HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 500,000 Max Cl/Cd: 97.08 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3015-il-500000.txt Download as CSV file: xf-hq3015-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6985 0.08704 0.08412 -0.0646 1.0000 0.0148
-15.500 -0.7575 0.07185 0.06861 -0.0743 1.0000 0.0144
-15.250 -0.7861 0.06329 0.05984 -0.0798 1.0000 0.0142
-15.000 -0.8038 0.05732 0.05372 -0.0834 1.0000 0.0143
-14.750 -0.8197 0.05212 0.04836 -0.0861 1.0000 0.0143
-14.500 -0.8262 0.04849 0.04463 -0.0879 1.0000 0.0145
-14.250 -0.8366 0.04464 0.04064 -0.0893 1.0000 0.0145
-14.000 -0.8439 0.04142 0.03730 -0.0901 1.0000 0.0147
-13.750 -0.8475 0.03883 0.03461 -0.0904 1.0000 0.0149
-13.500 -0.8528 0.03630 0.03196 -0.0902 1.0000 0.0150
-13.250 -0.8574 0.03414 0.02969 -0.0893 1.0000 0.0152
-13.000 -0.8635 0.03230 0.02775 -0.0877 1.0000 0.0154
-12.750 -0.8767 0.03098 0.02637 -0.0842 1.0000 0.0155
-12.500 -0.8695 0.02927 0.02452 -0.0847 0.9971 0.0157
-12.250 -0.8458 0.02731 0.02238 -0.0879 0.9909 0.0160
-12.000 -0.8248 0.02506 0.02001 -0.0909 0.9843 0.0166
-11.750 -0.7993 0.02369 0.01856 -0.0930 0.9788 0.0171
-11.500 -0.7701 0.02263 0.01744 -0.0951 0.9738 0.0178
-11.250 -0.7381 0.02158 0.01629 -0.0975 0.9704 0.0187
-11.000 -0.7104 0.02068 0.01524 -0.0987 0.9635 0.0197
-10.750 -0.6834 0.01959 0.01412 -0.1001 0.9569 0.0209
-10.500 -0.6573 0.01905 0.01355 -0.1005 0.9488 0.0224
-10.250 -0.6302 0.01853 0.01289 -0.1009 0.9413 0.0241
-10.000 -0.6122 0.01773 0.01209 -0.1000 0.9310 0.0262
-9.750 -0.5875 0.01736 0.01162 -0.0998 0.9237 0.0286
-9.500 -0.5688 0.01673 0.01095 -0.0987 0.9146 0.0311
-9.250 -0.5442 0.01651 0.01068 -0.0983 0.9079 0.0336
-9.000 -0.5203 0.01636 0.01042 -0.0977 0.9001 0.0356
-8.750 -0.4997 0.01572 0.00975 -0.0969 0.8934 0.0381
-8.500 -0.4763 0.01549 0.00949 -0.0963 0.8861 0.0401
-8.250 -0.4515 0.01527 0.00918 -0.0959 0.8799 0.0420
-8.000 -0.4291 0.01481 0.00866 -0.0952 0.8734 0.0441
-7.750 -0.4058 0.01443 0.00827 -0.0946 0.8670 0.0463
-7.500 -0.3806 0.01419 0.00796 -0.0942 0.8618 0.0484
-7.250 -0.3555 0.01398 0.00771 -0.0938 0.8554 0.0506
-7.000 -0.3310 0.01365 0.00730 -0.0933 0.8497 0.0525
-6.750 -0.3077 0.01316 0.00681 -0.0928 0.8444 0.0559
-6.500 -0.2824 0.01292 0.00654 -0.0924 0.8384 0.0587
-6.250 -0.2565 0.01269 0.00624 -0.0921 0.8331 0.0613
-6.000 -0.2323 0.01225 0.00575 -0.0916 0.8279 0.0642
-5.750 -0.2076 0.01186 0.00537 -0.0912 0.8221 0.0684
-5.500 -0.1813 0.01162 0.00507 -0.0909 0.8172 0.0729
-5.250 -0.1560 0.01127 0.00471 -0.0906 0.8121 0.0797
-5.000 -0.1297 0.01104 0.00447 -0.0903 0.8065 0.0869
-4.750 -0.1038 0.01070 0.00415 -0.0900 0.8016 0.0994
-4.500 -0.0778 0.01038 0.00389 -0.0898 0.7968 0.1186
-4.250 -0.0526 0.00997 0.00365 -0.0896 0.7912 0.1572
-4.000 -0.0272 0.00955 0.00342 -0.0894 0.7862 0.2138
-3.750 -0.0013 0.00919 0.00322 -0.0893 0.7815 0.2710
-3.500 0.0229 0.00862 0.00298 -0.0889 0.7757 0.3517
-3.250 0.0476 0.00818 0.00288 -0.0886 0.7704 0.4644
-3.000 0.0749 0.00808 0.00285 -0.0884 0.7654 0.5087
-2.750 0.1022 0.00802 0.00285 -0.0882 0.7597 0.5379
-2.500 0.1303 0.00801 0.00281 -0.0881 0.7548 0.5581
-2.250 0.1587 0.00804 0.00281 -0.0881 0.7501 0.5740
-2.000 0.1865 0.00803 0.00281 -0.0880 0.7447 0.5866
-1.750 0.2147 0.00803 0.00280 -0.0880 0.7397 0.5974
-1.500 0.2433 0.00809 0.00281 -0.0880 0.7352 0.6106
-1.250 0.2708 0.00811 0.00285 -0.0878 0.7292 0.6248
-1.000 0.2987 0.00815 0.00286 -0.0876 0.7233 0.6370
-0.750 0.3266 0.00816 0.00286 -0.0875 0.7170 0.6445
-0.500 0.3544 0.00816 0.00285 -0.0874 0.7099 0.6521
-0.250 0.3826 0.00819 0.00281 -0.0874 0.7036 0.6587
0.000 0.4101 0.00818 0.00284 -0.0872 0.6966 0.6653
0.250 0.4382 0.00822 0.00282 -0.0872 0.6904 0.6730
0.500 0.4657 0.00823 0.00287 -0.0870 0.6842 0.6804
0.750 0.4936 0.00828 0.00288 -0.0869 0.6777 0.6882
1.000 0.5214 0.00830 0.00290 -0.0868 0.6717 0.6939
1.250 0.5488 0.00831 0.00294 -0.0867 0.6643 0.7000
1.500 0.5767 0.00837 0.00293 -0.0867 0.6576 0.7059
1.750 0.6036 0.00836 0.00298 -0.0864 0.6492 0.7112
2.000 0.6307 0.00841 0.00299 -0.0862 0.6404 0.7173
2.250 0.6575 0.00843 0.00302 -0.0860 0.6305 0.7231
2.500 0.6842 0.00847 0.00308 -0.0857 0.6217 0.7291
2.750 0.7110 0.00854 0.00312 -0.0854 0.6121 0.7359
3.000 0.7373 0.00856 0.00318 -0.0851 0.6016 0.7418
3.250 0.7634 0.00864 0.00325 -0.0847 0.5910 0.7483
3.500 0.7890 0.00873 0.00331 -0.0843 0.5793 0.7551
3.750 0.8143 0.00880 0.00341 -0.0838 0.5659 0.7618
4.000 0.8393 0.00892 0.00350 -0.0832 0.5510 0.7694
4.250 0.8633 0.00903 0.00361 -0.0824 0.5352 0.7761
4.500 0.8868 0.00921 0.00373 -0.0817 0.5177 0.7843
4.750 0.9096 0.00937 0.00388 -0.0807 0.4988 0.7918
5.250 0.9527 0.00982 0.00424 -0.0784 0.4572 0.8090
5.500 0.9733 0.01008 0.00445 -0.0771 0.4369 0.8187
5.750 0.9930 0.01035 0.00468 -0.0757 0.4150 0.8296
6.000 1.0108 0.01066 0.00494 -0.0739 0.3928 0.8415
6.250 1.0289 0.01093 0.00519 -0.0722 0.3717 0.8555
6.500 1.0453 0.01120 0.00546 -0.0701 0.3513 0.8750
6.750 1.0618 0.01143 0.00576 -0.0680 0.3321 0.9189
7.000 1.0918 0.01187 0.00613 -0.0692 0.3118 1.0000
7.250 1.1075 0.01229 0.00646 -0.0672 0.2970 1.0000
7.750 1.1394 0.01312 0.00719 -0.0635 0.2715 1.0000
8.000 1.1557 0.01354 0.00758 -0.0617 0.2599 1.0000
8.250 1.1710 0.01400 0.00800 -0.0598 0.2486 1.0000
8.500 1.1858 0.01450 0.00845 -0.0580 0.2376 1.0000
8.750 1.2025 0.01495 0.00889 -0.0564 0.2264 1.0000
9.000 1.2175 0.01547 0.00938 -0.0547 0.2147 1.0000
9.250 1.2314 0.01606 0.00993 -0.0529 0.2047 1.0000
9.500 1.2450 0.01669 0.01050 -0.0511 0.1932 1.0000
9.750 1.2604 0.01725 0.01107 -0.0496 0.1847 1.0000
10.000 1.2729 0.01798 0.01177 -0.0478 0.1757 1.0000
10.250 1.2872 0.01864 0.01242 -0.0463 0.1671 1.0000
10.500 1.3004 0.01938 0.01316 -0.0447 0.1597 1.0000
10.750 1.3132 0.02016 0.01392 -0.0432 0.1516 1.0000
11.000 1.3266 0.02094 0.01471 -0.0418 0.1440 1.0000
11.250 1.3381 0.02185 0.01560 -0.0403 0.1361 1.0000
11.500 1.3513 0.02268 0.01644 -0.0390 0.1284 1.0000
11.750 1.3615 0.02373 0.01746 -0.0375 0.1213 1.0000
12.000 1.3747 0.02461 0.01838 -0.0363 0.1149 1.0000
12.250 1.3838 0.02578 0.01952 -0.0349 0.1081 1.0000
12.500 1.3958 0.02678 0.02057 -0.0338 0.1021 1.0000
12.750 1.4038 0.02809 0.02186 -0.0324 0.0953 1.0000
13.000 1.4144 0.02925 0.02305 -0.0313 0.0891 1.0000
13.250 1.4211 0.03073 0.02451 -0.0300 0.0828 1.0000
13.500 1.4304 0.03204 0.02586 -0.0290 0.0774 1.0000
13.750 1.4354 0.03374 0.02754 -0.0279 0.0710 1.0000
14.000 1.4435 0.03522 0.02907 -0.0269 0.0664 1.0000
14.250 1.4478 0.03708 0.03093 -0.0260 0.0614 1.0000
14.500 1.4543 0.03880 0.03270 -0.0252 0.0575 1.0000
14.750 1.4588 0.04075 0.03467 -0.0244 0.0533 1.0000
15.000 1.4619 0.04289 0.03684 -0.0237 0.0502 1.0000
15.250 1.4683 0.04478 0.03881 -0.0232 0.0478 1.0000
15.500 1.4711 0.04707 0.04114 -0.0228 0.0444 1.0000
15.750 1.4722 0.04961 0.04372 -0.0224 0.0420 1.0000
16.000 1.4763 0.05189 0.04607 -0.0222 0.0391 1.0000
16.250 1.4780 0.05450 0.04874 -0.0221 0.0368 1.0000
16.500 1.4763 0.05759 0.05187 -0.0222 0.0341 1.0000
16.750 1.4783 0.06031 0.05468 -0.0224 0.0321 1.0000
17.000 1.4764 0.06357 0.05800 -0.0227 0.0294 1.0000
17.250 1.4735 0.06707 0.06156 -0.0232 0.0274 1.0000
17.500 1.4719 0.07049 0.06507 -0.0238 0.0252 1.0000
17.750 1.4641 0.07485 0.06948 -0.0248 0.0220 1.0000
18.000 1.4577 0.07913 0.07384 -0.0260 0.0193 1.0000
18.250 1.4457 0.08435 0.07911 -0.0276 0.0159 1.0000
18.500 1.4371 0.08923 0.08408 -0.0292 0.0148 1.0000
18.750 1.4265 0.09453 0.08949 -0.0312 0.0132 1.0000
19.000 1.4104 0.10085 0.09590 -0.0337 0.0112 1.0000
19.250 1.4009 0.10622 0.10139 -0.0360 0.0108 1.0000
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