HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 50,000 Max Cl/Cd: 35.79 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2010-il-50000.txt Download as CSV file: xf-hq2010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 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 -0.4139 0.09927 0.09254 -0.0138 1.0000 0.2971
-8.250 -0.4101 0.09621 0.08954 -0.0133 1.0000 0.3118
-8.000 -0.4077 0.09334 0.08673 -0.0127 1.0000 0.3276
-7.750 -0.4168 0.09151 0.08503 -0.0119 1.0000 0.3450
-7.500 -0.3967 0.08750 0.08101 -0.0099 1.0000 0.3701
-6.000 -0.4992 0.05161 0.04447 -0.0418 1.0000 0.1320
-5.750 -0.4888 0.04719 0.03980 -0.0411 1.0000 0.1244
-5.500 -0.4756 0.04307 0.03498 -0.0407 1.0000 0.1173
-5.250 -0.4601 0.03978 0.03121 -0.0398 1.0000 0.1174
-5.000 -0.4422 0.03690 0.02762 -0.0389 1.0000 0.1198
-4.750 -0.4231 0.03400 0.02466 -0.0379 1.0000 0.1239
-4.500 -0.4013 0.03154 0.02179 -0.0369 1.0000 0.1290
-4.250 -0.3800 0.02951 0.01951 -0.0359 1.0000 0.1412
-4.000 -0.3570 0.02753 0.01730 -0.0347 1.0000 0.1537
-3.750 -0.3343 0.02602 0.01553 -0.0335 1.0000 0.1755
-3.500 -0.3122 0.02445 0.01412 -0.0321 1.0000 0.2008
-3.250 -0.2901 0.02293 0.01280 -0.0308 1.0000 0.2410
-3.000 -0.2689 0.02032 0.01145 -0.0298 1.0000 0.3790
-2.750 -0.2793 0.01973 0.01256 -0.0182 1.0000 0.7293
-2.500 -0.2845 0.01983 0.01274 -0.0086 1.0000 0.8230
-2.250 -0.1077 0.02086 0.01263 -0.0276 1.0000 1.0000
-2.000 -0.1205 0.02045 0.01217 -0.0234 1.0000 1.0000
-1.750 -0.1330 0.02000 0.01166 -0.0192 1.0000 1.0000
-1.500 -0.1395 0.01961 0.01115 -0.0158 1.0000 1.0000
-1.250 -0.1312 0.01947 0.01079 -0.0146 1.0000 1.0000
-1.000 -0.1147 0.01952 0.01057 -0.0146 1.0000 1.0000
-0.750 -0.0950 0.01970 0.01049 -0.0148 1.0000 1.0000
-0.500 -0.0742 0.01996 0.01052 -0.0152 1.0000 1.0000
-0.250 -0.0532 0.02028 0.01063 -0.0155 1.0000 1.0000
0.000 -0.0322 0.02066 0.01080 -0.0157 1.0000 1.0000
0.250 -0.0113 0.02109 0.01106 -0.0160 1.0000 1.0000
0.500 0.0092 0.02156 0.01139 -0.0162 1.0000 1.0000
0.750 0.0296 0.02208 0.01178 -0.0163 1.0000 1.0000
1.000 0.0496 0.02265 0.01221 -0.0165 1.0000 1.0000
1.250 0.0693 0.02326 0.01273 -0.0167 1.0000 1.0000
1.500 0.0887 0.02392 0.01332 -0.0168 1.0000 1.0000
1.750 0.1077 0.02463 0.01397 -0.0170 1.0000 1.0000
2.000 0.1537 0.02601 0.01531 -0.0223 0.9865 1.0000
2.250 0.2097 0.02757 0.01686 -0.0291 0.9679 1.0000
2.500 0.2642 0.02877 0.01810 -0.0352 0.9440 1.0000
2.750 0.3159 0.02977 0.01917 -0.0403 0.9198 1.0000
3.000 0.3716 0.03068 0.02018 -0.0457 0.8982 1.0000
3.250 0.4113 0.03133 0.02097 -0.0482 0.8752 1.0000
3.500 0.4586 0.03189 0.02169 -0.0516 0.8529 1.0000
3.750 0.5088 0.03219 0.02217 -0.0549 0.8298 1.0000
4.000 0.5507 0.03236 0.02258 -0.0566 0.8045 1.0000
4.250 0.6002 0.03211 0.02259 -0.0587 0.7787 1.0000
4.500 0.6513 0.03141 0.02216 -0.0601 0.7524 1.0000
4.750 0.6983 0.03040 0.02146 -0.0602 0.7244 1.0000
5.000 0.7423 0.02915 0.02046 -0.0594 0.6940 1.0000
5.250 0.7865 0.02760 0.01912 -0.0580 0.6615 1.0000
5.500 0.8195 0.02668 0.01836 -0.0557 0.6234 1.0000
5.750 0.8509 0.02589 0.01758 -0.0533 0.5827 1.0000
6.000 0.8781 0.02548 0.01710 -0.0507 0.5394 1.0000
6.250 0.9019 0.02545 0.01692 -0.0481 0.4941 1.0000
6.500 0.9226 0.02578 0.01709 -0.0456 0.4472 1.0000
6.750 0.9405 0.02657 0.01765 -0.0430 0.3977 1.0000
7.000 0.9570 0.02780 0.01860 -0.0405 0.3454 1.0000
7.250 0.9731 0.02945 0.01985 -0.0382 0.2922 1.0000
7.500 0.9901 0.03158 0.02176 -0.0363 0.2464 1.0000
7.750 1.0111 0.03389 0.02400 -0.0349 0.2146 1.0000
8.000 1.0301 0.03589 0.02601 -0.0336 0.1908 1.0000
8.250 1.0513 0.03829 0.02865 -0.0324 0.1746 1.0000
8.500 1.0715 0.04106 0.03166 -0.0313 0.1628 1.0000
8.750 1.0884 0.04352 0.03431 -0.0299 0.1507 1.0000
9.000 1.1099 0.04646 0.03726 -0.0292 0.1412 1.0000
9.250 1.1135 0.05054 0.04212 -0.0266 0.1375 1.0000
9.500 1.1332 0.05371 0.04522 -0.0259 0.1281 1.0000
9.750 1.1231 0.05780 0.05007 -0.0227 0.1250 1.0000
10.000 1.1129 0.06234 0.05510 -0.0203 0.1229 1.0000
10.250 1.0986 0.06720 0.06034 -0.0181 0.1225 1.0000
10.500 1.0774 0.07211 0.06554 -0.0163 0.1233 1.0000
10.750 1.0521 0.07684 0.07043 -0.0147 0.1246 1.0000
11.000 1.0276 0.08211 0.07582 -0.0146 0.1259 1.0000
11.250 1.0065 0.08807 0.08185 -0.0157 0.1271 1.0000
11.500 0.9907 0.09464 0.08845 -0.0176 0.1280 1.0000
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Polar data table (+)
Polar graphs
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