NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 100,000 Max Cl/Cd: 33.52 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662415-il-100000.txt Download as CSV file: xf-naca662415-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5378 0.11093 0.10658 -0.0321 1.0000 0.1415
-9.500 -0.5867 0.10561 0.10139 -0.0371 0.9990 0.1457
-9.250 -0.6383 0.10070 0.09649 -0.0405 0.9966 0.1462
-9.000 -0.5671 0.09926 0.09502 -0.0354 0.9960 0.1563
-8.750 -0.6064 0.09399 0.08981 -0.0389 0.9940 0.1593
-8.500 -0.6531 0.09078 0.08660 -0.0374 0.9916 0.1601
-8.250 -0.7007 0.08833 0.08408 -0.0338 0.9913 0.1610
-8.000 -0.7513 0.08670 0.08229 -0.0281 0.9945 0.1619
-7.750 -0.7067 0.08222 0.07803 -0.0285 0.9921 0.1699
-7.500 -0.7346 0.07974 0.07547 -0.0246 0.9942 0.1742
-7.250 -0.8021 0.07936 0.07461 -0.0166 1.0000 0.1780
-7.000 -0.7731 0.07424 0.06991 -0.0153 1.0000 0.1836
-5.500 -0.7383 0.04760 0.04069 -0.0090 1.0000 0.1259
-5.250 -0.7094 0.04178 0.03334 -0.0063 1.0000 0.0857
-5.000 -0.6897 0.03909 0.03040 -0.0053 1.0000 0.0834
-4.750 -0.6690 0.03714 0.02813 -0.0043 1.0000 0.0824
-4.500 -0.6480 0.03570 0.02639 -0.0032 1.0000 0.0834
-4.250 -0.6264 0.03433 0.02475 -0.0022 1.0000 0.0837
-4.000 -0.6046 0.03311 0.02332 -0.0013 1.0000 0.0837
-3.750 -0.5827 0.03209 0.02212 -0.0003 1.0000 0.0844
-3.500 -0.5610 0.03132 0.02121 0.0007 1.0000 0.0859
-3.250 -0.5399 0.03038 0.02023 0.0016 1.0000 0.0889
-3.000 -0.5194 0.02961 0.01955 0.0025 1.0000 0.0923
-2.750 -0.4989 0.02906 0.01904 0.0034 1.0000 0.0952
-2.500 -0.4785 0.02864 0.01860 0.0043 1.0000 0.0997
-2.250 -0.4587 0.02811 0.01814 0.0051 1.0000 0.1069
-2.000 -0.4381 0.02785 0.01785 0.0059 1.0000 0.1163
-1.750 -0.4172 0.02745 0.01757 0.0064 1.0000 0.1332
-1.500 -0.4114 0.02532 0.01867 0.0109 1.0000 0.7065
-1.250 -0.4224 0.02676 0.02028 0.0224 1.0000 0.8187
-1.000 -0.4280 0.02762 0.02111 0.0315 1.0000 0.8611
-0.750 -0.1857 0.03666 0.02960 -0.0002 1.0000 0.9873
-0.500 -0.1353 0.03749 0.03026 -0.0064 1.0000 0.9960
-0.250 -0.1058 0.03800 0.03066 -0.0087 1.0000 1.0000
0.000 -0.0984 0.03798 0.03058 -0.0067 1.0000 1.0000
0.250 -0.0911 0.03798 0.03052 -0.0046 1.0000 1.0000
0.500 -0.0840 0.03799 0.03048 -0.0026 1.0000 1.0000
0.750 -0.0772 0.03801 0.03046 -0.0005 1.0000 1.0000
1.000 -0.0608 0.03822 0.03063 -0.0003 0.9978 1.0000
1.250 -0.0226 0.03903 0.03140 -0.0044 0.9880 1.0000
1.500 0.0106 0.03978 0.03211 -0.0074 0.9772 1.0000
1.750 0.0405 0.04048 0.03278 -0.0097 0.9657 1.0000
2.000 0.0705 0.04136 0.03364 -0.0119 0.9549 1.0000
2.250 0.1057 0.04241 0.03467 -0.0149 0.9419 1.0000
2.500 0.2320 0.04198 0.03419 -0.0304 0.8701 1.0000
2.750 0.2556 0.04220 0.03443 -0.0305 0.8579 1.0000
3.000 0.3004 0.04270 0.03495 -0.0340 0.8490 1.0000
3.250 0.3025 0.04262 0.03489 -0.0305 0.8363 1.0000
3.500 0.3167 0.04274 0.03504 -0.0290 0.8244 1.0000
3.750 0.3648 0.04311 0.03548 -0.0326 0.8172 1.0000
4.000 0.3654 0.04301 0.03542 -0.0289 0.8040 1.0000
4.250 0.3740 0.04304 0.03549 -0.0263 0.7916 1.0000
4.500 0.3943 0.04310 0.03560 -0.0255 0.7811 1.0000
4.750 0.4233 0.04307 0.03564 -0.0258 0.7722 1.0000
5.000 0.4276 0.04298 0.03562 -0.0225 0.7593 1.0000
5.250 0.4390 0.04289 0.03558 -0.0201 0.7476 1.0000
5.500 0.4802 0.04257 0.03538 -0.0219 0.7406 1.0000
5.750 0.4849 0.04235 0.03522 -0.0185 0.7272 1.0000
6.000 0.4999 0.04213 0.03509 -0.0166 0.7144 1.0000
6.250 0.5551 0.04125 0.03439 -0.0197 0.7092 1.0000
6.500 0.5789 0.04059 0.03386 -0.0187 0.6952 1.0000
6.750 0.6631 0.03550 0.02904 -0.0216 0.6783 1.0000
7.000 0.7075 0.03121 0.02494 -0.0196 0.6523 1.0000
7.500 0.7540 0.02761 0.02167 -0.0148 0.6030 1.0000
7.750 0.7921 0.02363 0.01604 -0.0092 0.3188 1.0000
8.000 0.7722 0.02657 0.01760 -0.0041 0.1539 1.0000
8.250 0.7749 0.02852 0.01906 -0.0016 0.1156 1.0000
8.500 0.7847 0.03001 0.02041 0.0000 0.1013 1.0000
8.750 0.8009 0.03119 0.02160 0.0010 0.0925 1.0000
9.000 0.8214 0.03246 0.02276 0.0017 0.0855 1.0000
9.250 0.8484 0.03353 0.02380 0.0016 0.0788 1.0000
9.500 0.9029 0.03506 0.02517 -0.0011 0.0738 1.0000
9.750 0.9438 0.03652 0.02681 -0.0027 0.0697 1.0000
10.000 0.9906 0.03851 0.02887 -0.0054 0.0659 1.0000
10.250 1.0604 0.04251 0.03302 -0.0115 0.0640 1.0000
10.500 1.1062 0.04726 0.03812 -0.0150 0.0630 1.0000
10.750 1.1182 0.04960 0.04083 -0.0133 0.0626 1.0000
11.000 1.1257 0.05203 0.04363 -0.0110 0.0622 1.0000
11.250 1.1447 0.05651 0.04841 -0.0110 0.0628 1.0000
11.500 1.1526 0.05879 0.05103 -0.0087 0.0639 1.0000
11.750 1.1169 0.06032 0.05320 -0.0007 0.0663 1.0000
12.000 1.0941 0.06444 0.05781 0.0039 0.0694 1.0000
12.250 1.0828 0.06882 0.06247 0.0065 0.0717 1.0000
12.500 0.9618 0.06515 0.05944 0.0171 0.0708 1.0000
12.750 0.9409 0.07014 0.06465 0.0188 0.0722 1.0000
13.000 0.9484 0.07547 0.07011 0.0189 0.0762 1.0000
13.250 0.8988 0.08038 0.07532 0.0207 0.0767 1.0000
13.500 0.8445 0.08659 0.08181 0.0206 0.0772 1.0000
13.750 0.7823 0.09432 0.08979 0.0181 0.0778 1.0000
14.000 0.6567 0.11756 0.11333 0.0047 0.1024 1.0000
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Polar data table (+)
Polar graphs
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