HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 500,000 Max Cl/Cd: 85.43 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3014-il-500000-n5.txt Download as CSV file: xf-hq3014-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/14 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5638 0.12631 0.12362 -0.0394 1.0000 0.0086
-15.750 -0.6414 0.10546 0.10258 -0.0495 1.0000 0.0085
-15.500 -0.6925 0.09162 0.08863 -0.0568 1.0000 0.0083
-15.250 -0.7470 0.07746 0.07429 -0.0647 1.0000 0.0081
-15.000 -0.7873 0.06581 0.06245 -0.0719 1.0000 0.0080
-14.750 -0.8140 0.05717 0.05362 -0.0777 1.0000 0.0080
-14.500 -0.8337 0.05078 0.04706 -0.0817 1.0000 0.0080
-14.250 -0.8476 0.04589 0.04203 -0.0845 1.0000 0.0080
-14.000 -0.8584 0.04185 0.03785 -0.0863 1.0000 0.0080
-13.750 -0.8660 0.03855 0.03443 -0.0873 1.0000 0.0081
-13.500 -0.8708 0.03587 0.03163 -0.0876 1.0000 0.0082
-13.250 -0.8766 0.03344 0.02909 -0.0872 1.0000 0.0082
-13.000 -0.8816 0.03150 0.02706 -0.0861 1.0000 0.0084
-12.500 -0.8588 0.02766 0.02294 -0.0890 0.9850 0.0086
-12.250 -0.8385 0.02587 0.02099 -0.0915 0.9764 0.0088
-12.000 -0.8158 0.02426 0.01924 -0.0936 0.9683 0.0090
-11.750 -0.7924 0.02290 0.01777 -0.0951 0.9587 0.0093
-11.500 -0.7682 0.02180 0.01656 -0.0962 0.9487 0.0096
-11.250 -0.7439 0.02084 0.01549 -0.0969 0.9387 0.0098
-11.000 -0.7217 0.02000 0.01453 -0.0970 0.9275 0.0101
-10.750 -0.7008 0.01924 0.01363 -0.0966 0.9166 0.0104
-10.500 -0.6798 0.01856 0.01283 -0.0961 0.9070 0.0107
-10.250 -0.6590 0.01793 0.01207 -0.0954 0.8979 0.0110
-10.000 -0.6379 0.01735 0.01138 -0.0947 0.8897 0.0113
-9.750 -0.6170 0.01671 0.01065 -0.0940 0.8816 0.0118
-9.500 -0.5952 0.01615 0.01001 -0.0933 0.8741 0.0124
-9.250 -0.5726 0.01565 0.00943 -0.0927 0.8673 0.0133
-9.000 -0.5494 0.01519 0.00888 -0.0922 0.8610 0.0144
-8.750 -0.5262 0.01472 0.00838 -0.0917 0.8544 0.0159
-8.500 -0.5021 0.01433 0.00793 -0.0912 0.8488 0.0180
-8.250 -0.4775 0.01397 0.00756 -0.0909 0.8428 0.0208
-8.000 -0.4524 0.01366 0.00719 -0.0905 0.8371 0.0234
-7.750 -0.4270 0.01338 0.00687 -0.0902 0.8318 0.0260
-7.500 -0.4012 0.01313 0.00655 -0.0900 0.8260 0.0281
-7.250 -0.3758 0.01283 0.00622 -0.0897 0.8206 0.0303
-7.000 -0.3498 0.01258 0.00592 -0.0895 0.8155 0.0324
-6.750 -0.3236 0.01234 0.00564 -0.0893 0.8098 0.0342
-6.500 -0.2975 0.01209 0.00533 -0.0891 0.8047 0.0361
-6.250 -0.2712 0.01184 0.00508 -0.0889 0.7996 0.0389
-6.000 -0.2445 0.01166 0.00486 -0.0888 0.7940 0.0419
-5.750 -0.2181 0.01143 0.00460 -0.0886 0.7890 0.0454
-5.500 -0.1914 0.01121 0.00438 -0.0885 0.7840 0.0491
-5.250 -0.1644 0.01102 0.00414 -0.0884 0.7785 0.0520
-5.000 -0.1376 0.01080 0.00387 -0.0882 0.7735 0.0554
-4.750 -0.1107 0.01059 0.00366 -0.0881 0.7685 0.0599
-4.500 -0.0835 0.01042 0.00346 -0.0880 0.7630 0.0643
-4.250 -0.0565 0.01023 0.00325 -0.0879 0.7580 0.0714
-4.000 -0.0291 0.01006 0.00308 -0.0878 0.7528 0.0796
-3.750 -0.0019 0.00987 0.00292 -0.0878 0.7472 0.0920
-3.500 0.0250 0.00967 0.00274 -0.0877 0.7420 0.1113
-3.250 0.0518 0.00941 0.00259 -0.0876 0.7359 0.1419
-3.000 0.0784 0.00912 0.00244 -0.0876 0.7296 0.1866
-2.750 0.1052 0.00888 0.00230 -0.0875 0.7239 0.2296
-2.500 0.1319 0.00858 0.00216 -0.0875 0.7179 0.2828
-2.250 0.1569 0.00804 0.00200 -0.0873 0.7126 0.3992
-2.000 0.1835 0.00780 0.00197 -0.0872 0.7073 0.4740
-1.750 0.2112 0.00772 0.00196 -0.0871 0.7016 0.5066
-1.500 0.2389 0.00770 0.00193 -0.0871 0.6963 0.5261
-1.250 0.2668 0.00766 0.00194 -0.0870 0.6906 0.5503
-1.000 0.2942 0.00764 0.00197 -0.0868 0.6838 0.5787
-0.750 0.3218 0.00765 0.00198 -0.0867 0.6763 0.5955
-0.500 0.3495 0.00768 0.00197 -0.0866 0.6675 0.6042
-0.250 0.3773 0.00770 0.00197 -0.0865 0.6590 0.6121
0.000 0.4048 0.00775 0.00198 -0.0864 0.6507 0.6201
0.250 0.4326 0.00777 0.00200 -0.0863 0.6422 0.6296
0.750 0.4878 0.00786 0.00206 -0.0861 0.6264 0.6477
1.000 0.5150 0.00791 0.00210 -0.0860 0.6180 0.6537
1.250 0.5425 0.00796 0.00213 -0.0858 0.6080 0.6596
1.500 0.5697 0.00802 0.00217 -0.0857 0.5969 0.6649
1.750 0.5961 0.00811 0.00222 -0.0854 0.5824 0.6703
2.000 0.6223 0.00821 0.00228 -0.0850 0.5667 0.6764
2.250 0.6484 0.00832 0.00235 -0.0847 0.5520 0.6822
2.500 0.6743 0.00844 0.00244 -0.0843 0.5364 0.6884
2.750 0.6998 0.00859 0.00253 -0.0839 0.5192 0.6947
3.000 0.7250 0.00874 0.00265 -0.0834 0.5025 0.7006
3.250 0.7495 0.00894 0.00278 -0.0828 0.4831 0.7075
3.500 0.7738 0.00914 0.00292 -0.0821 0.4630 0.7140
3.750 0.7976 0.00937 0.00310 -0.0814 0.4424 0.7208
4.000 0.8207 0.00964 0.00328 -0.0806 0.4207 0.7278
4.250 0.8440 0.00988 0.00348 -0.0798 0.4003 0.7350
4.750 0.8889 0.01045 0.00392 -0.0780 0.3561 0.7500
5.000 0.9112 0.01075 0.00415 -0.0771 0.3354 0.7583
5.500 0.9537 0.01138 0.00468 -0.0750 0.2981 0.7752
5.750 0.9749 0.01167 0.00495 -0.0739 0.2838 0.7844
6.000 0.9961 0.01195 0.00522 -0.0728 0.2706 0.7939
6.500 1.0375 0.01249 0.00578 -0.0704 0.2475 0.8168
6.750 1.0569 0.01276 0.00607 -0.0690 0.2365 0.8307
7.000 1.0749 0.01303 0.00636 -0.0673 0.2247 0.8489
7.250 1.0906 0.01322 0.00664 -0.0651 0.2136 0.8803
7.500 1.1203 0.01352 0.00702 -0.0660 0.2007 1.0000
7.750 1.1373 0.01392 0.00737 -0.0643 0.1901 1.0000
8.000 1.1532 0.01438 0.00777 -0.0624 0.1782 1.0000
8.250 1.1686 0.01487 0.00821 -0.0606 0.1660 1.0000
8.500 1.1851 0.01533 0.00864 -0.0590 0.1559 1.0000
8.750 1.2011 0.01581 0.00911 -0.0573 0.1472 1.0000
9.000 1.2165 0.01635 0.00961 -0.0557 0.1385 1.0000
9.250 1.2329 0.01685 0.01011 -0.0542 0.1309 1.0000
9.500 1.2470 0.01748 0.01071 -0.0524 0.1211 1.0000
9.750 1.2598 0.01820 0.01137 -0.0506 0.1094 1.0000
10.000 1.2721 0.01896 0.01208 -0.0488 0.0979 1.0000
10.250 1.2843 0.01977 0.01284 -0.0471 0.0868 1.0000
10.500 1.2976 0.02052 0.01359 -0.0456 0.0801 1.0000
10.750 1.3089 0.02143 0.01448 -0.0439 0.0716 1.0000
11.000 1.3212 0.02230 0.01535 -0.0424 0.0650 1.0000
11.250 1.3320 0.02329 0.01632 -0.0408 0.0581 1.0000
11.500 1.3423 0.02435 0.01737 -0.0393 0.0521 1.0000
11.750 1.3537 0.02535 0.01839 -0.0379 0.0478 1.0000
12.000 1.3639 0.02647 0.01953 -0.0366 0.0436 1.0000
12.250 1.3734 0.02767 0.02075 -0.0352 0.0392 1.0000
12.500 1.3826 0.02892 0.02202 -0.0339 0.0356 1.0000
12.750 1.3900 0.03034 0.02345 -0.0326 0.0312 1.0000
13.000 1.3981 0.03175 0.02489 -0.0315 0.0282 1.0000
13.250 1.4051 0.03328 0.02644 -0.0303 0.0246 1.0000
13.500 1.4104 0.03499 0.02817 -0.0292 0.0212 1.0000
13.750 1.4156 0.03677 0.02999 -0.0282 0.0176 1.0000
14.000 1.4200 0.03868 0.03194 -0.0273 0.0148 1.0000
14.250 1.4234 0.04074 0.03404 -0.0265 0.0123 1.0000
14.500 1.4232 0.04323 0.03657 -0.0257 0.0077 1.0000
14.750 1.4216 0.04597 0.03935 -0.0251 0.0056 1.0000
15.000 1.4224 0.04857 0.04202 -0.0247 0.0051 1.0000
15.250 1.4222 0.05135 0.04490 -0.0245 0.0047 1.0000
15.500 1.4215 0.05432 0.04796 -0.0244 0.0043 1.0000
15.750 1.4235 0.05705 0.05078 -0.0245 0.0043 1.0000
16.000 1.4221 0.06027 0.05412 -0.0248 0.0041 1.0000
16.250 1.4210 0.06357 0.05752 -0.0253 0.0040 1.0000
16.500 1.4178 0.06726 0.06134 -0.0259 0.0039 1.0000
16.750 1.4155 0.07092 0.06512 -0.0268 0.0038 1.0000
17.000 1.4103 0.07513 0.06946 -0.0279 0.0038 1.0000
17.250 1.4052 0.07943 0.07387 -0.0292 0.0037 1.0000
17.500 1.3988 0.08405 0.07863 -0.0307 0.0037 1.0000
17.750 1.3914 0.08897 0.08368 -0.0325 0.0036 1.0000
18.000 1.3796 0.09472 0.08957 -0.0348 0.0035 1.0000
18.250 1.3702 0.10020 0.09518 -0.0371 0.0035 1.0000
18.500 1.3602 0.10594 0.10105 -0.0397 0.0035 1.0000
18.750 1.3493 0.11191 0.10715 -0.0425 0.0035 1.0000
19.000 1.3384 0.11799 0.11336 -0.0454 0.0035 1.0000
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