HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/8 AIRFOIL (hq108-il) Reynolds number: 500,000 Max Cl/Cd: 63.85 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq108-il-500000-n5.txt Download as CSV file: xf-hq108-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5746 0.08135 0.07915 -0.0134 1.0000 0.0030
-8.750 -0.5841 0.07481 0.07266 -0.0177 1.0000 0.0028
-8.500 -0.6014 0.06668 0.06458 -0.0256 1.0000 0.0028
-8.250 -0.6173 0.05891 0.05671 -0.0310 1.0000 0.0027
-8.000 -0.6290 0.05029 0.04787 -0.0339 1.0000 0.0025
-7.750 -0.6346 0.04203 0.03930 -0.0347 1.0000 0.0025
-7.500 -0.6359 0.03376 0.03057 -0.0341 1.0000 0.0025
-7.250 -0.6256 0.02934 0.02576 -0.0333 1.0000 0.0027
-7.000 -0.6105 0.02633 0.02241 -0.0323 1.0000 0.0029
-6.750 -0.5935 0.02378 0.01952 -0.0312 1.0000 0.0031
-6.500 -0.5750 0.02167 0.01711 -0.0301 1.0000 0.0033
-6.250 -0.5556 0.01989 0.01506 -0.0289 1.0000 0.0036
-6.000 -0.5337 0.01816 0.01306 -0.0280 0.9991 0.0038
-5.750 -0.5023 0.01676 0.01143 -0.0291 0.9937 0.0042
-5.500 -0.4703 0.01608 0.01062 -0.0303 0.9885 0.0048
-5.250 -0.4370 0.01555 0.00996 -0.0316 0.9836 0.0051
-5.000 -0.4070 0.01386 0.00801 -0.0322 0.9764 0.0052
-4.750 -0.3760 0.01256 0.00654 -0.0330 0.9693 0.0052
-4.500 -0.3455 0.01146 0.00529 -0.0337 0.9604 0.0053
-4.250 -0.3157 0.01059 0.00427 -0.0342 0.9500 0.0055
-4.000 -0.2861 0.00999 0.00353 -0.0346 0.9388 0.0060
-3.750 -0.2573 0.00956 0.00297 -0.0346 0.9267 0.0075
-3.500 -0.2299 0.00912 0.00256 -0.0345 0.9146 0.0227
-3.250 -0.2032 0.00882 0.00227 -0.0343 0.9029 0.0474
-3.000 -0.1776 0.00835 0.00204 -0.0341 0.8914 0.1059
-2.750 -0.1520 0.00790 0.00182 -0.0338 0.8798 0.1789
-2.500 -0.1260 0.00757 0.00163 -0.0336 0.8689 0.2419
-2.250 -0.1002 0.00719 0.00146 -0.0333 0.8582 0.3176
-2.000 -0.0747 0.00679 0.00131 -0.0331 0.8472 0.4130
-1.750 -0.0492 0.00646 0.00120 -0.0327 0.8355 0.5018
-1.500 -0.0236 0.00622 0.00116 -0.0322 0.8240 0.5772
-1.250 0.0027 0.00608 0.00115 -0.0318 0.8133 0.6289
-1.000 0.0291 0.00599 0.00114 -0.0314 0.8018 0.6699
-0.750 0.0558 0.00597 0.00111 -0.0310 0.7877 0.6917
-0.500 0.0826 0.00597 0.00106 -0.0307 0.7723 0.7092
-0.250 0.1094 0.00597 0.00105 -0.0303 0.7578 0.7288
0.000 0.1361 0.00596 0.00105 -0.0300 0.7435 0.7483
0.250 0.1629 0.00596 0.00105 -0.0296 0.7275 0.7651
0.500 0.1898 0.00598 0.00105 -0.0294 0.7103 0.7774
0.750 0.2169 0.00601 0.00107 -0.0291 0.6950 0.7885
1.000 0.2439 0.00604 0.00108 -0.0289 0.6797 0.8002
1.250 0.2707 0.00608 0.00111 -0.0286 0.6637 0.8126
1.500 0.2974 0.00612 0.00115 -0.0283 0.6448 0.8260
1.750 0.3236 0.00618 0.00119 -0.0278 0.6225 0.8405
2.000 0.3493 0.00626 0.00126 -0.0273 0.5900 0.8567
2.250 0.3742 0.00640 0.00133 -0.0266 0.5482 0.8763
2.500 0.3983 0.00663 0.00142 -0.0258 0.4898 0.9016
2.750 0.4255 0.00703 0.00157 -0.0258 0.4104 0.9360
3.000 0.4612 0.00743 0.00175 -0.0278 0.3431 0.9746
3.250 0.4920 0.00787 0.00198 -0.0288 0.2817 1.0000
3.750 0.5429 0.00855 0.00240 -0.0283 0.2124 1.0000
4.000 0.5683 0.00890 0.00263 -0.0280 0.1772 1.0000
4.250 0.5931 0.00937 0.00289 -0.0277 0.1293 1.0000
4.500 0.6180 0.00983 0.00323 -0.0274 0.0939 1.0000
4.750 0.6428 0.01030 0.00357 -0.0270 0.0643 1.0000
5.000 0.6681 0.01070 0.00391 -0.0267 0.0478 1.0000
5.250 0.6935 0.01109 0.00428 -0.0264 0.0352 1.0000
5.500 0.7186 0.01153 0.00470 -0.0260 0.0246 1.0000
5.750 0.7439 0.01193 0.00511 -0.0257 0.0190 1.0000
6.000 0.7684 0.01251 0.00573 -0.0252 0.0142 1.0000
6.250 0.7939 0.01284 0.00611 -0.0249 0.0116 1.0000
6.500 0.8183 0.01338 0.00673 -0.0244 0.0089 1.0000
6.750 0.8415 0.01419 0.00765 -0.0237 0.0066 1.0000
7.000 0.8653 0.01483 0.00839 -0.0231 0.0054 1.0000
7.250 0.8895 0.01535 0.00895 -0.0227 0.0044 1.0000
7.500 0.9112 0.01632 0.01000 -0.0220 0.0033 1.0000
7.750 0.9342 0.01704 0.01084 -0.0213 0.0030 1.0000
8.000 0.9560 0.01798 0.01192 -0.0205 0.0027 1.0000
8.250 0.9770 0.01906 0.01317 -0.0196 0.0025 1.0000
8.500 0.9979 0.02011 0.01436 -0.0188 0.0022 1.0000
8.750 1.0186 0.02114 0.01553 -0.0180 0.0020 1.0000
9.000 1.0381 0.02235 0.01691 -0.0171 0.0018 1.0000
9.250 1.0568 0.02359 0.01837 -0.0161 0.0016 1.0000
9.500 1.0705 0.02564 0.02069 -0.0146 0.0014 1.0000
9.750 1.0756 0.02906 0.02457 -0.0123 0.0013 1.0000
10.250 1.0742 0.03618 0.03252 -0.0073 0.0013 1.0000
10.500 1.0671 0.03934 0.03600 -0.0044 0.0013 1.0000
10.750 1.0509 0.04263 0.03956 -0.0012 0.0012 1.0000
11.000 1.0301 0.04672 0.04388 0.0002 0.0013 1.0000
11.250 1.0114 0.05131 0.04867 -0.0004 0.0013 1.0000
11.500 0.9921 0.05713 0.05468 -0.0033 0.0013 1.0000
11.750 0.9703 0.06509 0.06281 -0.0091 0.0013 1.0000
12.250 0.9501 0.08245 0.08040 -0.0218 0.0013 1.0000
12.500 0.9378 0.09161 0.08960 -0.0268 0.0014 1.0000
12.750 0.9243 0.10034 0.09836 -0.0310 0.0015 1.0000
13.000 0.8217 0.13471 0.13261 -0.0463 0.0017 1.0000
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Polar data table (+)
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