HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 200,000 Max Cl/Cd: 88.56 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq359-il-200000.txt Download as CSV file: xf-hq359-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3749 0.08885 0.08578 -0.0284 1.0000 0.0323
-7.250 -0.3913 0.08775 0.08476 -0.0252 1.0000 0.0325
-7.000 -0.4100 0.08668 0.08377 -0.0219 1.0000 0.0326
-6.750 -0.4220 0.08490 0.08205 -0.0205 1.0000 0.0329
-6.500 -0.3973 0.07951 0.07664 -0.0293 0.9950 0.0344
-6.250 -0.3714 0.07357 0.07067 -0.0397 0.9889 0.0362
-6.000 -0.3325 0.06620 0.06315 -0.0554 0.9832 0.0388
-5.750 -0.2929 0.06121 0.05771 -0.0675 0.9752 0.0403
-5.500 -0.2698 0.05325 0.04961 -0.0738 0.9713 0.0414
-5.250 -0.2430 0.04900 0.04540 -0.0772 0.9690 0.0432
-5.000 -0.2222 0.04587 0.04217 -0.0790 0.9620 0.0452
-4.750 -0.1863 0.04199 0.03798 -0.0837 0.9583 0.0494
-4.500 -0.1431 0.03725 0.03263 -0.0895 0.9558 0.0554
-4.250 -0.1215 0.03458 0.02992 -0.0900 0.9490 0.0578
-4.000 -0.0820 0.03210 0.02681 -0.0932 0.9453 0.0685
-3.750 -0.0364 0.02813 0.02217 -0.0942 0.9434 0.0404
-3.500 0.0016 0.02350 0.01717 -0.0970 0.9420 0.0381
-3.250 0.0269 0.02103 0.01433 -0.0962 0.9352 0.0345
-3.000 0.0646 0.01887 0.01178 -0.0974 0.9325 0.0327
-2.750 0.1037 0.01738 0.01011 -0.0993 0.9303 0.0339
-2.500 0.1447 0.01620 0.00884 -0.1015 0.9287 0.0385
-2.250 0.1698 0.01549 0.00814 -0.1010 0.9214 0.0521
-2.000 0.2079 0.01434 0.00713 -0.1032 0.9182 0.1059
-1.750 0.2399 0.01229 0.00698 -0.1048 0.9158 0.6262
-1.500 0.2634 0.01224 0.00701 -0.1034 0.9083 0.7074
-1.250 0.2950 0.01207 0.00688 -0.1034 0.9039 0.7620
-1.000 0.3217 0.01188 0.00675 -0.1022 0.8985 0.8097
-0.750 0.3442 0.01165 0.00658 -0.1002 0.8913 0.8509
-0.500 0.3725 0.01119 0.00616 -0.0990 0.8873 0.8981
-0.250 0.4074 0.01088 0.00588 -0.0999 0.8785 0.9533
0.000 0.4547 0.01049 0.00537 -0.1035 0.8735 1.0000
0.250 0.4832 0.01045 0.00522 -0.1039 0.8635 1.0000
0.500 0.5135 0.01038 0.00505 -0.1043 0.8549 1.0000
0.750 0.5454 0.01022 0.00479 -0.1049 0.8472 1.0000
1.000 0.5728 0.01020 0.00470 -0.1047 0.8367 1.0000
1.250 0.6013 0.01017 0.00462 -0.1046 0.8277 1.0000
1.500 0.6309 0.01011 0.00449 -0.1047 0.8197 1.0000
1.750 0.6575 0.01013 0.00448 -0.1044 0.8090 1.0000
2.000 0.6849 0.01012 0.00444 -0.1041 0.7985 1.0000
2.250 0.7127 0.01011 0.00442 -0.1038 0.7880 1.0000
2.500 0.7405 0.01008 0.00436 -0.1035 0.7767 1.0000
2.750 0.7677 0.01008 0.00433 -0.1031 0.7642 1.0000
3.000 0.7943 0.01010 0.00434 -0.1027 0.7502 1.0000
3.250 0.8202 0.01014 0.00437 -0.1021 0.7341 1.0000
3.500 0.8461 0.01019 0.00445 -0.1014 0.7162 1.0000
3.750 0.8723 0.01025 0.00448 -0.1008 0.6971 1.0000
4.000 0.8973 0.01035 0.00456 -0.1000 0.6737 1.0000
4.250 0.9220 0.01048 0.00465 -0.0992 0.6467 1.0000
4.500 0.9458 0.01068 0.00479 -0.0981 0.6140 1.0000
4.750 0.9681 0.01097 0.00496 -0.0969 0.5714 1.0000
5.000 0.9887 0.01142 0.00519 -0.0954 0.5191 1.0000
5.250 1.0074 0.01205 0.00554 -0.0936 0.4631 1.0000
5.500 1.0259 0.01276 0.00600 -0.0921 0.4132 1.0000
5.750 1.0453 0.01346 0.00654 -0.0907 0.3749 1.0000
6.000 1.0659 0.01409 0.00706 -0.0896 0.3453 1.0000
6.250 1.0869 0.01471 0.00760 -0.0885 0.3227 1.0000
6.500 1.1083 0.01529 0.00816 -0.0876 0.3021 1.0000
6.750 1.1285 0.01590 0.00871 -0.0865 0.2784 1.0000
7.000 1.1479 0.01649 0.00924 -0.0853 0.2512 1.0000
7.250 1.1674 0.01703 0.00974 -0.0841 0.2221 1.0000
7.500 1.1874 0.01757 0.01030 -0.0830 0.1925 1.0000
7.750 1.2044 0.01838 0.01091 -0.0816 0.1420 1.0000
8.000 1.2034 0.02120 0.01276 -0.0779 0.0346 1.0000
8.250 1.2131 0.02294 0.01449 -0.0750 0.0212 1.0000
8.500 1.2186 0.02479 0.01651 -0.0717 0.0179 1.0000
8.750 1.2268 0.02613 0.01800 -0.0687 0.0169 1.0000
9.000 1.2339 0.02760 0.01962 -0.0657 0.0162 1.0000
9.250 1.2405 0.02926 0.02142 -0.0628 0.0155 1.0000
9.500 1.2481 0.03108 0.02337 -0.0602 0.0151 1.0000
9.750 1.2575 0.03309 0.02552 -0.0579 0.0148 1.0000
10.000 1.2698 0.03532 0.02790 -0.0561 0.0146 1.0000
10.250 1.2840 0.03787 0.03072 -0.0545 0.0145 1.0000
10.500 1.2977 0.04078 0.03391 -0.0529 0.0147 1.0000
10.750 1.3073 0.04402 0.03747 -0.0510 0.0149 1.0000
11.000 1.3106 0.04750 0.04129 -0.0487 0.0152 1.0000
11.250 1.3077 0.05113 0.04526 -0.0462 0.0156 1.0000
11.500 1.3000 0.05495 0.04939 -0.0438 0.0159 1.0000
11.750 1.2883 0.05906 0.05380 -0.0418 0.0162 1.0000
12.000 1.2739 0.06343 0.05846 -0.0403 0.0165 1.0000
12.250 1.2579 0.06805 0.06333 -0.0395 0.0167 1.0000
12.500 1.2397 0.07323 0.06875 -0.0396 0.0169 1.0000
12.750 1.2202 0.07889 0.07463 -0.0405 0.0171 1.0000
13.000 1.2003 0.08501 0.08096 -0.0424 0.0172 1.0000
13.250 1.1783 0.09224 0.08837 -0.0452 0.0175 1.0000
13.500 1.0360 0.09796 0.09459 -0.0450 0.0168 1.0000
13.750 1.0085 0.10507 0.10189 -0.0495 0.0169 1.0000
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