HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 200,000 Max Cl/Cd: 73.95 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq258-il-200000-n5.txt Download as CSV file: xf-hq258-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4014 0.09706 0.09356 -0.0305 1.0000 0.0162
-8.500 -0.4065 0.09169 0.08825 -0.0318 1.0000 0.0167
-8.250 -0.4067 0.08791 0.08452 -0.0329 1.0000 0.0168
-8.000 -0.4075 0.08446 0.08112 -0.0340 1.0000 0.0169
-7.750 -0.4106 0.08126 0.07799 -0.0346 1.0000 0.0170
-7.500 -0.4153 0.07797 0.07477 -0.0357 1.0000 0.0170
-7.250 -0.4158 0.07414 0.07100 -0.0385 1.0000 0.0169
-7.000 -0.4153 0.07032 0.06719 -0.0413 1.0000 0.0168
-6.750 -0.4136 0.06728 0.06414 -0.0422 1.0000 0.0165
-6.500 -0.4149 0.06477 0.06165 -0.0402 0.9988 0.0144
-6.250 -0.3916 0.05818 0.05493 -0.0484 0.9923 0.0126
-6.000 -0.3631 0.05123 0.04777 -0.0565 0.9864 0.0111
-5.750 -0.3328 0.04222 0.03833 -0.0634 0.9793 0.0092
-5.500 -0.2991 0.03689 0.03262 -0.0668 0.9751 0.0083
-5.000 -0.2385 0.02929 0.02425 -0.0713 0.9652 0.0079
-4.750 -0.2057 0.02510 0.01949 -0.0735 0.9617 0.0078
-4.500 -0.1758 0.02207 0.01595 -0.0744 0.9563 0.0079
-4.250 -0.1447 0.01946 0.01287 -0.0751 0.9516 0.0080
-4.000 -0.1127 0.01648 0.00940 -0.0760 0.9482 0.0089
-3.750 -0.0838 0.01578 0.00861 -0.0765 0.9423 0.0120
-3.500 -0.0529 0.01469 0.00730 -0.0769 0.9373 0.0143
-3.250 -0.0217 0.01356 0.00601 -0.0775 0.9329 0.0158
-3.000 0.0064 0.01259 0.00493 -0.0775 0.9261 0.0203
-2.750 0.0381 0.01202 0.00431 -0.0783 0.9215 0.0392
-2.500 0.0662 0.01155 0.00389 -0.0784 0.9144 0.0687
-2.250 0.0956 0.01087 0.00353 -0.0791 0.9089 0.1562
-2.000 0.1212 0.00986 0.00329 -0.0794 0.9018 0.3909
-1.750 0.1472 0.00930 0.00323 -0.0790 0.8955 0.5702
-1.500 0.1725 0.00912 0.00323 -0.0781 0.8879 0.6540
-1.250 0.1983 0.00897 0.00321 -0.0772 0.8812 0.7201
-1.000 0.2207 0.00885 0.00322 -0.0755 0.8722 0.7803
-0.750 0.2463 0.00874 0.00311 -0.0746 0.8639 0.8087
-0.500 0.2733 0.00867 0.00295 -0.0742 0.8550 0.8240
-0.250 0.2994 0.00860 0.00286 -0.0736 0.8455 0.8407
0.000 0.3259 0.00853 0.00277 -0.0730 0.8369 0.8600
0.250 0.3533 0.00845 0.00269 -0.0726 0.8278 0.8849
0.500 0.3847 0.00834 0.00259 -0.0731 0.8158 0.9217
0.750 0.4218 0.00826 0.00245 -0.0749 0.8008 1.0000
1.000 0.4488 0.00830 0.00240 -0.0746 0.7862 1.0000
1.250 0.4760 0.00836 0.00240 -0.0744 0.7729 1.0000
1.500 0.5030 0.00843 0.00243 -0.0742 0.7587 1.0000
1.750 0.5298 0.00851 0.00245 -0.0740 0.7427 1.0000
2.000 0.5565 0.00859 0.00248 -0.0736 0.7253 1.0000
2.250 0.5832 0.00870 0.00252 -0.0733 0.7070 1.0000
2.500 0.6096 0.00882 0.00260 -0.0729 0.6868 1.0000
2.750 0.6358 0.00896 0.00272 -0.0725 0.6641 1.0000
3.000 0.6615 0.00914 0.00282 -0.0720 0.6362 1.0000
3.250 0.6867 0.00935 0.00294 -0.0714 0.6025 1.0000
3.500 0.7114 0.00962 0.00310 -0.0707 0.5640 1.0000
3.750 0.7353 0.00997 0.00329 -0.0699 0.5195 1.0000
4.000 0.7584 0.01040 0.00353 -0.0691 0.4696 1.0000
4.250 0.7810 0.01091 0.00391 -0.0682 0.4185 1.0000
4.500 0.8032 0.01148 0.00428 -0.0674 0.3662 1.0000
4.750 0.8233 0.01230 0.00473 -0.0663 0.2919 1.0000
5.000 0.8432 0.01321 0.00523 -0.0654 0.2189 1.0000
5.250 0.8668 0.01373 0.00569 -0.0648 0.1876 1.0000
5.500 0.8869 0.01470 0.00627 -0.0639 0.1194 1.0000
5.750 0.9055 0.01592 0.00705 -0.0629 0.0508 1.0000
6.000 0.9242 0.01725 0.00811 -0.0616 0.0111 1.0000
6.250 0.9467 0.01804 0.00913 -0.0606 0.0078 1.0000
6.500 0.9682 0.01892 0.01015 -0.0597 0.0057 1.0000
6.750 0.9889 0.01996 0.01139 -0.0585 0.0052 1.0000
7.000 1.0073 0.02130 0.01297 -0.0571 0.0048 1.0000
7.250 1.0234 0.02290 0.01479 -0.0554 0.0046 1.0000
7.500 1.0399 0.02450 0.01653 -0.0537 0.0045 1.0000
7.750 1.0567 0.02617 0.01838 -0.0522 0.0044 1.0000
8.000 1.0734 0.02803 0.02043 -0.0506 0.0044 1.0000
8.250 1.0899 0.03009 0.02270 -0.0491 0.0044 1.0000
8.500 1.1054 0.03242 0.02530 -0.0476 0.0043 1.0000
8.750 1.1189 0.03497 0.02814 -0.0458 0.0043 1.0000
9.000 1.1293 0.03777 0.03128 -0.0439 0.0044 1.0000
9.250 1.1359 0.04071 0.03457 -0.0417 0.0044 1.0000
9.500 1.1382 0.04379 0.03808 -0.0392 0.0044 1.0000
9.750 1.1341 0.04687 0.04148 -0.0362 0.0044 1.0000
10.000 1.1254 0.04992 0.04480 -0.0331 0.0044 1.0000
10.250 1.1136 0.05323 0.04837 -0.0305 0.0044 1.0000
10.500 1.0998 0.05698 0.05235 -0.0288 0.0045 1.0000
10.750 1.0844 0.06120 0.05680 -0.0282 0.0045 1.0000
11.000 1.0710 0.06551 0.06134 -0.0286 0.0045 1.0000
11.250 1.0545 0.07073 0.06677 -0.0302 0.0045 1.0000
11.500 1.0411 0.07609 0.07231 -0.0328 0.0046 1.0000
11.750 1.0266 0.08244 0.07882 -0.0366 0.0046 1.0000
12.000 1.0150 0.08906 0.08559 -0.0411 0.0046 1.0000
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Polar data table (+)
Polar graphs
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