HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il) Reynolds number: 50,000 Max Cl/Cd: 32.43 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1010-il-50000.txt Download as CSV file: xf-hq1010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/10 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4861 0.09645 0.08966 0.0036 1.0000 0.3518
-8.250 -0.4849 0.09306 0.08632 0.0036 1.0000 0.3643
-8.000 -0.5806 0.07561 0.06927 -0.0259 1.0000 0.1714
-7.500 -0.6170 0.06048 0.05366 -0.0348 1.0000 0.1316
-7.250 -0.6255 0.05445 0.04692 -0.0357 1.0000 0.1209
-7.000 -0.6145 0.04993 0.04221 -0.0350 1.0000 0.1184
-6.750 -0.6051 0.04556 0.03743 -0.0340 1.0000 0.1165
-6.500 -0.5935 0.04180 0.03317 -0.0327 1.0000 0.1172
-6.250 -0.5810 0.03869 0.02928 -0.0309 1.0000 0.1215
-6.000 -0.5627 0.03561 0.02625 -0.0297 1.0000 0.1283
-5.750 -0.5444 0.03290 0.02285 -0.0279 1.0000 0.1352
-5.500 -0.5252 0.03065 0.02039 -0.0265 1.0000 0.1494
-5.250 -0.5041 0.02840 0.01808 -0.0250 1.0000 0.1644
-5.000 -0.4836 0.02658 0.01634 -0.0235 1.0000 0.1855
-4.750 -0.4625 0.02482 0.01463 -0.0219 1.0000 0.2110
-4.500 -0.4424 0.02313 0.01308 -0.0201 1.0000 0.2489
-4.250 -0.4250 0.02108 0.01163 -0.0181 1.0000 0.3195
-4.000 -0.4220 0.01903 0.01137 -0.0123 1.0000 0.5242
-3.750 -0.4224 0.01954 0.01234 -0.0032 1.0000 0.6785
-3.500 -0.4189 0.02012 0.01290 0.0048 1.0000 0.7501
-3.250 -0.4125 0.02049 0.01320 0.0120 1.0000 0.8062
-3.000 -0.3917 0.02098 0.01349 0.0175 1.0000 0.8661
-2.750 -0.1589 0.02213 0.01318 -0.0125 1.0000 0.9584
-2.500 -0.0513 0.02087 0.01134 -0.0287 1.0000 0.9930
-2.250 -0.0252 0.02027 0.01062 -0.0309 1.0000 1.0000
-2.000 -0.0262 0.02004 0.01039 -0.0280 1.0000 1.0000
-1.750 -0.0325 0.01989 0.01024 -0.0244 1.0000 1.0000
-1.500 -0.0429 0.01977 0.01011 -0.0201 1.0000 1.0000
-1.250 -0.0555 0.01963 0.00993 -0.0156 1.0000 1.0000
-1.000 -0.0692 0.01943 0.00972 -0.0109 1.0000 1.0000
-0.750 -0.0824 0.01918 0.00944 -0.0062 1.0000 1.0000
-0.500 -0.0895 0.01899 0.00917 -0.0024 1.0000 1.0000
-0.250 -0.0855 0.01896 0.00902 -0.0002 1.0000 1.0000
0.000 -0.0737 0.01909 0.00902 0.0009 1.0000 1.0000
0.250 -0.0584 0.01931 0.00912 0.0015 1.0000 1.0000
0.500 -0.0415 0.01961 0.00931 0.0019 1.0000 1.0000
0.750 -0.0239 0.01997 0.00955 0.0021 1.0000 1.0000
1.000 -0.0059 0.02038 0.00988 0.0023 1.0000 1.0000
1.250 0.0123 0.02084 0.01028 0.0025 1.0000 1.0000
1.500 0.0305 0.02135 0.01075 0.0025 1.0000 1.0000
1.750 0.0485 0.02192 0.01129 0.0025 1.0000 1.0000
2.000 0.0664 0.02255 0.01189 0.0025 1.0000 1.0000
2.250 0.1235 0.02403 0.01342 -0.0049 0.9827 1.0000
2.500 0.1858 0.02533 0.01485 -0.0128 0.9579 1.0000
2.750 0.2429 0.02637 0.01602 -0.0192 0.9329 1.0000
3.000 0.2988 0.02725 0.01706 -0.0249 0.9095 1.0000
3.250 0.3548 0.02791 0.01797 -0.0301 0.8855 1.0000
3.500 0.4030 0.02837 0.01866 -0.0336 0.8597 1.0000
3.750 0.4590 0.02852 0.01914 -0.0377 0.8321 1.0000
4.000 0.5175 0.02822 0.01919 -0.0410 0.8029 1.0000
4.250 0.5728 0.02735 0.01867 -0.0423 0.7719 1.0000
4.500 0.6089 0.02660 0.01821 -0.0405 0.7353 1.0000
4.750 0.6463 0.02536 0.01719 -0.0379 0.6959 1.0000
5.000 0.6767 0.02420 0.01615 -0.0342 0.6503 1.0000
5.250 0.7032 0.02328 0.01521 -0.0303 0.5983 1.0000
5.500 0.7252 0.02287 0.01470 -0.0265 0.5384 1.0000
5.750 0.7456 0.02299 0.01447 -0.0231 0.4752 1.0000
6.000 0.7630 0.02386 0.01499 -0.0202 0.4093 1.0000
6.250 0.7810 0.02524 0.01591 -0.0178 0.3473 1.0000
6.500 0.7996 0.02700 0.01726 -0.0158 0.2919 1.0000
6.750 0.8192 0.02903 0.01916 -0.0142 0.2469 1.0000
7.000 0.8403 0.03117 0.02127 -0.0128 0.2125 1.0000
7.250 0.8600 0.03312 0.02319 -0.0114 0.1839 1.0000
7.500 0.8807 0.03557 0.02575 -0.0102 0.1627 1.0000
7.750 0.8995 0.03800 0.02837 -0.0087 0.1443 1.0000
8.000 0.9170 0.04119 0.03188 -0.0073 0.1322 1.0000
8.250 0.9313 0.04425 0.03522 -0.0058 0.1207 1.0000
8.500 0.9486 0.04784 0.03898 -0.0046 0.1138 1.0000
8.750 0.9522 0.05215 0.04386 -0.0026 0.1100 1.0000
9.000 0.9499 0.05639 0.04866 -0.0007 0.1067 1.0000
9.250 0.9467 0.06068 0.05334 0.0009 0.1043 1.0000
9.500 0.9348 0.06569 0.05872 0.0022 0.1049 1.0000
9.750 0.9156 0.07084 0.06414 0.0030 0.1068 1.0000
10.000 0.8934 0.07577 0.06923 0.0035 0.1084 1.0000
10.250 0.8741 0.08088 0.07440 0.0030 0.1100 1.0000
10.500 0.8594 0.08663 0.08018 0.0015 0.1114 1.0000
10.750 0.8077 0.09914 0.09271 -0.0086 0.1271 1.0000
11.000 0.8097 0.10460 0.09813 -0.0096 0.1257 1.0000
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Polar data table (+)
Polar graphs
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