HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/9 AIRFOIL (hq109-il) Reynolds number: 500,000 Max Cl/Cd: 79.53 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq109-il-500000.txt Download as CSV file: xf-hq109-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6038 0.16479 0.16236 0.0194 1.0000 0.0114
-13.750 -0.5981 0.16084 0.15841 0.0176 1.0000 0.0121
-7.250 -0.6322 0.03037 0.02636 -0.0338 1.0000 0.0151
-7.000 -0.6251 0.02451 0.02002 -0.0312 1.0000 0.0113
-6.750 -0.6135 0.01980 0.01466 -0.0284 1.0000 0.0104
-6.500 -0.5959 0.01794 0.01256 -0.0266 1.0000 0.0106
-6.250 -0.5780 0.01672 0.01116 -0.0249 1.0000 0.0112
-6.000 -0.5613 0.01567 0.00999 -0.0230 1.0000 0.0119
-5.750 -0.5359 0.01455 0.00874 -0.0228 0.9985 0.0126
-5.500 -0.5003 0.01354 0.00759 -0.0246 0.9950 0.0136
-5.250 -0.4670 0.01229 0.00621 -0.0261 0.9906 0.0157
-5.000 -0.4318 0.01148 0.00535 -0.0279 0.9862 0.0188
-4.750 -0.3947 0.01084 0.00460 -0.0299 0.9830 0.0226
-4.500 -0.3607 0.01007 0.00388 -0.0314 0.9778 0.0404
-4.250 -0.3252 0.00970 0.00352 -0.0332 0.9726 0.0563
-4.000 -0.2899 0.00922 0.00313 -0.0350 0.9678 0.0789
-3.750 -0.2596 0.00866 0.00281 -0.0358 0.9587 0.1342
-3.500 -0.2303 0.00802 0.00250 -0.0365 0.9495 0.2258
-3.250 -0.2034 0.00730 0.00222 -0.0368 0.9396 0.3444
-3.000 -0.1790 0.00670 0.00204 -0.0363 0.9282 0.4730
-2.750 -0.1541 0.00640 0.00195 -0.0356 0.9168 0.5524
-2.500 -0.1283 0.00626 0.00188 -0.0350 0.9060 0.5969
-2.250 -0.1022 0.00619 0.00183 -0.0344 0.8952 0.6300
-2.000 -0.0762 0.00614 0.00179 -0.0338 0.8845 0.6596
-1.750 -0.0500 0.00611 0.00176 -0.0332 0.8738 0.6830
-1.500 -0.0234 0.00609 0.00173 -0.0328 0.8639 0.7059
-1.250 0.0030 0.00608 0.00173 -0.0322 0.8550 0.7269
-1.000 0.0296 0.00608 0.00171 -0.0317 0.8450 0.7430
-0.750 0.0561 0.00607 0.00169 -0.0313 0.8335 0.7583
-0.500 0.0828 0.00606 0.00167 -0.0308 0.8223 0.7722
-0.250 0.1095 0.00606 0.00165 -0.0304 0.8118 0.7851
0.000 0.1361 0.00605 0.00164 -0.0300 0.8005 0.7978
0.250 0.1626 0.00604 0.00162 -0.0295 0.7889 0.8110
0.500 0.1892 0.00602 0.00163 -0.0290 0.7774 0.8250
0.750 0.2158 0.00600 0.00163 -0.0286 0.7660 0.8379
1.000 0.2425 0.00599 0.00163 -0.0282 0.7545 0.8501
1.250 0.2689 0.00598 0.00163 -0.0277 0.7429 0.8632
1.500 0.2951 0.00596 0.00165 -0.0272 0.7305 0.8779
1.750 0.3210 0.00595 0.00167 -0.0266 0.7171 0.8951
2.000 0.3469 0.00593 0.00169 -0.0259 0.7018 0.9152
2.250 0.3756 0.00594 0.00172 -0.0259 0.6835 0.9401
2.500 0.4111 0.00599 0.00177 -0.0274 0.6629 0.9635
2.750 0.4495 0.00609 0.00180 -0.0297 0.6337 0.9831
3.000 0.4880 0.00624 0.00184 -0.0321 0.5935 1.0000
3.250 0.5114 0.00643 0.00192 -0.0313 0.5572 1.0000
3.500 0.5348 0.00673 0.00204 -0.0305 0.5068 1.0000
3.750 0.5578 0.00715 0.00221 -0.0298 0.4441 1.0000
4.000 0.5806 0.00766 0.00243 -0.0290 0.3737 1.0000
4.250 0.6038 0.00820 0.00269 -0.0284 0.3072 1.0000
4.500 0.6277 0.00868 0.00298 -0.0279 0.2622 1.0000
4.750 0.6520 0.00913 0.00328 -0.0275 0.2223 1.0000
5.000 0.6768 0.00953 0.00355 -0.0271 0.1851 1.0000
5.250 0.7009 0.01002 0.00387 -0.0266 0.1433 1.0000
5.500 0.7243 0.01062 0.00427 -0.0261 0.1024 1.0000
5.750 0.7479 0.01120 0.00470 -0.0256 0.0717 1.0000
6.000 0.7715 0.01179 0.00518 -0.0251 0.0500 1.0000
6.250 0.7956 0.01231 0.00568 -0.0245 0.0358 1.0000
6.500 0.8190 0.01298 0.00633 -0.0238 0.0243 1.0000
6.750 0.8411 0.01386 0.00723 -0.0229 0.0159 1.0000
7.000 0.8628 0.01475 0.00816 -0.0220 0.0122 1.0000
7.250 0.8827 0.01592 0.00946 -0.0207 0.0109 1.0000
7.500 0.9047 0.01675 0.01040 -0.0198 0.0101 1.0000
7.750 0.9258 0.01773 0.01152 -0.0188 0.0092 1.0000
8.000 0.9464 0.01876 0.01264 -0.0178 0.0084 1.0000
8.250 0.9658 0.02002 0.01402 -0.0166 0.0081 1.0000
8.500 0.9836 0.02165 0.01578 -0.0153 0.0077 1.0000
8.750 1.0007 0.02355 0.01789 -0.0139 0.0076 1.0000
9.000 1.0168 0.02572 0.02029 -0.0124 0.0076 1.0000
9.250 1.0310 0.02813 0.02300 -0.0108 0.0076 1.0000
9.500 1.0404 0.03151 0.02683 -0.0085 0.0080 1.0000
9.750 1.0213 0.03975 0.03594 -0.0037 0.0094 1.0000
10.000 1.0065 0.04468 0.04126 -0.0005 0.0101 1.0000
10.250 0.9839 0.04865 0.04548 0.0034 0.0105 1.0000
10.500 0.9612 0.05250 0.04952 0.0056 0.0107 1.0000
10.750 0.8854 0.04699 0.04432 0.0064 0.0103 1.0000
11.000 0.8624 0.05277 0.05026 0.0046 0.0104 1.0000
11.250 0.8409 0.05933 0.05696 0.0016 0.0103 1.0000
11.500 0.8175 0.06746 0.06523 -0.0029 0.0103 1.0000
11.750 0.7961 0.07653 0.07442 -0.0085 0.0102 1.0000
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Polar data table (+)
Polar graphs
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