HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.97 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3010-il-1000000.txt Download as CSV file: xf-hq3010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3822 0.11127 0.10960 -0.0323 1.0000 0.0087
-10.500 -0.3786 0.10766 0.10600 -0.0336 1.0000 0.0088
-10.250 -0.3761 0.10380 0.10214 -0.0349 1.0000 0.0088
-6.750 -0.3071 0.01845 0.01473 -0.0945 0.9165 0.0073
-6.500 -0.2875 0.01515 0.01087 -0.0936 0.9097 0.0072
-6.250 -0.2633 0.01385 0.00935 -0.0931 0.9035 0.0075
-6.000 -0.2378 0.01300 0.00833 -0.0927 0.8981 0.0080
-5.750 -0.2120 0.01223 0.00743 -0.0924 0.8923 0.0084
-5.500 -0.1859 0.01162 0.00669 -0.0921 0.8869 0.0086
-5.250 -0.1593 0.01114 0.00611 -0.0919 0.8815 0.0088
-5.000 -0.1345 0.01000 0.00481 -0.0914 0.8756 0.0091
-4.750 -0.1087 0.00928 0.00394 -0.0911 0.8703 0.0098
-4.500 -0.0818 0.00886 0.00349 -0.0909 0.8644 0.0107
-4.250 -0.0546 0.00851 0.00306 -0.0907 0.8588 0.0115
-4.000 -0.0272 0.00821 0.00269 -0.0906 0.8530 0.0126
-3.750 0.0003 0.00788 0.00229 -0.0905 0.8469 0.0157
-3.500 0.0278 0.00762 0.00206 -0.0904 0.8409 0.0286
-3.250 0.0555 0.00747 0.00193 -0.0903 0.8337 0.0384
-3.000 0.0831 0.00732 0.00178 -0.0903 0.8263 0.0477
-2.750 0.1107 0.00718 0.00163 -0.0902 0.8182 0.0577
-2.500 0.1385 0.00702 0.00149 -0.0902 0.8109 0.0751
-2.250 0.1658 0.00674 0.00136 -0.0902 0.8038 0.1264
-2.000 0.1923 0.00613 0.00121 -0.0904 0.7968 0.2799
-1.750 0.2183 0.00551 0.00110 -0.0904 0.7895 0.4622
-1.500 0.2457 0.00533 0.00107 -0.0903 0.7810 0.5290
-1.250 0.2731 0.00526 0.00104 -0.0902 0.7713 0.5671
-1.000 0.3007 0.00524 0.00102 -0.0901 0.7612 0.5948
-0.750 0.3286 0.00522 0.00101 -0.0900 0.7523 0.6176
-0.500 0.3563 0.00522 0.00102 -0.0899 0.7444 0.6389
-0.250 0.3840 0.00521 0.00104 -0.0898 0.7358 0.6634
0.000 0.4116 0.00521 0.00107 -0.0897 0.7272 0.6892
0.250 0.4390 0.00524 0.00109 -0.0895 0.7176 0.7049
0.500 0.4666 0.00527 0.00110 -0.0894 0.7057 0.7176
0.750 0.4941 0.00531 0.00112 -0.0893 0.6937 0.7283
1.000 0.5217 0.00534 0.00115 -0.0892 0.6830 0.7370
1.250 0.5493 0.00540 0.00118 -0.0891 0.6719 0.7457
1.500 0.5766 0.00545 0.00122 -0.0890 0.6600 0.7549
1.750 0.6038 0.00551 0.00126 -0.0888 0.6467 0.7643
2.000 0.6310 0.00558 0.00131 -0.0886 0.6319 0.7743
2.250 0.6579 0.00565 0.00137 -0.0885 0.6149 0.7850
2.500 0.6845 0.00574 0.00144 -0.0882 0.5957 0.7964
2.750 0.7105 0.00585 0.00152 -0.0878 0.5727 0.8090
3.000 0.7360 0.00600 0.00162 -0.0874 0.5455 0.8236
3.250 0.7610 0.00617 0.00173 -0.0868 0.5157 0.8413
3.500 0.7845 0.00637 0.00187 -0.0860 0.4805 0.8660
3.750 0.8087 0.00642 0.00201 -0.0852 0.4482 0.9519
4.000 0.8380 0.00674 0.00219 -0.0858 0.4120 1.0000
4.250 0.8629 0.00708 0.00238 -0.0854 0.3779 1.0000
4.500 0.8875 0.00743 0.00258 -0.0849 0.3428 1.0000
4.750 0.9118 0.00781 0.00280 -0.0845 0.3090 1.0000
5.000 0.9360 0.00819 0.00305 -0.0840 0.2774 1.0000
5.250 0.9595 0.00863 0.00331 -0.0834 0.2425 1.0000
5.500 0.9828 0.00908 0.00359 -0.0828 0.2064 1.0000
5.750 1.0067 0.00947 0.00385 -0.0822 0.1817 1.0000
6.000 1.0305 0.00987 0.00414 -0.0817 0.1599 1.0000
6.250 1.0544 0.01024 0.00443 -0.0812 0.1401 1.0000
6.500 1.0775 0.01068 0.00475 -0.0805 0.1188 1.0000
6.750 1.0996 0.01120 0.00513 -0.0797 0.0931 1.0000
7.000 1.1209 0.01178 0.00556 -0.0788 0.0677 1.0000
7.250 1.1423 0.01235 0.00600 -0.0779 0.0481 1.0000
7.500 1.1631 0.01295 0.00651 -0.0769 0.0311 1.0000
7.750 1.1837 0.01356 0.00703 -0.0759 0.0188 1.0000
8.000 1.2026 0.01433 0.00770 -0.0746 0.0065 1.0000
8.250 1.2237 0.01487 0.00825 -0.0735 0.0046 1.0000
8.500 1.2451 0.01535 0.00880 -0.0726 0.0043 1.0000
8.750 1.2654 0.01591 0.00943 -0.0714 0.0040 1.0000
9.000 1.2853 0.01648 0.01007 -0.0702 0.0039 1.0000
9.250 1.3039 0.01712 0.01080 -0.0689 0.0037 1.0000
9.500 1.3217 0.01779 0.01155 -0.0674 0.0036 1.0000
9.750 1.3379 0.01854 0.01238 -0.0657 0.0035 1.0000
10.000 1.3508 0.01934 0.01327 -0.0634 0.0034 1.0000
10.250 1.3619 0.02016 0.01417 -0.0608 0.0033 1.0000
10.500 1.3705 0.02112 0.01523 -0.0580 0.0032 1.0000
10.750 1.3776 0.02220 0.01640 -0.0551 0.0031 1.0000
11.000 1.3833 0.02340 0.01771 -0.0523 0.0031 1.0000
11.250 1.3878 0.02472 0.01914 -0.0495 0.0030 1.0000
11.500 1.3901 0.02626 0.02080 -0.0466 0.0030 1.0000
11.750 1.3905 0.02802 0.02270 -0.0439 0.0029 1.0000
12.000 1.3912 0.02985 0.02466 -0.0414 0.0029 1.0000
12.250 1.3927 0.03173 0.02666 -0.0393 0.0029 1.0000
12.500 1.3896 0.03412 0.02918 -0.0372 0.0029 1.0000
12.750 1.3875 0.03654 0.03174 -0.0354 0.0029 1.0000
13.000 1.3844 0.03923 0.03456 -0.0339 0.0029 1.0000
13.250 1.3751 0.04274 0.03824 -0.0326 0.0028 1.0000
13.500 1.3733 0.04556 0.04119 -0.0319 0.0029 1.0000
13.750 1.3638 0.04948 0.04528 -0.0313 0.0028 1.0000
14.000 1.3642 0.05228 0.04818 -0.0313 0.0029 1.0000
14.250 1.3549 0.05657 0.05264 -0.0317 0.0028 1.0000
14.750 1.3515 0.06364 0.05995 -0.0335 0.0027 1.0000
15.000 1.3432 0.06852 0.06498 -0.0351 0.0027 1.0000
15.250 1.3225 0.07566 0.07231 -0.0377 0.0028 1.0000
15.500 1.3145 0.08116 0.07794 -0.0402 0.0027 1.0000
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Polar data table (+)
Polar graphs
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