HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 500,000 Max Cl/Cd: 88.66 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3513-il-500000-n5.txt Download as CSV file: xf-hq3513-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/13 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6309 0.06154 0.05880 -0.0726 1.0000 0.0072
-12.250 -0.6821 0.04601 0.04297 -0.0827 1.0000 0.0070
-12.000 -0.6875 0.03914 0.03581 -0.0915 0.9885 0.0071
-11.750 -0.6828 0.03434 0.03075 -0.0984 0.9783 0.0071
-11.500 -0.6763 0.02992 0.02599 -0.1045 0.9661 0.0072
-11.250 -0.6591 0.02725 0.02305 -0.1074 0.9572 0.0074
-11.000 -0.6419 0.02549 0.02112 -0.1084 0.9462 0.0076
-10.750 -0.6228 0.02409 0.01956 -0.1089 0.9364 0.0077
-10.500 -0.6023 0.02290 0.01821 -0.1092 0.9276 0.0079
-10.250 -0.5836 0.02180 0.01696 -0.1088 0.9180 0.0081
-10.000 -0.5634 0.02083 0.01582 -0.1085 0.9100 0.0083
-9.750 -0.5435 0.01984 0.01466 -0.1080 0.9019 0.0085
-9.500 -0.5227 0.01894 0.01360 -0.1074 0.8948 0.0087
-9.250 -0.5015 0.01810 0.01261 -0.1069 0.8874 0.0088
-9.000 -0.4793 0.01734 0.01171 -0.1064 0.8808 0.0090
-8.750 -0.4566 0.01663 0.01087 -0.1059 0.8739 0.0092
-8.500 -0.4330 0.01601 0.01011 -0.1055 0.8681 0.0094
-8.250 -0.4092 0.01543 0.00943 -0.1051 0.8616 0.0096
-8.000 -0.3853 0.01481 0.00869 -0.1047 0.8557 0.0098
-7.750 -0.3611 0.01422 0.00802 -0.1044 0.8499 0.0102
-7.500 -0.3361 0.01374 0.00746 -0.1041 0.8439 0.0106
-7.250 -0.3106 0.01332 0.00695 -0.1039 0.8385 0.0110
-7.000 -0.2850 0.01292 0.00649 -0.1036 0.8325 0.0115
-6.750 -0.2590 0.01256 0.00603 -0.1034 0.8269 0.0123
-6.500 -0.2329 0.01219 0.00561 -0.1032 0.8216 0.0134
-6.250 -0.2068 0.01183 0.00523 -0.1030 0.8156 0.0152
-6.000 -0.1804 0.01151 0.00489 -0.1029 0.8102 0.0187
-5.750 -0.1536 0.01125 0.00464 -0.1028 0.8048 0.0246
-5.500 -0.1265 0.01106 0.00438 -0.1027 0.7990 0.0283
-5.250 -0.0994 0.01086 0.00415 -0.1026 0.7939 0.0318
-5.000 -0.0720 0.01069 0.00394 -0.1026 0.7883 0.0345
-4.750 -0.0448 0.01049 0.00373 -0.1025 0.7828 0.0383
-4.500 -0.0174 0.01034 0.00354 -0.1025 0.7777 0.0421
-4.250 0.0102 0.01019 0.00335 -0.1024 0.7720 0.0447
-4.000 0.0375 0.01000 0.00315 -0.1024 0.7667 0.0500
-3.750 0.0652 0.00986 0.00298 -0.1024 0.7615 0.0553
-3.500 0.0926 0.00968 0.00281 -0.1024 0.7557 0.0638
-3.250 0.1201 0.00954 0.00265 -0.1023 0.7504 0.0741
-3.000 0.1477 0.00936 0.00251 -0.1024 0.7446 0.0887
-2.750 0.1751 0.00919 0.00237 -0.1023 0.7383 0.1098
-2.500 0.2023 0.00896 0.00224 -0.1023 0.7320 0.1476
-2.250 0.2290 0.00867 0.00211 -0.1023 0.7237 0.2090
-2.000 0.2555 0.00835 0.00197 -0.1023 0.7152 0.2789
-1.750 0.2813 0.00790 0.00185 -0.1022 0.7065 0.3998
-1.500 0.3079 0.00767 0.00183 -0.1021 0.6983 0.4777
-1.000 0.3623 0.00753 0.00185 -0.1018 0.6830 0.5638
-0.750 0.3895 0.00754 0.00188 -0.1016 0.6757 0.5956
-0.500 0.4169 0.00755 0.00194 -0.1014 0.6681 0.6240
-0.250 0.4443 0.00759 0.00196 -0.1012 0.6606 0.6379
0.000 0.4720 0.00762 0.00198 -0.1011 0.6521 0.6482
0.500 0.5267 0.00773 0.00202 -0.1008 0.6333 0.6640
0.750 0.5541 0.00778 0.00204 -0.1007 0.6236 0.6699
1.000 0.5812 0.00785 0.00207 -0.1006 0.6133 0.6754
1.250 0.6081 0.00792 0.00211 -0.1003 0.6016 0.6812
1.500 0.6350 0.00801 0.00216 -0.1001 0.5891 0.6872
1.750 0.6616 0.00809 0.00222 -0.0999 0.5767 0.6927
2.000 0.6880 0.00819 0.00228 -0.0996 0.5629 0.6988
2.250 0.7138 0.00833 0.00237 -0.0992 0.5463 0.7050
2.500 0.7386 0.00850 0.00247 -0.0986 0.5262 0.7110
2.750 0.7634 0.00869 0.00258 -0.0981 0.5040 0.7176
3.000 0.7874 0.00891 0.00272 -0.0974 0.4814 0.7237
3.250 0.8112 0.00915 0.00288 -0.0967 0.4574 0.7306
3.500 0.8343 0.00943 0.00307 -0.0959 0.4319 0.7371
3.750 0.8568 0.00974 0.00328 -0.0950 0.4055 0.7442
4.000 0.8794 0.01005 0.00350 -0.0941 0.3806 0.7514
4.250 0.9016 0.01037 0.00373 -0.0932 0.3551 0.7589
4.500 0.9232 0.01072 0.00398 -0.0922 0.3281 0.7668
4.750 0.9446 0.01107 0.00425 -0.0911 0.3053 0.7752
5.000 0.9662 0.01139 0.00452 -0.0901 0.2884 0.7840
5.250 0.9884 0.01167 0.00477 -0.0892 0.2761 0.7938
5.500 1.0107 0.01190 0.00502 -0.0883 0.2671 0.8044
5.750 1.0321 0.01216 0.00530 -0.0872 0.2588 0.8166
6.000 1.0544 0.01234 0.00554 -0.0863 0.2523 0.8317
6.250 1.0748 0.01256 0.00581 -0.0850 0.2457 0.8522
6.500 1.0950 0.01263 0.00605 -0.0836 0.2398 0.9040
6.750 1.1244 0.01291 0.00636 -0.0843 0.2316 1.0000
7.000 1.1459 0.01319 0.00665 -0.0834 0.2250 1.0000
7.250 1.1660 0.01348 0.00693 -0.0821 0.2184 1.0000
7.500 1.1853 0.01380 0.00725 -0.0808 0.2119 1.0000
7.750 1.2044 0.01412 0.00757 -0.0794 0.2037 1.0000
8.000 1.2230 0.01448 0.00792 -0.0780 0.1957 1.0000
8.250 1.2410 0.01486 0.00829 -0.0765 0.1871 1.0000
8.500 1.2591 0.01525 0.00868 -0.0751 0.1774 1.0000
8.750 1.2756 0.01573 0.00912 -0.0735 0.1653 1.0000
9.000 1.2910 0.01627 0.00961 -0.0718 0.1522 1.0000
9.250 1.3057 0.01686 0.01016 -0.0700 0.1396 1.0000
9.500 1.3190 0.01754 0.01078 -0.0681 0.1259 1.0000
9.750 1.3306 0.01835 0.01151 -0.0661 0.1102 1.0000
10.000 1.3406 0.01928 0.01234 -0.0640 0.0942 1.0000
10.500 1.3606 0.02123 0.01417 -0.0600 0.0679 1.0000
10.750 1.3718 0.02217 0.01510 -0.0582 0.0591 1.0000
11.000 1.3822 0.02319 0.01610 -0.0565 0.0503 1.0000
11.250 1.3903 0.02441 0.01727 -0.0547 0.0399 1.0000
11.500 1.3994 0.02558 0.01843 -0.0530 0.0329 1.0000
11.750 1.4014 0.02732 0.02009 -0.0508 0.0203 1.0000
12.000 1.4081 0.02876 0.02154 -0.0492 0.0149 1.0000
12.250 1.4117 0.03050 0.02329 -0.0474 0.0094 1.0000
12.500 1.4178 0.03209 0.02493 -0.0460 0.0066 1.0000
12.750 1.4246 0.03365 0.02655 -0.0447 0.0056 1.0000
13.000 1.4309 0.03531 0.02828 -0.0435 0.0050 1.0000
13.250 1.4368 0.03706 0.03011 -0.0424 0.0047 1.0000
13.500 1.4412 0.03898 0.03212 -0.0414 0.0043 1.0000
13.750 1.4467 0.04086 0.03409 -0.0406 0.0042 1.0000
14.000 1.4501 0.04301 0.03634 -0.0398 0.0041 1.0000
14.250 1.4537 0.04522 0.03864 -0.0391 0.0040 1.0000
14.500 1.4534 0.04792 0.04147 -0.0385 0.0038 1.0000
14.750 1.4545 0.05058 0.04424 -0.0382 0.0037 1.0000
15.000 1.4531 0.05364 0.04741 -0.0380 0.0036 1.0000
15.250 1.4524 0.05670 0.05060 -0.0380 0.0035 1.0000
15.500 1.4513 0.05993 0.05394 -0.0382 0.0035 1.0000
15.750 1.4480 0.06357 0.05771 -0.0386 0.0034 1.0000
16.000 1.4439 0.06747 0.06174 -0.0393 0.0033 1.0000
16.250 1.4385 0.07169 0.06608 -0.0402 0.0033 1.0000
16.500 1.4324 0.07614 0.07067 -0.0414 0.0032 1.0000
16.750 1.4243 0.08110 0.07576 -0.0430 0.0032 1.0000
17.000 1.4153 0.08638 0.08117 -0.0448 0.0031 1.0000
17.250 1.4047 0.09204 0.08698 -0.0470 0.0031 1.0000
17.500 1.3933 0.09803 0.09311 -0.0495 0.0031 1.0000
17.750 1.3808 0.10439 0.09962 -0.0523 0.0030 1.0000
18.000 1.3683 0.11085 0.10621 -0.0553 0.0030 1.0000
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