HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/8 AIRFOIL (hq108-il) Reynolds number: 100,000 Max Cl/Cd: 44.7 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq108-il-100000-n5.txt Download as CSV file: xf-hq108-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5583 0.09043 0.08558 -0.0111 1.0000 0.0194
-8.750 -0.5612 0.08521 0.08042 -0.0143 1.0000 0.0189
-8.500 -0.5658 0.07958 0.07487 -0.0182 1.0000 0.0184
-8.250 -0.5743 0.07306 0.06842 -0.0241 1.0000 0.0179
-8.000 -0.5827 0.06696 0.06227 -0.0286 1.0000 0.0175
-7.750 -0.5891 0.06032 0.05547 -0.0319 1.0000 0.0168
-7.500 -0.5901 0.05437 0.04925 -0.0336 1.0000 0.0162
-7.250 -0.5863 0.04927 0.04382 -0.0342 1.0000 0.0159
-7.000 -0.5782 0.04493 0.03911 -0.0341 1.0000 0.0157
-6.750 -0.5680 0.04076 0.03452 -0.0337 1.0000 0.0157
-6.500 -0.5551 0.03691 0.03024 -0.0331 1.0000 0.0157
-6.250 -0.5401 0.03335 0.02622 -0.0322 1.0000 0.0160
-6.000 -0.5229 0.03088 0.02346 -0.0315 1.0000 0.0173
-5.750 -0.5033 0.02914 0.02145 -0.0308 1.0000 0.0196
-5.500 -0.4827 0.02689 0.01879 -0.0296 1.0000 0.0216
-5.250 -0.4611 0.02448 0.01596 -0.0282 1.0000 0.0227
-5.000 -0.4391 0.02246 0.01363 -0.0269 1.0000 0.0239
-4.750 -0.4175 0.02081 0.01178 -0.0255 1.0000 0.0254
-4.500 -0.3980 0.01919 0.01013 -0.0242 1.0000 0.0293
-4.250 -0.3767 0.01838 0.00910 -0.0230 1.0000 0.0369
-4.000 -0.3573 0.01714 0.00786 -0.0216 1.0000 0.0449
-3.750 -0.3370 0.01628 0.00695 -0.0204 1.0000 0.0623
-3.500 -0.3172 0.01540 0.00623 -0.0193 1.0000 0.0934
-3.250 -0.2974 0.01448 0.00559 -0.0183 1.0000 0.1503
-3.000 -0.2790 0.01328 0.00512 -0.0174 1.0000 0.3065
-2.750 -0.2624 0.01231 0.00505 -0.0156 1.0000 0.5194
-2.500 -0.2350 0.01206 0.00510 -0.0153 0.9942 0.6407
-2.250 -0.2033 0.01200 0.00505 -0.0157 0.9862 0.7123
-2.000 -0.1733 0.01197 0.00506 -0.0156 0.9779 0.7705
-1.750 -0.1416 0.01194 0.00504 -0.0158 0.9707 0.8143
-1.500 -0.1094 0.01190 0.00494 -0.0162 0.9628 0.8463
-1.250 -0.0745 0.01186 0.00483 -0.0172 0.9563 0.8799
-1.000 -0.0354 0.01183 0.00473 -0.0192 0.9497 0.9063
-0.750 0.0089 0.01180 0.00462 -0.0226 0.9444 0.9241
-0.500 0.0520 0.01176 0.00452 -0.0258 0.9369 0.9427
-0.250 0.0983 0.01172 0.00439 -0.0297 0.9305 0.9599
0.000 0.1437 0.01165 0.00429 -0.0335 0.9219 0.9767
0.250 0.1885 0.01159 0.00420 -0.0372 0.9129 0.9941
0.500 0.2229 0.01157 0.00415 -0.0388 0.9017 1.0000
0.750 0.2518 0.01158 0.00413 -0.0392 0.8884 1.0000
1.000 0.2789 0.01159 0.00411 -0.0390 0.8725 1.0000
1.250 0.3054 0.01158 0.00408 -0.0384 0.8541 1.0000
1.500 0.3303 0.01159 0.00409 -0.0375 0.8338 1.0000
1.750 0.3549 0.01164 0.00412 -0.0366 0.8145 1.0000
2.000 0.3802 0.01170 0.00419 -0.0358 0.7978 1.0000
2.250 0.4051 0.01178 0.00430 -0.0350 0.7801 1.0000
2.500 0.4301 0.01187 0.00442 -0.0342 0.7611 1.0000
2.750 0.4552 0.01195 0.00460 -0.0333 0.7409 1.0000
3.000 0.4799 0.01205 0.00473 -0.0323 0.7166 1.0000
3.250 0.5042 0.01215 0.00486 -0.0312 0.6868 1.0000
3.500 0.5281 0.01229 0.00498 -0.0300 0.6483 1.0000
3.750 0.5514 0.01249 0.00510 -0.0286 0.5956 1.0000
4.000 0.5735 0.01283 0.00531 -0.0271 0.5222 1.0000
4.250 0.5944 0.01343 0.00555 -0.0256 0.4350 1.0000
4.500 0.6150 0.01421 0.00598 -0.0243 0.3492 1.0000
4.750 0.6358 0.01508 0.00652 -0.0234 0.2742 1.0000
5.000 0.6573 0.01595 0.00717 -0.0226 0.2134 1.0000
5.250 0.6789 0.01688 0.00786 -0.0219 0.1484 1.0000
5.500 0.6997 0.01802 0.00872 -0.0210 0.0971 1.0000
5.750 0.7203 0.01926 0.00979 -0.0201 0.0657 1.0000
6.000 0.7410 0.02060 0.01126 -0.0190 0.0466 1.0000
6.250 0.7616 0.02192 0.01259 -0.0181 0.0321 1.0000
6.500 0.7821 0.02333 0.01414 -0.0170 0.0242 1.0000
6.750 0.8013 0.02508 0.01601 -0.0158 0.0208 1.0000
7.000 0.8202 0.02758 0.01869 -0.0144 0.0191 1.0000
7.250 0.8417 0.02998 0.02141 -0.0132 0.0178 1.0000
7.500 0.8622 0.03219 0.02398 -0.0122 0.0157 1.0000
7.750 0.8807 0.03441 0.02655 -0.0111 0.0141 1.0000
8.000 0.8965 0.03662 0.02906 -0.0101 0.0127 1.0000
8.250 0.9090 0.03979 0.03264 -0.0088 0.0123 1.0000
8.500 0.9174 0.04335 0.03664 -0.0073 0.0121 1.0000
8.750 0.9211 0.04715 0.04087 -0.0058 0.0119 1.0000
9.000 0.9200 0.05115 0.04526 -0.0043 0.0118 1.0000
9.250 0.9142 0.05516 0.04962 -0.0029 0.0118 1.0000
9.500 0.9025 0.05903 0.05377 -0.0015 0.0119 1.0000
9.750 0.8859 0.06307 0.05804 -0.0008 0.0120 1.0000
10.000 0.8666 0.06814 0.06331 -0.0023 0.0122 1.0000
10.250 0.8455 0.07481 0.07014 -0.0066 0.0124 1.0000
10.500 0.8220 0.08475 0.08020 -0.0143 0.0128 1.0000
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Polar data table (+)
Polar graphs
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