0.3102 0.03451 0.02535 -0.0574 0.8374 0.5377
-5.000 -0.2763 0.03507 0.02576 -0.0570 0.8325 0.5510
-4.500 -0.2417 0.03505 0.02547 -0.0543 0.8166 0.5774
-4.250 -0.2099 0.03554 0.02585 -0.0536 0.8114 0.5848
-4.000 -0.2010 0.03527 0.02546 -0.0518 0.8019 0.5970
-3.750 -0.1688 0.03552 0.02561 -0.0514 0.7971 0.6037
-3.500 -0.1583 0.03522 0.02518 -0.0500 0.7888 0.6151
-3.250 -0.1338 0.03543 0.02533 -0.0488 0.7823 0.6210
-3.000 -0.1082 0.03494 0.02466 -0.0493 0.7776 0.6317
-2.750 -0.0958 0.03524 0.02494 -0.0469 0.7689 0.6373
-2.500 -0.0728 0.03515 0.02476 -0.0463 0.7629 0.6451
-2.250 -0.0443 0.03478 0.02424 -0.0469 0.7589 0.6534
-2.000 -0.0361 0.03511 0.02457 -0.0442 0.7496 0.6593
-1.750 -0.0129 0.03480 0.02413 -0.0445 0.7441 0.6684
-1.500 0.0178 0.03468 0.02395 -0.0446 0.7405 0.6739
-1.250 0.0232 0.03505 0.02431 -0.0420 0.7310 0.6805
-1.000 0.0481 0.03481 0.02397 -0.0424 0.7259 0.6888
-0.750 0.0785 0.03473 0.02384 -0.0424 0.7225 0.6940
-0.500 0.0824 0.03519 0.02430 -0.0399 0.7128 0.7012
-0.250 0.1081 0.03509 0.02414 -0.0402 0.7080 0.7084
0.000 0.1382 0.03500 0.02401 -0.0403 0.7047 0.7142
0.250 0.1412 0.03560 0.02462 -0.0381 0.6951 0.7221
0.500 0.1665 0.03563 0.02462 -0.0379 0.6903 0.7282
0.750 0.1965 0.03554 0.02450 -0.0381 0.6871 0.7346
1.000 0.1990 0.03632 0.02528 -0.0363 0.6774 0.7432
1.250 0.2222 0.03646 0.02543 -0.0355 0.6727 0.7489
1.500 0.2535 0.03636 0.02531 -0.0361 0.6695 0.7562
1.750 0.2532 0.03738 0.02637 -0.0337 0.6597 0.7638
2.000 0.2766 0.03756 0.02657 -0.0332 0.6550 0.7708
2.250 0.3100 0.03747 0.02646 -0.0343 0.6519 0.7791
2.500 0.3026 0.03875 0.02781 -0.0307 0.6415 0.7863
2.750 0.3294 0.03892 0.02799 -0.0310 0.6370 0.7951
3.000 0.3607 0.03882 0.02793 -0.0311 0.6342 0.8022
3.250 0.3521 0.04043 0.02959 -0.0284 0.6229 0.8119
3.500 0.3780 0.04052 0.02973 -0.0280 0.6188 0.8200
3.750 0.4117 0.04035 0.02959 -0.0285 0.6161 0.8292
4.000 0.4004 0.04225 0.03158 -0.0255 0.6041 0.8393
4.250 0.4299 0.04226 0.03164 -0.0257 0.6004 0.8494
4.750 0.4504 0.04409 0.03364 -0.0230 0.5852 0.8722
5.000 0.4818 0.04391 0.03354 -0.0231 0.5819 0.8841
5.250 0.4777 0.04576 0.03548 -0.0213 0.5706 0.8996
5.500 0.5065 0.04580 0.03562 -0.0215 0.5661 0.9151
5.750 0.5456 0.04539 0.03532 -0.0225 0.5633 0.9313
6.250 0.5950 0.04719 0.03738 -0.0257 0.5468 1.0000
6.500 0.5953 0.04959 0.03983 -0.0261 0.5340 1.0000
6.750 0.6354 0.04928 0.03960 -0.0275 0.5301 1.0000
7.000 0.6382 0.05162 0.04197 -0.0278 0.5175 1.0000
7.250 0.6774 0.05123 0.04167 -0.0289 0.5132 1.0000
7.500 0.6806 0.05354 0.04403 -0.0291 0.5004 1.0000
7.750 0.7205 0.05287 0.04345 -0.0298 0.4960 1.0000
8.000 0.7233 0.05517 0.04581 -0.0297 0.4826 1.0000
8.250 0.7650 0.05407 0.04483 -0.0300 0.4784 1.0000
8.500 0.7671 0.05637 0.04720 -0.0298 0.4644 1.0000
9.000 0.8137 0.05688 0.04792 -0.0294 0.4460 1.0000
9.250 0.8188 0.05888 0.05000 -0.0291 0.4322 1.0000
9.500 0.8608 0.05684 0.04809 -0.0284 0.4269 1.0000
9.750 0.8693 0.05825 0.04960 -0.0279 0.4128 1.0000
10.000 0.8775 0.05972 0.05118 -0.0274 0.3983 1.0000
10.500 0.9094 0.06062 0.05229 -0.0260 0.3708 1.0000
10.750 0.9335 0.05994 0.05173 -0.0250 0.3571 1.0000
11.000 0.9521 0.05990 0.05177 -0.0242 0.3411 1.0000
11.250 0.9672 0.06032 0.05225 -0.0234 0.3232 1.0000
11.500 0.9835 0.06062 0.05258 -0.0226 0.3039 1.0000
11.750 1.0031 0.06046 0.05239 -0.0215 0.2831 1.0000
12.000 1.0158 0.06130 0.05314 -0.0208 0.2614 1.0000
12.250 1.0217 0.06315 0.05491 -0.0203 0.2398 1.0000
12.500 1.0280 0.06496 0.05658 -0.0199 0.2195 1.0000
12.750 1.0322 0.06715 0.05862 -0.0196 0.2012 1.0000
13.000 1.0343 0.06979 0.06112 -0.0195 0.1847 1.0000
13.250 1.0363 0.07255 0.06380 -0.0196 0.1702 1.0000
13.500 1.0378 0.07555 0.06678 -0.0199 0.1572 1.0000
13.750 1.0403 0.07853 0.06974 -0.0202 0.1458 1.0000
14.000 1.0442 0.08133 0.07250 -0.0205 0.1361 1.0000
14.250 1.0492 0.08398 0.07510 -0.0208 0.1276 1.0000
14.500 1.0528 0.08712 0.07835 -0.0214 0.1199 1.0000
14.750 1.0607 0.08937 0.08048 -0.0216 0.1133 1.0000
15.000 1.0627 0.09294 0.08426 -0.0224 0.1075 1.0000
15.250 1.0701 0.09545 0.08676 -0.0228 0.1022 1.0000
15.500 1.0740 0.09872 0.09015 -0.0236 0.0977 1.0000
15.750 1.0749 0.10257 0.09420 -0.0248 0.0936 1.0000
16.000 1.0847 0.10476 0.09637 -0.0252 0.0898 1.0000
16.250 1.0844 0.10891 0.10068 -0.0266 0.0868 1.0000
16.500 1.0747 0.11484 0.10691 -0.0293 0.0843 1.0000
16.750 1.0672 0.12046 0.11273 -0.0319 0.0820 1.0000
17.000 1.0689 0.12431 0.11665 -0.0335 0.0796 1.0000
17.250 1.0732 0.12766 0.12003 -0.0349 0.0774 1.0000
17.500 1.0370 0.13977 0.13249 -0.0420 0.0768 1.0000
17.750 0.9660 0.16258 0.15558 -0.0559 0.0765 1.0000
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