HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 50,000 Max Cl/Cd: 33.47 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3512-il-50000.txt Download as CSV file: xf-hq3512-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3302 0.10373 0.09753 -0.0269 1.0000 0.2677
-8.000 -0.3394 0.10196 0.09588 -0.0246 1.0000 0.2775
-7.750 -0.3637 0.10198 0.09606 -0.0216 1.0000 0.2873
-7.500 -0.3648 0.09977 0.09393 -0.0186 1.0000 0.3016
-7.250 -0.3685 0.09784 0.09208 -0.0155 1.0000 0.3160
-7.000 -0.3798 0.09655 0.09090 -0.0119 1.0000 0.3314
-6.750 -0.3892 0.09511 0.08956 -0.0084 1.0000 0.3464
-6.500 -0.4001 0.09381 0.08836 -0.0046 1.0000 0.3614
-6.250 -0.3815 0.09022 0.08476 -0.0020 1.0000 0.3854
-6.000 -0.3923 0.08897 0.08360 0.0019 1.0000 0.4030
-5.750 -0.4138 0.08846 0.08322 0.0068 1.0000 0.4205
-5.500 -0.3999 0.08516 0.07994 0.0092 1.0000 0.4427
-5.250 -0.4159 0.08437 0.07925 0.0141 1.0000 0.4643
-4.750 -0.4399 0.05428 0.04753 -0.0444 1.0000 0.1533
-4.500 -0.4128 0.04893 0.04154 -0.0473 1.0000 0.1381
-4.250 -0.3895 0.04505 0.03736 -0.0482 1.0000 0.1330
-4.000 -0.3615 0.04139 0.03304 -0.0497 1.0000 0.1298
-3.750 -0.3356 0.03888 0.02999 -0.0503 1.0000 0.1349
-3.500 -0.3073 0.03660 0.02697 -0.0508 1.0000 0.1395
-3.250 -0.2844 0.03469 0.02498 -0.0506 1.0000 0.1507
-3.000 -0.2604 0.03310 0.02319 -0.0503 1.0000 0.1635
-2.750 -0.2363 0.03173 0.02163 -0.0497 1.0000 0.1751
-2.500 -0.2137 0.03074 0.02057 -0.0489 1.0000 0.1929
-2.250 -0.1915 0.02987 0.01963 -0.0479 1.0000 0.2093
-2.000 -0.1685 0.02910 0.01895 -0.0473 1.0000 0.2392
-1.750 -0.1413 0.02798 0.01826 -0.0476 1.0000 0.2999
-1.500 -0.1397 0.02680 0.01944 -0.0394 1.0000 0.7302
-1.250 -0.1472 0.02668 0.01948 -0.0301 1.0000 0.8418
-1.000 -0.1329 0.02585 0.01874 -0.0271 1.0000 1.0000
-0.750 -0.1070 0.02628 0.01870 -0.0289 1.0000 1.0000
-0.500 -0.0813 0.02681 0.01884 -0.0306 1.0000 1.0000
-0.250 -0.0564 0.02741 0.01911 -0.0322 1.0000 1.0000
0.000 -0.0323 0.02808 0.01947 -0.0335 1.0000 1.0000
0.250 -0.0089 0.02881 0.01993 -0.0347 1.0000 1.0000
0.500 0.0135 0.02959 0.02047 -0.0357 1.0000 1.0000
0.750 0.0586 0.03118 0.02177 -0.0408 0.9884 1.0000
1.000 0.1047 0.03280 0.02314 -0.0460 0.9743 1.0000
1.250 0.1461 0.03423 0.02438 -0.0502 0.9606 1.0000
1.500 0.1850 0.03557 0.02554 -0.0538 0.9467 1.0000
1.750 0.2238 0.03688 0.02671 -0.0573 0.9317 1.0000
2.000 0.2651 0.03818 0.02787 -0.0609 0.9151 1.0000
2.250 0.3084 0.03931 0.02891 -0.0645 0.8945 1.0000
2.500 0.3496 0.04020 0.02973 -0.0673 0.8727 1.0000
2.750 0.3992 0.04110 0.03056 -0.0712 0.8528 1.0000
3.000 0.4281 0.04181 0.03125 -0.0720 0.8332 1.0000
3.250 0.4649 0.04252 0.03195 -0.0738 0.8148 1.0000
3.500 0.5064 0.04311 0.03255 -0.0760 0.7972 1.0000
3.750 0.5472 0.04355 0.03301 -0.0778 0.7795 1.0000
4.000 0.5724 0.04413 0.03364 -0.0776 0.7590 1.0000
4.250 0.6115 0.04435 0.03393 -0.0788 0.7406 1.0000
4.500 0.6584 0.04408 0.03375 -0.0805 0.7231 1.0000
4.750 0.6828 0.04451 0.03424 -0.0798 0.7015 1.0000
5.000 0.7239 0.04409 0.03396 -0.0803 0.6826 1.0000
5.250 0.7738 0.04294 0.03294 -0.0812 0.6656 1.0000
5.500 0.8278 0.04119 0.03139 -0.0821 0.6497 1.0000
5.750 0.8490 0.04137 0.03165 -0.0804 0.6268 1.0000
6.000 0.9031 0.03951 0.02996 -0.0812 0.6097 1.0000
6.250 0.9618 0.03722 0.02786 -0.0822 0.5927 1.0000
6.500 0.9986 0.03652 0.02726 -0.0818 0.5724 1.0000
6.750 1.0372 0.03577 0.02663 -0.0815 0.5519 1.0000
7.000 1.0907 0.03427 0.02516 -0.0827 0.5326 1.0000
7.250 1.1075 0.03520 0.02619 -0.0809 0.5122 1.0000
7.500 1.1408 0.03522 0.02627 -0.0806 0.4925 1.0000
7.750 1.1780 0.03520 0.02623 -0.0808 0.4736 1.0000
8.000 1.1949 0.03640 0.02755 -0.0792 0.4554 1.0000
8.250 1.2168 0.03738 0.02863 -0.0780 0.4374 1.0000
8.500 1.2432 0.03818 0.02947 -0.0773 0.4191 1.0000
8.750 1.2739 0.03889 0.03019 -0.0770 0.4004 1.0000
9.000 1.2875 0.04045 0.03192 -0.0751 0.3834 1.0000
9.250 1.3021 0.04195 0.03356 -0.0733 0.3659 1.0000
9.500 1.3190 0.04342 0.03514 -0.0716 0.3486 1.0000
9.750 1.3423 0.04460 0.03635 -0.0706 0.3300 1.0000
10.000 1.3629 0.04612 0.03794 -0.0694 0.3123 1.0000
10.250 1.3711 0.04811 0.04012 -0.0670 0.2964 1.0000
10.500 1.3796 0.05025 0.04243 -0.0647 0.2810 1.0000
10.750 1.3864 0.05241 0.04475 -0.0623 0.2658 1.0000
11.000 1.3918 0.05461 0.04710 -0.0597 0.2509 1.0000
11.250 1.3961 0.05685 0.04948 -0.0572 0.2368 1.0000
11.500 1.3988 0.05893 0.05168 -0.0545 0.2227 1.0000
11.750 1.1254 0.08713 0.08020 -0.0516 0.2752 1.0000
12.000 1.0907 0.09731 0.09035 -0.0548 0.2709 1.0000
12.250 1.3685 0.06673 0.05996 -0.0442 0.1938 1.0000
12.500 1.3327 0.07176 0.06525 -0.0411 0.1932 1.0000
12.750 1.2929 0.07817 0.07185 -0.0397 0.1943 1.0000
13.000 1.2515 0.08600 0.07981 -0.0400 0.1960 1.0000
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Polar data table (+)
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