NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-618 (naca633618-il) Reynolds number: 50,000 Max Cl/Cd: 5.09 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633618-il-50000.txt Download as CSV file: xf-naca633618-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-618
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2603 0.12512 0.11799 -0.0390 1.0000 0.3312
-11.000 -0.2985 0.12671 0.11978 -0.0368 1.0000 0.3361
-10.000 -0.5650 0.08586 0.07966 -0.0529 1.0000 0.1683
-9.750 -0.5613 0.08487 0.07872 -0.0497 1.0000 0.1704
-9.500 -0.7611 0.07330 0.06689 -0.0502 1.0000 0.1515
-9.250 -0.7792 0.06957 0.06299 -0.0487 1.0000 0.1510
-9.000 -0.7958 0.06572 0.05888 -0.0476 1.0000 0.1510
-8.750 -0.8063 0.06188 0.05470 -0.0467 1.0000 0.1512
-8.500 -0.8037 0.05852 0.05125 -0.0459 1.0000 0.1530
-8.250 -0.7972 0.05582 0.04843 -0.0449 1.0000 0.1550
-8.000 -0.7901 0.05325 0.04566 -0.0443 1.0000 0.1579
-7.750 -0.7818 0.05053 0.04259 -0.0440 1.0000 0.1612
-7.500 -0.7704 0.04773 0.03929 -0.0442 1.0000 0.1648
-7.250 -0.7557 0.04523 0.03638 -0.0442 1.0000 0.1685
-7.000 -0.7398 0.04369 0.03491 -0.0433 1.0000 0.1743
-6.750 -0.7223 0.04201 0.03290 -0.0431 1.0000 0.1809
-6.500 -0.7046 0.04043 0.03122 -0.0425 1.0000 0.1873
-6.250 -0.6866 0.03925 0.02994 -0.0420 1.0000 0.1968
-6.000 -0.6690 0.03812 0.02888 -0.0410 1.0000 0.2071
-5.750 -0.6386 0.03722 0.02804 -0.0423 0.9954 0.2245
-5.500 -0.6054 0.03634 0.02730 -0.0441 0.9889 0.2528
-5.250 -0.5719 0.03544 0.02700 -0.0460 0.9823 0.3055
-5.000 -0.5488 0.03540 0.02796 -0.0452 0.9764 0.4056
-4.750 -0.5314 0.03798 0.03093 -0.0407 0.9708 0.4835
-4.500 -0.5158 0.04045 0.03339 -0.0362 0.9657 0.5299
-4.250 -0.5075 0.04267 0.03565 -0.0301 0.9612 0.5562
-4.000 -0.4941 0.04456 0.03744 -0.0257 0.9572 0.5856
-3.750 -0.4800 0.04693 0.03977 -0.0202 0.9532 0.6091
-3.500 -0.4752 0.04798 0.04077 -0.0149 0.9507 0.6304
-3.250 -0.4687 0.04888 0.04160 -0.0101 0.9491 0.6528
-3.000 -0.5370 0.04483 0.03772 0.0022 1.0000 0.6504
-2.750 -0.5296 0.04553 0.03833 0.0064 1.0000 0.6737
-2.500 -0.5216 0.04602 0.03873 0.0102 1.0000 0.6960
-2.250 -0.5154 0.04642 0.03905 0.0145 1.0000 0.7153
-2.000 -0.5082 0.04664 0.03919 0.0183 1.0000 0.7342
-1.750 -0.5003 0.04674 0.03920 0.0217 1.0000 0.7529
-1.500 -0.4919 0.04675 0.03911 0.0248 1.0000 0.7711
-1.250 -0.4828 0.04669 0.03896 0.0275 1.0000 0.7889
-1.000 -0.4720 0.04656 0.03873 0.0294 1.0000 0.8056
-0.750 -0.4586 0.04643 0.03848 0.0303 1.0000 0.8209
-0.500 -0.4469 0.04624 0.03820 0.0320 1.0000 0.8338
-0.250 -0.4329 0.04609 0.03794 0.0328 1.0000 0.8465
0.000 -0.4173 0.04600 0.03775 0.0330 1.0000 0.8591
0.250 -0.4009 0.04600 0.03764 0.0328 1.0000 0.8720
0.500 -0.3850 0.04600 0.03754 0.0330 1.0000 0.8842
0.750 -0.3677 0.04608 0.03753 0.0328 1.0000 0.8963
1.000 -0.3425 0.04668 0.03805 0.0308 0.9966 0.9091
1.250 -0.3105 0.04775 0.03901 0.0275 0.9898 0.9222
1.500 -0.2691 0.04965 0.04081 0.0222 0.9815 0.9364
1.750 -0.2334 0.05050 0.04159 0.0179 0.9717 0.9485
2.000 -0.1906 0.05201 0.04303 0.0119 0.9630 0.9605
2.250 -0.1286 0.05504 0.04599 0.0022 0.9534 0.9728
2.500 -0.0866 0.05607 0.04698 -0.0039 0.9415 0.9828
2.750 -0.0399 0.05795 0.04883 -0.0110 0.9315 0.9947
3.000 -0.0139 0.05955 0.05035 -0.0143 0.9206 1.0000
3.250 -0.0066 0.05909 0.04985 -0.0140 0.9077 1.0000
3.500 0.0180 0.06062 0.05132 -0.0170 0.8998 1.0000
3.750 0.0488 0.06211 0.05276 -0.0209 0.8872 1.0000
4.000 0.0698 0.06318 0.05380 -0.0232 0.8774 1.0000
4.250 0.1128 0.06612 0.05668 -0.0292 0.8677 1.0000
4.500 0.1298 0.06685 0.05740 -0.0307 0.8562 1.0000
4.750 0.1783 0.07077 0.06127 -0.0375 0.8484 1.0000
5.000 0.1905 0.07104 0.06154 -0.0382 0.8354 1.0000
5.250 0.2284 0.07438 0.06486 -0.0431 0.8281 1.0000
5.500 0.2507 0.07568 0.06617 -0.0453 0.8146 1.0000
5.750 0.2708 0.07757 0.06806 -0.0474 0.8048 1.0000
6.000 0.3106 0.08088 0.07138 -0.0520 0.7941 1.0000
6.250 0.3207 0.08195 0.07247 -0.0525 0.7820 1.0000
6.500 0.3648 0.08634 0.07685 -0.0576 0.7739 1.0000
6.750 0.3732 0.08699 0.07755 -0.0577 0.7599 1.0000
7.000 0.3885 0.08909 0.07967 -0.0589 0.7494 1.0000
7.250 0.4294 0.09306 0.08366 -0.0631 0.7388 1.0000
7.500 0.4328 0.09397 0.08461 -0.0627 0.7253 1.0000
7.750 0.4510 0.09662 0.08731 -0.0642 0.7152 1.0000
8.000 0.4881 0.10037 0.09111 -0.0675 0.7030 1.0000
8.250 0.4906 0.10154 0.09233 -0.0671 0.6891 1.0000
8.500 0.5042 0.10413 0.09497 -0.0681 0.6782 1.0000
8.750 0.5454 0.10862 0.09953 -0.0715 0.6665 1.0000
9.000 0.5476 0.10977 0.10075 -0.0712 0.6518 1.0000
9.250 0.5544 0.11199 0.10303 -0.0716 0.6387 1.0000
9.500 0.5728 0.11520 0.10632 -0.0730 0.6276 1.0000
9.750 0.6069 0.11920 0.11041 -0.0753 0.6136 1.0000
10.000 0.6156 0.12113 0.11242 -0.0756 0.5982 1.0000
10.250 0.6169 0.12326 0.11462 -0.0758 0.5846 1.0000
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Polar data table (+)
Polar graphs
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