HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 500,000 Max Cl/Cd: 83.39 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq208-il-500000-n5.txt Download as CSV file: xf-hq208-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4561 0.07970 0.07752 -0.0270 1.0000 0.0060
-8.000 -0.4608 0.07553 0.07338 -0.0290 1.0000 0.0058
-7.750 -0.4681 0.07165 0.06956 -0.0309 1.0000 0.0057
-7.500 -0.4701 0.06630 0.06423 -0.0368 1.0000 0.0056
-7.250 -0.4713 0.06068 0.05858 -0.0414 1.0000 0.0054
-7.000 -0.4684 0.05549 0.05331 -0.0445 0.9991 0.0052
-6.750 -0.4465 0.04802 0.04563 -0.0519 0.9903 0.0049
-6.500 -0.4216 0.04062 0.03791 -0.0577 0.9836 0.0047
-6.250 -0.3964 0.03309 0.02994 -0.0614 0.9756 0.0043
-6.000 -0.3729 0.02265 0.01859 -0.0632 0.9663 0.0039
-5.750 -0.3444 0.01828 0.01358 -0.0641 0.9600 0.0039
-5.500 -0.3170 0.01605 0.01097 -0.0643 0.9516 0.0040
-5.250 -0.2881 0.01449 0.00912 -0.0646 0.9446 0.0042
-5.000 -0.2604 0.01330 0.00772 -0.0646 0.9361 0.0046
-4.750 -0.2331 0.01232 0.00656 -0.0645 0.9278 0.0053
-4.250 -0.1789 0.01110 0.00505 -0.0641 0.9112 0.0064
-4.000 -0.1531 0.01027 0.00412 -0.0639 0.9032 0.0085
-3.750 -0.1263 0.00981 0.00356 -0.0636 0.8951 0.0098
-3.500 -0.0994 0.00943 0.00307 -0.0633 0.8874 0.0112
-3.250 -0.0723 0.00916 0.00268 -0.0631 0.8799 0.0123
-3.000 -0.0452 0.00881 0.00228 -0.0629 0.8723 0.0193
-2.500 0.0091 0.00836 0.00185 -0.0626 0.8574 0.0560
-2.250 0.0362 0.00816 0.00168 -0.0625 0.8500 0.0821
-2.000 0.0625 0.00766 0.00152 -0.0625 0.8416 0.1835
-1.750 0.0878 0.00686 0.00134 -0.0625 0.8333 0.3831
-1.500 0.1140 0.00652 0.00124 -0.0623 0.8245 0.4862
-1.250 0.1406 0.00635 0.00120 -0.0621 0.8130 0.5451
-1.000 0.1668 0.00621 0.00118 -0.0616 0.7992 0.6077
-0.750 0.1927 0.00609 0.00118 -0.0611 0.7849 0.6684
-0.500 0.2190 0.00603 0.00117 -0.0606 0.7717 0.7060
-0.250 0.2457 0.00602 0.00116 -0.0602 0.7580 0.7298
0.000 0.2724 0.00602 0.00114 -0.0599 0.7436 0.7481
0.250 0.2994 0.00605 0.00113 -0.0596 0.7276 0.7600
0.500 0.3265 0.00608 0.00113 -0.0594 0.7111 0.7714
0.750 0.3535 0.00612 0.00114 -0.0591 0.6964 0.7835
1.250 0.4069 0.00621 0.00118 -0.0585 0.6635 0.8096
1.500 0.4332 0.00625 0.00123 -0.0581 0.6457 0.8245
1.750 0.4592 0.00630 0.00128 -0.0576 0.6250 0.8418
2.000 0.4844 0.00636 0.00134 -0.0570 0.6004 0.8634
2.250 0.5087 0.00642 0.00140 -0.0561 0.5722 0.8968
2.500 0.5429 0.00654 0.00147 -0.0575 0.5325 0.9705
2.750 0.5704 0.00684 0.00161 -0.0576 0.4874 1.0000
3.000 0.5945 0.00730 0.00179 -0.0571 0.4225 1.0000
3.250 0.6172 0.00796 0.00204 -0.0564 0.3332 1.0000
3.500 0.6412 0.00851 0.00229 -0.0560 0.2707 1.0000
3.750 0.6667 0.00886 0.00252 -0.0557 0.2407 1.0000
4.000 0.6923 0.00920 0.00277 -0.0555 0.2113 1.0000
4.250 0.7178 0.00955 0.00301 -0.0552 0.1805 1.0000
4.500 0.7427 0.00997 0.00327 -0.0549 0.1440 1.0000
4.750 0.7659 0.01064 0.00366 -0.0544 0.0886 1.0000
5.000 0.7893 0.01129 0.00409 -0.0539 0.0492 1.0000
5.250 0.8138 0.01177 0.00446 -0.0535 0.0313 1.0000
5.500 0.8387 0.01218 0.00485 -0.0531 0.0201 1.0000
5.750 0.8636 0.01260 0.00524 -0.0527 0.0117 1.0000
6.000 0.8879 0.01311 0.00574 -0.0522 0.0058 1.0000
6.250 0.9121 0.01364 0.00631 -0.0516 0.0043 1.0000
6.500 0.9363 0.01416 0.00693 -0.0511 0.0033 1.0000
6.750 0.9603 0.01469 0.00756 -0.0505 0.0031 1.0000
7.000 0.9838 0.01529 0.00828 -0.0499 0.0028 1.0000
7.250 1.0067 0.01599 0.00913 -0.0491 0.0025 1.0000
7.500 1.0285 0.01683 0.01011 -0.0482 0.0022 1.0000
7.750 1.0499 0.01769 0.01109 -0.0473 0.0021 1.0000
8.000 1.0703 0.01868 0.01222 -0.0463 0.0020 1.0000
8.250 1.0897 0.01980 0.01349 -0.0451 0.0019 1.0000
8.500 1.1080 0.02105 0.01490 -0.0438 0.0019 1.0000
8.750 1.1255 0.02239 0.01641 -0.0424 0.0018 1.0000
9.000 1.1418 0.02390 0.01810 -0.0410 0.0018 1.0000
9.250 1.1567 0.02556 0.01997 -0.0394 0.0017 1.0000
9.500 1.1703 0.02732 0.02196 -0.0377 0.0017 1.0000
9.750 1.1812 0.02936 0.02425 -0.0357 0.0017 1.0000
10.000 1.1900 0.03146 0.02661 -0.0336 0.0017 1.0000
10.250 1.1948 0.03381 0.02929 -0.0312 0.0017 1.0000
10.500 1.1924 0.03627 0.03202 -0.0279 0.0017 1.0000
10.750 1.1861 0.03878 0.03478 -0.0245 0.0017 1.0000
11.000 1.1776 0.04153 0.03778 -0.0217 0.0017 1.0000
11.250 1.1654 0.04486 0.04135 -0.0197 0.0017 1.0000
11.500 1.1523 0.04861 0.04533 -0.0187 0.0017 1.0000
11.750 1.1360 0.05317 0.05012 -0.0189 0.0017 1.0000
12.000 1.1192 0.05846 0.05562 -0.0204 0.0018 1.0000
12.250 1.1008 0.06483 0.06218 -0.0235 0.0018 1.0000
12.500 1.0813 0.07261 0.07016 -0.0284 0.0018 1.0000
12.750 1.0602 0.08236 0.08009 -0.0353 0.0018 1.0000
13.000 1.0395 0.09363 0.09149 -0.0429 0.0018 1.0000
13.250 1.0161 0.10609 0.10403 -0.0502 0.0018 1.0000
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Polar data table (+)
Polar graphs
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