NACA 66 (p51htip-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66 (p51htip-il) Reynolds number: 100,000 Max Cl/Cd: 35.37 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-p51htip-il-100000.txt Download as CSV file: xf-p51htip-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4602 0.09906 0.09424 -0.0455 1.0000 0.1205
-10.000 -0.4776 0.09511 0.09040 -0.0493 1.0000 0.1257
-9.750 -0.5193 0.09128 0.08675 -0.0530 1.0000 0.1268
-9.500 -0.5479 0.08978 0.08533 -0.0498 1.0000 0.1267
-9.250 -0.5806 0.08865 0.08427 -0.0455 1.0000 0.1267
-9.000 -0.6123 0.08759 0.08327 -0.0407 1.0000 0.1266
-8.750 -0.6465 0.08645 0.08214 -0.0358 1.0000 0.1267
-8.500 -0.6802 0.08501 0.08064 -0.0316 1.0000 0.1270
-8.250 -0.6469 0.08031 0.07611 -0.0304 1.0000 0.1338
-8.000 -0.6675 0.07818 0.07396 -0.0271 1.0000 0.1359
-7.750 -0.6930 0.07593 0.07164 -0.0239 1.0000 0.1390
-7.500 -0.7463 0.07614 0.07131 -0.0187 1.0000 0.1422
-7.250 -0.7129 0.07029 0.06592 -0.0182 1.0000 0.1497
-7.000 -0.7452 0.06866 0.06384 -0.0146 1.0000 0.1575
-6.750 -0.7268 0.06510 0.06055 -0.0129 1.0000 0.1666
-6.500 -0.7293 0.06237 0.05777 -0.0104 1.0000 0.1780
-6.250 -0.7295 0.05994 0.05526 -0.0077 1.0000 0.1937
-6.000 -0.7281 0.05757 0.05282 -0.0052 1.0000 0.2103
-5.000 -0.6610 0.03747 0.02931 0.0016 1.0000 0.0818
-4.750 -0.6411 0.03462 0.02612 0.0031 1.0000 0.0778
-4.500 -0.6208 0.03268 0.02381 0.0045 1.0000 0.0780
-4.250 -0.5988 0.03075 0.02150 0.0059 1.0000 0.0769
-4.000 -0.5760 0.02912 0.01953 0.0072 1.0000 0.0758
-3.750 -0.5532 0.02775 0.01793 0.0083 1.0000 0.0762
-3.500 -0.5313 0.02675 0.01681 0.0093 1.0000 0.0800
-3.250 -0.5057 0.02594 0.01584 0.0098 0.9990 0.0832
-3.000 -0.4794 0.02489 0.01476 0.0100 0.9977 0.0858
-2.750 -0.4542 0.02403 0.01402 0.0101 0.9960 0.0918
-2.500 -0.4280 0.02349 0.01349 0.0101 0.9940 0.1007
-2.250 -0.4062 0.02292 0.01293 0.0108 0.9925 0.1110
-2.000 -0.0917 0.02680 0.01971 -0.0289 0.9905 1.0000
-1.750 -0.0729 0.02673 0.01951 -0.0289 0.9878 1.0000
-1.500 -0.0520 0.02676 0.01943 -0.0292 0.9853 1.0000
-1.250 -0.0348 0.02675 0.01931 -0.0287 0.9825 1.0000
-1.000 -0.0206 0.02673 0.01921 -0.0276 0.9796 1.0000
-0.750 -0.0028 0.02680 0.01920 -0.0272 0.9765 1.0000
-0.500 0.0198 0.02699 0.01932 -0.0277 0.9734 1.0000
-0.250 0.0341 0.02706 0.01934 -0.0266 0.9700 1.0000
0.000 0.0480 0.02714 0.01938 -0.0253 0.9659 1.0000
0.250 0.0693 0.02737 0.01957 -0.0255 0.9619 1.0000
0.500 0.0889 0.02762 0.01979 -0.0253 0.9575 1.0000
0.750 0.1003 0.02772 0.01987 -0.0236 0.9523 1.0000
1.000 0.1266 0.02809 0.02023 -0.0246 0.9472 1.0000
1.250 0.1381 0.02826 0.02040 -0.0228 0.9411 1.0000
1.500 0.1592 0.02856 0.02070 -0.0228 0.9347 1.0000
1.750 0.1771 0.02886 0.02102 -0.0221 0.9275 1.0000
2.000 0.1990 0.02919 0.02137 -0.0222 0.9201 1.0000
2.250 0.2138 0.02945 0.02167 -0.0208 0.9113 1.0000
2.500 0.2496 0.02999 0.02226 -0.0232 0.9035 1.0000
2.750 0.2567 0.03011 0.02242 -0.0204 0.8927 1.0000
3.000 0.2767 0.03043 0.02280 -0.0197 0.8825 1.0000
3.250 0.3186 0.03096 0.02343 -0.0228 0.8738 1.0000
3.500 0.3289 0.03108 0.02360 -0.0203 0.8612 1.0000
3.750 0.3465 0.03128 0.02390 -0.0189 0.8487 1.0000
4.000 0.3704 0.03151 0.02423 -0.0185 0.8364 1.0000
4.250 0.4025 0.03169 0.02454 -0.0193 0.8240 1.0000
4.500 0.4452 0.03169 0.02476 -0.0215 0.8115 1.0000
4.750 0.6929 0.01959 0.01027 -0.0355 0.1673 1.0000
5.000 0.6881 0.02089 0.01109 -0.0301 0.1184 1.0000
5.250 0.6878 0.02169 0.01179 -0.0253 0.1037 1.0000
5.500 0.6865 0.02242 0.01251 -0.0204 0.0968 1.0000
5.750 0.6868 0.02304 0.01316 -0.0157 0.0915 1.0000
6.000 0.6897 0.02402 0.01400 -0.0115 0.0868 1.0000
6.250 0.7019 0.02473 0.01477 -0.0087 0.0813 1.0000
6.500 0.7254 0.02594 0.01589 -0.0079 0.0760 1.0000
6.750 0.7788 0.02863 0.01852 -0.0120 0.0724 1.0000
7.000 0.8049 0.03007 0.02019 -0.0113 0.0702 1.0000
7.250 0.8270 0.03156 0.02187 -0.0101 0.0673 1.0000
7.500 0.8513 0.03366 0.02424 -0.0092 0.0668 1.0000
7.750 0.8720 0.03607 0.02698 -0.0076 0.0676 1.0000
8.000 0.8900 0.03887 0.03015 -0.0057 0.0692 1.0000
8.250 0.9058 0.04208 0.03367 -0.0038 0.0709 1.0000
8.500 0.9193 0.04552 0.03737 -0.0018 0.0720 1.0000
8.750 0.9368 0.05003 0.04206 -0.0009 0.0735 1.0000
10.500 0.7530 0.09093 0.08615 0.0160 0.1986 1.0000
10.750 0.6895 0.10023 0.09531 0.0073 0.1935 1.0000
11.000 0.6982 0.10356 0.09864 0.0083 0.1827 1.0000
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Polar data table (+)
Polar graphs
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