HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 200,000 Max Cl/Cd: 75.32 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3513-il-200000-n5.txt Download as CSV file: xf-hq3513-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3740 0.08882 0.08543 -0.0531 0.9982 0.0154
-10.000 -0.3770 0.08069 0.07733 -0.0600 0.9913 0.0152
-9.750 -0.4851 0.04407 0.04017 -0.0960 0.9649 0.0138
-9.500 -0.4916 0.03698 0.03246 -0.1015 0.9525 0.0139
-9.250 -0.4812 0.03279 0.02777 -0.1037 0.9442 0.0142
-9.000 -0.4670 0.02990 0.02448 -0.1043 0.9358 0.0145
-8.750 -0.4466 0.02733 0.02151 -0.1052 0.9297 0.0149
-8.500 -0.4263 0.02535 0.01919 -0.1053 0.9229 0.0154
-8.250 -0.4031 0.02370 0.01722 -0.1054 0.9170 0.0161
-8.000 -0.3772 0.02240 0.01571 -0.1060 0.9123 0.0170
-7.750 -0.3539 0.02176 0.01500 -0.1057 0.9052 0.0180
-7.500 -0.3276 0.02080 0.01389 -0.1059 0.9003 0.0190
-7.250 -0.3039 0.01979 0.01271 -0.1056 0.8942 0.0200
-7.000 -0.2797 0.01883 0.01158 -0.1052 0.8880 0.0213
-6.750 -0.2529 0.01813 0.01081 -0.1053 0.8835 0.0232
-6.500 -0.2297 0.01751 0.01010 -0.1047 0.8764 0.0259
-6.250 -0.2039 0.01687 0.00939 -0.1046 0.8712 0.0295
-6.000 -0.1778 0.01646 0.00887 -0.1044 0.8657 0.0340
-5.750 -0.1525 0.01607 0.00846 -0.1041 0.8596 0.0384
-5.500 -0.1246 0.01583 0.00809 -0.1041 0.8550 0.0437
-5.250 -0.0991 0.01556 0.00783 -0.1040 0.8490 0.0501
-5.000 -0.0721 0.01539 0.00756 -0.1038 0.8433 0.0561
-4.750 -0.0456 0.01484 0.00700 -0.1038 0.8390 0.0609
-4.500 -0.0207 0.01449 0.00659 -0.1034 0.8324 0.0647
-4.250 0.0061 0.01418 0.00619 -0.1032 0.8271 0.0692
-4.000 0.0328 0.01378 0.00579 -0.1031 0.8224 0.0768
-3.750 0.0586 0.01350 0.00547 -0.1028 0.8162 0.0852
-3.500 0.0858 0.01320 0.00514 -0.1028 0.8112 0.0982
-3.250 0.1124 0.01287 0.00487 -0.1027 0.8060 0.1217
-3.000 0.1380 0.01244 0.00465 -0.1026 0.8000 0.1749
-2.750 0.1639 0.01181 0.00437 -0.1027 0.7953 0.2824
-2.500 0.1872 0.01116 0.00434 -0.1023 0.7893 0.4496
-2.250 0.2130 0.01100 0.00438 -0.1018 0.7836 0.5264
-2.000 0.2408 0.01095 0.00434 -0.1015 0.7790 0.5685
-1.750 0.2669 0.01097 0.00437 -0.1011 0.7721 0.5963
-1.500 0.2941 0.01099 0.00438 -0.1007 0.7664 0.6251
-1.250 0.3202 0.01106 0.00447 -0.1000 0.7602 0.6575
-1.000 0.3464 0.01110 0.00452 -0.0994 0.7531 0.6775
-0.750 0.3735 0.01111 0.00448 -0.0990 0.7458 0.6905
-0.500 0.4005 0.01111 0.00442 -0.0986 0.7373 0.7004
-0.250 0.4273 0.01111 0.00437 -0.0983 0.7285 0.7073
0.000 0.4550 0.01110 0.00429 -0.0981 0.7207 0.7141
0.250 0.4817 0.01112 0.00428 -0.0978 0.7118 0.7210
0.500 0.5092 0.01112 0.00423 -0.0976 0.7042 0.7275
0.750 0.5359 0.01115 0.00423 -0.0974 0.6950 0.7349
1.000 0.5626 0.01116 0.00423 -0.0970 0.6865 0.7412
1.250 0.5895 0.01120 0.00421 -0.0967 0.6768 0.7490
1.500 0.6154 0.01122 0.00425 -0.0963 0.6666 0.7554
1.750 0.6422 0.01127 0.00426 -0.0960 0.6576 0.7634
2.000 0.6682 0.01131 0.00431 -0.0956 0.6483 0.7703
2.250 0.6944 0.01136 0.00436 -0.0952 0.6383 0.7787
2.500 0.7202 0.01141 0.00442 -0.0947 0.6275 0.7861
2.750 0.7460 0.01148 0.00447 -0.0943 0.6153 0.7950
3.000 0.7707 0.01153 0.00454 -0.0936 0.6021 0.8034
3.250 0.7954 0.01161 0.00463 -0.0930 0.5884 0.8129
3.500 0.8196 0.01169 0.00471 -0.0922 0.5726 0.8235
3.750 0.8430 0.01179 0.00480 -0.0913 0.5545 0.8349
4.000 0.8662 0.01191 0.00490 -0.0903 0.5338 0.8484
4.250 0.8883 0.01207 0.00503 -0.0892 0.5119 0.8653
4.500 0.9102 0.01223 0.00518 -0.0880 0.4866 0.8920
4.750 0.9392 0.01247 0.00536 -0.0885 0.4573 1.0000
5.000 0.9599 0.01288 0.00564 -0.0874 0.4298 1.0000
5.250 0.9797 0.01334 0.00595 -0.0862 0.4036 1.0000
5.500 0.9989 0.01382 0.00629 -0.0849 0.3784 1.0000
5.750 1.0182 0.01429 0.00666 -0.0836 0.3551 1.0000
6.000 1.0368 0.01479 0.00706 -0.0823 0.3342 1.0000
6.250 1.0553 0.01528 0.00746 -0.0809 0.3167 1.0000
6.500 1.0736 0.01578 0.00789 -0.0795 0.3028 1.0000
6.750 1.0920 0.01626 0.00833 -0.0781 0.2909 1.0000
7.000 1.1102 0.01671 0.00878 -0.0767 0.2815 1.0000
7.250 1.1265 0.01722 0.00925 -0.0749 0.2729 1.0000
7.500 1.1447 0.01768 0.00973 -0.0735 0.2648 1.0000
7.750 1.1612 0.01822 0.01025 -0.0719 0.2574 1.0000
8.000 1.1790 0.01870 0.01078 -0.0705 0.2491 1.0000
8.250 1.1954 0.01925 0.01134 -0.0690 0.2419 1.0000
8.500 1.2130 0.01975 0.01189 -0.0676 0.2342 1.0000
8.750 1.2291 0.02034 0.01249 -0.0661 0.2275 1.0000
9.000 1.2464 0.02086 0.01309 -0.0648 0.2199 1.0000
9.250 1.2617 0.02150 0.01376 -0.0633 0.2133 1.0000
9.500 1.2788 0.02205 0.01441 -0.0620 0.2060 1.0000
9.750 1.2930 0.02274 0.01513 -0.0604 0.1980 1.0000
10.000 1.3073 0.02343 0.01587 -0.0590 0.1880 1.0000
10.250 1.3208 0.02418 0.01666 -0.0575 0.1763 1.0000
10.500 1.3338 0.02501 0.01754 -0.0560 0.1660 1.0000
10.750 1.3450 0.02596 0.01850 -0.0544 0.1542 1.0000
11.000 1.3551 0.02703 0.01956 -0.0529 0.1415 1.0000
11.250 1.3638 0.02823 0.02074 -0.0512 0.1282 1.0000
11.500 1.3712 0.02958 0.02205 -0.0497 0.1148 1.0000
11.750 1.3778 0.03104 0.02348 -0.0481 0.1019 1.0000
12.000 1.3840 0.03258 0.02501 -0.0466 0.0908 1.0000
12.250 1.3903 0.03417 0.02661 -0.0453 0.0811 1.0000
12.500 1.3969 0.03577 0.02828 -0.0440 0.0729 1.0000
12.750 1.4017 0.03758 0.03011 -0.0428 0.0652 1.0000
13.000 1.4045 0.03962 0.03216 -0.0417 0.0571 1.0000
13.250 1.4078 0.04167 0.03426 -0.0406 0.0488 1.0000
13.500 1.4095 0.04394 0.03657 -0.0397 0.0412 1.0000
13.750 1.4098 0.04644 0.03911 -0.0389 0.0346 1.0000
14.000 1.4070 0.04935 0.04204 -0.0382 0.0275 1.0000
14.500 1.3972 0.05604 0.04883 -0.0375 0.0174 1.0000
14.750 1.3925 0.05960 0.05249 -0.0375 0.0148 1.0000
15.000 1.3856 0.06358 0.05657 -0.0379 0.0130 1.0000
15.250 1.3800 0.06758 0.06074 -0.0384 0.0116 1.0000
15.500 1.3734 0.07187 0.06517 -0.0392 0.0108 1.0000
15.750 1.3642 0.07671 0.07014 -0.0405 0.0100 1.0000
16.000 1.3545 0.08185 0.07542 -0.0420 0.0095 1.0000
16.250 1.3456 0.08705 0.08080 -0.0438 0.0092 1.0000
16.500 1.3361 0.09253 0.08645 -0.0458 0.0090 1.0000
16.750 1.3249 0.09849 0.09258 -0.0483 0.0087 1.0000
17.000 1.3131 0.10470 0.09896 -0.0510 0.0085 1.0000
17.250 1.3007 0.11118 0.10561 -0.0541 0.0083 1.0000
17.500 1.2883 0.11779 0.11238 -0.0573 0.0082 1.0000
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