HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 500,000 Max Cl/Cd: 84.76 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq159b-il-500000.txt Download as CSV file: xf-hq159b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.6011 0.03980 0.03681 -0.0445 1.0000 0.0135
-7.500 -0.6044 0.03387 0.03049 -0.0428 1.0000 0.0128
-7.250 -0.6089 0.02665 0.02259 -0.0397 1.0000 0.0119
-7.000 -0.6001 0.02358 0.01912 -0.0372 1.0000 0.0120
-6.750 -0.5879 0.02199 0.01731 -0.0349 1.0000 0.0126
-6.500 -0.5554 0.01923 0.01413 -0.0365 0.9971 0.0130
-6.250 -0.5221 0.01681 0.01136 -0.0381 0.9943 0.0133
-6.000 -0.4890 0.01542 0.00974 -0.0393 0.9906 0.0141
-5.750 -0.4568 0.01345 0.00756 -0.0406 0.9869 0.0154
-5.500 -0.4210 0.01271 0.00677 -0.0426 0.9840 0.0176
-5.250 -0.3853 0.01225 0.00624 -0.0443 0.9808 0.0205
-5.000 -0.3519 0.01146 0.00545 -0.0458 0.9762 0.0268
-4.750 -0.3168 0.01077 0.00470 -0.0475 0.9724 0.0330
-4.500 -0.2803 0.01051 0.00441 -0.0494 0.9692 0.0390
-4.250 -0.2504 0.01002 0.00390 -0.0500 0.9614 0.0457
-4.000 -0.2171 0.00976 0.00361 -0.0511 0.9559 0.0521
-3.750 -0.1897 0.00931 0.00315 -0.0511 0.9459 0.0629
-3.500 -0.1622 0.00896 0.00279 -0.0509 0.9363 0.0789
-3.250 -0.1362 0.00843 0.00245 -0.0506 0.9269 0.1269
-3.000 -0.1129 0.00764 0.00218 -0.0501 0.9157 0.2664
-2.750 -0.0898 0.00686 0.00197 -0.0496 0.9052 0.4358
-2.500 -0.0652 0.00646 0.00186 -0.0489 0.8958 0.5356
-2.250 -0.0397 0.00628 0.00184 -0.0483 0.8864 0.6035
-2.000 -0.0136 0.00621 0.00182 -0.0477 0.8764 0.6453
-1.750 0.0128 0.00619 0.00179 -0.0472 0.8665 0.6736
-1.250 0.0660 0.00617 0.00174 -0.0462 0.8462 0.7148
-1.000 0.0926 0.00615 0.00173 -0.0457 0.8364 0.7328
-0.750 0.1191 0.00615 0.00172 -0.0452 0.8267 0.7507
-0.500 0.1458 0.00613 0.00170 -0.0448 0.8165 0.7657
-0.250 0.1727 0.00612 0.00170 -0.0444 0.8065 0.7797
0.000 0.1995 0.00611 0.00168 -0.0440 0.7965 0.7919
0.250 0.2264 0.00611 0.00165 -0.0436 0.7855 0.8034
0.500 0.2533 0.00609 0.00164 -0.0432 0.7739 0.8152
1.000 0.3069 0.00607 0.00165 -0.0425 0.7536 0.8414
1.250 0.3334 0.00606 0.00167 -0.0420 0.7437 0.8551
1.500 0.3598 0.00603 0.00169 -0.0416 0.7327 0.8697
1.750 0.3857 0.00601 0.00172 -0.0410 0.7215 0.8870
2.000 0.4112 0.00598 0.00175 -0.0403 0.7090 0.9093
2.250 0.4390 0.00597 0.00178 -0.0400 0.6928 0.9391
2.500 0.4763 0.00601 0.00179 -0.0419 0.6682 0.9704
2.750 0.5125 0.00613 0.00179 -0.0438 0.6287 1.0000
3.000 0.5374 0.00634 0.00185 -0.0433 0.5837 1.0000
3.250 0.5619 0.00663 0.00194 -0.0427 0.5302 1.0000
3.500 0.5856 0.00706 0.00210 -0.0420 0.4681 1.0000
3.750 0.6090 0.00757 0.00232 -0.0414 0.4025 1.0000
4.000 0.6318 0.00820 0.00258 -0.0408 0.3198 1.0000
4.250 0.6560 0.00868 0.00287 -0.0403 0.2735 1.0000
4.500 0.6811 0.00907 0.00313 -0.0400 0.2421 1.0000
4.750 0.7062 0.00945 0.00340 -0.0397 0.2116 1.0000
5.000 0.7309 0.00989 0.00368 -0.0393 0.1689 1.0000
5.250 0.7513 0.01093 0.00424 -0.0384 0.0792 1.0000
5.500 0.7738 0.01171 0.00481 -0.0377 0.0438 1.0000
5.750 0.7981 0.01227 0.00537 -0.0371 0.0371 1.0000
6.000 0.8227 0.01273 0.00589 -0.0366 0.0337 1.0000
6.250 0.8461 0.01337 0.00656 -0.0359 0.0301 1.0000
6.500 0.8681 0.01419 0.00749 -0.0350 0.0272 1.0000
6.750 0.8918 0.01475 0.00812 -0.0344 0.0252 1.0000
7.000 0.9147 0.01540 0.00881 -0.0337 0.0225 1.0000
7.250 0.9303 0.01718 0.01069 -0.0320 0.0191 1.0000
7.500 0.9547 0.01761 0.01119 -0.0314 0.0179 1.0000
7.750 0.9768 0.01839 0.01206 -0.0306 0.0162 1.0000
8.000 0.9986 0.01918 0.01292 -0.0298 0.0148 1.0000
8.250 1.0177 0.02045 0.01424 -0.0287 0.0138 1.0000
8.500 1.0337 0.02282 0.01680 -0.0272 0.0126 1.0000
8.750 1.0560 0.02329 0.01739 -0.0264 0.0117 1.0000
9.000 1.0755 0.02456 0.01881 -0.0254 0.0110 1.0000
9.250 1.0942 0.02577 0.02015 -0.0243 0.0104 1.0000
9.500 1.1115 0.02716 0.02168 -0.0231 0.0099 1.0000
9.750 1.1275 0.02848 0.02315 -0.0219 0.0095 1.0000
10.000 1.1401 0.03041 0.02523 -0.0203 0.0092 1.0000
10.250 1.1439 0.03396 0.02911 -0.0180 0.0089 1.0000
10.500 1.1372 0.03853 0.03410 -0.0149 0.0087 1.0000
10.750 1.1267 0.04215 0.03803 -0.0113 0.0087 1.0000
11.000 1.1141 0.04506 0.04117 -0.0078 0.0087 1.0000
11.250 1.0983 0.04835 0.04470 -0.0051 0.0087 1.0000
11.500 1.0763 0.05265 0.04924 -0.0036 0.0087 1.0000
11.750 1.0701 0.05538 0.05211 -0.0033 0.0087 1.0000
12.000 1.0588 0.05912 0.05601 -0.0039 0.0088 1.0000
12.250 1.0360 0.06503 0.06212 -0.0061 0.0088 1.0000
12.500 1.0242 0.06999 0.06721 -0.0087 0.0088 1.0000
12.750 1.0039 0.07723 0.07462 -0.0134 0.0088 1.0000
13.000 0.9946 0.08339 0.08091 -0.0179 0.0089 1.0000
13.250 0.9681 0.09515 0.09290 -0.0265 0.0092 1.0000
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Polar data table (+)
Polar graphs
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