HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 500,000 Max Cl/Cd: 100.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3514-il-500000.txt Download as CSV file: xf-hq3514-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/14 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3732 0.14580 0.14331 -0.0429 1.0000 0.0240
-14.250 -0.3721 0.14122 0.13875 -0.0442 1.0000 0.0241
-14.000 -0.6949 0.06023 0.05725 -0.0832 1.0000 0.0162
-13.250 -0.7685 0.04261 0.03911 -0.0928 1.0000 0.0162
-13.000 -0.7909 0.03926 0.03564 -0.0921 1.0000 0.0163
-12.750 -0.8133 0.03754 0.03385 -0.0886 1.0000 0.0162
-12.500 -0.8094 0.03419 0.03037 -0.0923 0.9956 0.0166
-12.250 -0.7900 0.03191 0.02797 -0.0964 0.9893 0.0170
-12.000 -0.7654 0.03021 0.02616 -0.0999 0.9843 0.0175
-11.750 -0.7390 0.02864 0.02443 -0.1027 0.9799 0.0183
-11.500 -0.7146 0.02675 0.02230 -0.1050 0.9750 0.0190
-11.250 -0.6861 0.02504 0.02030 -0.1076 0.9717 0.0198
-11.000 -0.6605 0.02353 0.01875 -0.1094 0.9671 0.0208
-10.750 -0.6334 0.02292 0.01810 -0.1103 0.9611 0.0217
-10.500 -0.6048 0.02208 0.01712 -0.1116 0.9565 0.0229
-10.250 -0.5831 0.02150 0.01636 -0.1112 0.9479 0.0239
-10.000 -0.5622 0.02004 0.01478 -0.1111 0.9414 0.0250
-9.750 -0.5417 0.01962 0.01435 -0.1103 0.9326 0.0260
-9.500 -0.5180 0.01911 0.01374 -0.1099 0.9264 0.0272
-9.250 -0.4965 0.01862 0.01312 -0.1091 0.9181 0.0285
-9.000 -0.4751 0.01767 0.01203 -0.1084 0.9114 0.0300
-8.750 -0.4523 0.01729 0.01165 -0.1078 0.9035 0.0313
-8.500 -0.4278 0.01697 0.01126 -0.1074 0.8965 0.0328
-8.250 -0.4038 0.01658 0.01075 -0.1068 0.8887 0.0343
-8.000 -0.3806 0.01581 0.00986 -0.1062 0.8819 0.0359
-7.750 -0.3563 0.01538 0.00942 -0.1058 0.8751 0.0376
-7.500 -0.3310 0.01508 0.00907 -0.1055 0.8688 0.0392
-7.250 -0.3048 0.01482 0.00870 -0.1053 0.8632 0.0411
-7.000 -0.2800 0.01435 0.00816 -0.1048 0.8567 0.0427
-6.750 -0.2560 0.01371 0.00750 -0.1044 0.8508 0.0449
-6.500 -0.2300 0.01347 0.00723 -0.1042 0.8447 0.0471
-6.250 -0.2039 0.01319 0.00688 -0.1039 0.8383 0.0492
-6.000 -0.1771 0.01295 0.00654 -0.1037 0.8333 0.0509
-5.750 -0.1531 0.01230 0.00592 -0.1033 0.8274 0.0543
-5.500 -0.1264 0.01207 0.00566 -0.1031 0.8219 0.0573
-5.250 -0.0991 0.01187 0.00537 -0.1030 0.8173 0.0601
-5.000 -0.0738 0.01140 0.00490 -0.1028 0.8115 0.0641
-4.750 -0.0468 0.01117 0.00467 -0.1026 0.8059 0.0685
-4.500 -0.0190 0.01103 0.00444 -0.1026 0.8011 0.0724
-4.250 0.0071 0.01062 0.00407 -0.1024 0.7954 0.0787
-4.000 0.0347 0.01046 0.00387 -0.1024 0.7907 0.0846
-3.750 0.0622 0.01018 0.00356 -0.1024 0.7865 0.0927
-3.500 0.0896 0.01000 0.00337 -0.1024 0.7814 0.1006
-3.000 0.1429 0.00914 0.00285 -0.1024 0.7702 0.2066
-2.750 0.1683 0.00851 0.00264 -0.1024 0.7640 0.3190
-2.500 0.1936 0.00792 0.00257 -0.1024 0.7589 0.4879
-2.250 0.2217 0.00788 0.00253 -0.1023 0.7539 0.5227
-2.000 0.2493 0.00783 0.00252 -0.1022 0.7476 0.5454
-1.750 0.2775 0.00780 0.00249 -0.1022 0.7425 0.5631
-1.500 0.3059 0.00782 0.00249 -0.1022 0.7382 0.5786
-1.250 0.3340 0.00782 0.00251 -0.1022 0.7333 0.5931
-1.000 0.3623 0.00784 0.00252 -0.1022 0.7286 0.6049
-0.750 0.3907 0.00788 0.00253 -0.1022 0.7240 0.6164
-0.500 0.4187 0.00790 0.00257 -0.1021 0.7183 0.6272
-0.250 0.4467 0.00793 0.00258 -0.1021 0.7124 0.6375
0.000 0.4750 0.00798 0.00261 -0.1020 0.7073 0.6474
0.250 0.5029 0.00801 0.00265 -0.1020 0.7016 0.6575
0.500 0.5308 0.00804 0.00269 -0.1019 0.6962 0.6659
0.750 0.5592 0.00810 0.00271 -0.1020 0.6910 0.6742
1.000 0.5865 0.00810 0.00276 -0.1018 0.6838 0.6819
1.250 0.6143 0.00815 0.00276 -0.1017 0.6765 0.6902
1.500 0.6413 0.00815 0.00281 -0.1015 0.6681 0.6984
1.750 0.6687 0.00820 0.00282 -0.1013 0.6598 0.7068
2.000 0.6955 0.00821 0.00287 -0.1010 0.6504 0.7150
2.250 0.7225 0.00825 0.00291 -0.1008 0.6413 0.7228
2.500 0.7490 0.00829 0.00295 -0.1005 0.6304 0.7307
2.750 0.7753 0.00833 0.00300 -0.1001 0.6177 0.7389
3.000 0.8012 0.00839 0.00306 -0.0997 0.6040 0.7469
3.250 0.8270 0.00846 0.00313 -0.0993 0.5897 0.7551
3.500 0.8520 0.00856 0.00322 -0.0987 0.5724 0.7637
3.750 0.8756 0.00871 0.00331 -0.0979 0.5490 0.7723
4.000 0.8978 0.00893 0.00343 -0.0968 0.5198 0.7811
4.250 0.9196 0.00918 0.00361 -0.0957 0.4935 0.7891
4.500 0.9414 0.00947 0.00381 -0.0946 0.4732 0.7983
4.750 0.9633 0.00973 0.00403 -0.0936 0.4564 0.8073
5.000 0.9854 0.01000 0.00426 -0.0926 0.4408 0.8177
5.250 1.0069 0.01025 0.00450 -0.0915 0.4254 0.8295
5.500 1.0281 0.01048 0.00474 -0.0903 0.4102 0.8428
5.750 1.0490 0.01067 0.00496 -0.0890 0.3939 0.8599
6.000 1.0684 0.01079 0.00516 -0.0874 0.3738 0.8873
6.250 1.0944 0.01102 0.00539 -0.0874 0.3442 1.0000
6.500 1.1132 0.01147 0.00571 -0.0860 0.3231 1.0000
6.750 1.1317 0.01193 0.00607 -0.0846 0.3082 1.0000
7.000 1.1499 0.01234 0.00643 -0.0831 0.2959 1.0000
7.250 1.1664 0.01276 0.00679 -0.0813 0.2843 1.0000
7.500 1.1826 0.01319 0.00718 -0.0794 0.2723 1.0000
7.750 1.2002 0.01358 0.00755 -0.0778 0.2589 1.0000
8.000 1.2172 0.01399 0.00793 -0.0762 0.2448 1.0000
8.250 1.2329 0.01448 0.00835 -0.0744 0.2278 1.0000
8.500 1.2473 0.01504 0.00883 -0.0724 0.2097 1.0000
8.750 1.2611 0.01564 0.00936 -0.0705 0.1950 1.0000
9.000 1.2749 0.01627 0.00994 -0.0686 0.1845 1.0000
9.250 1.2892 0.01688 0.01055 -0.0668 0.1767 1.0000
9.500 1.3016 0.01762 0.01125 -0.0649 0.1695 1.0000
9.750 1.3167 0.01823 0.01189 -0.0633 0.1634 1.0000
10.000 1.3302 0.01895 0.01261 -0.0617 0.1572 1.0000
10.250 1.3434 0.01970 0.01337 -0.0600 0.1512 1.0000
10.500 1.3593 0.02033 0.01403 -0.0588 0.1453 1.0000
10.750 1.3704 0.02124 0.01492 -0.0571 0.1393 1.0000
11.000 1.3877 0.02181 0.01556 -0.0561 0.1341 1.0000
11.250 1.4015 0.02260 0.01637 -0.0548 0.1286 1.0000
11.500 1.4145 0.02347 0.01726 -0.0534 0.1234 1.0000
11.750 1.4298 0.02420 0.01803 -0.0524 0.1168 1.0000
12.000 1.4414 0.02520 0.01902 -0.0510 0.1102 1.0000
12.250 1.4542 0.02614 0.01998 -0.0499 0.1015 1.0000
12.500 1.4645 0.02728 0.02111 -0.0485 0.0911 1.0000
12.750 1.4710 0.02874 0.02250 -0.0470 0.0773 1.0000
13.000 1.4727 0.03061 0.02428 -0.0453 0.0609 1.0000
13.250 1.4727 0.03270 0.02629 -0.0436 0.0491 1.0000
13.500 1.4739 0.03476 0.02834 -0.0421 0.0420 1.0000
13.750 1.4756 0.03687 0.03047 -0.0408 0.0376 1.0000
14.000 1.4785 0.03894 0.03259 -0.0397 0.0340 1.0000
14.250 1.4785 0.04135 0.03505 -0.0387 0.0307 1.0000
14.500 1.4804 0.04367 0.03745 -0.0379 0.0276 1.0000
14.750 1.4783 0.04649 0.04033 -0.0371 0.0247 1.0000
15.000 1.4798 0.04902 0.04293 -0.0366 0.0224 1.0000
15.250 1.4742 0.05246 0.04643 -0.0362 0.0204 1.0000
15.500 1.4754 0.05523 0.04930 -0.0361 0.0188 1.0000
15.750 1.4728 0.05855 0.05269 -0.0361 0.0176 1.0000
16.000 1.4640 0.06278 0.05701 -0.0365 0.0167 1.0000
16.250 1.4616 0.06635 0.06070 -0.0369 0.0159 1.0000
16.500 1.4578 0.07023 0.06469 -0.0376 0.0152 1.0000
16.750 1.4524 0.07447 0.06905 -0.0386 0.0147 1.0000
17.000 1.4458 0.07901 0.07369 -0.0399 0.0142 1.0000
17.250 1.4347 0.08444 0.07924 -0.0416 0.0137 1.0000
17.500 1.4216 0.09034 0.08526 -0.0437 0.0135 1.0000
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