HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 50,000 Max Cl/Cd: 39.03 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2590sm-il-50000.txt Download as CSV file: xf-hq2590sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9.0 smoothed by Eppler
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4127 0.10684 0.09976 -0.0195 1.0000 0.2412
-8.750 -0.4353 0.10673 0.09983 -0.0211 1.0000 0.2507
-8.500 -0.4257 0.10311 0.09625 -0.0200 1.0000 0.2650
-8.250 -0.4211 0.10011 0.09328 -0.0191 1.0000 0.2797
-8.000 -0.4046 0.09588 0.08907 -0.0173 1.0000 0.2976
-7.750 -0.3971 0.09322 0.08646 -0.0154 1.0000 0.3215
-7.500 -0.3901 0.09023 0.08353 -0.0136 1.0000 0.3433
-7.250 -0.3919 0.08844 0.08184 -0.0115 1.0000 0.3668
-7.000 -0.3757 0.08492 0.07834 -0.0094 1.0000 0.3911
-6.750 -0.3742 0.08268 0.07618 -0.0069 1.0000 0.4160
-6.500 -0.3846 0.08179 0.07544 -0.0033 1.0000 0.4414
-6.250 -0.3760 0.07920 0.07290 -0.0004 1.0000 0.4709
-6.000 -0.3685 0.07674 0.07048 0.0027 1.0000 0.5006
-5.750 -0.3337 0.07214 0.06583 0.0037 1.0000 0.5395
-4.750 -0.3964 0.04442 0.03646 -0.0464 1.0000 0.1626
-4.500 -0.3701 0.04044 0.03193 -0.0473 1.0000 0.1456
-4.250 -0.3468 0.03729 0.02846 -0.0476 1.0000 0.1416
-4.000 -0.3211 0.03464 0.02532 -0.0479 1.0000 0.1399
-3.750 -0.2941 0.03223 0.02238 -0.0479 1.0000 0.1374
-3.500 -0.2671 0.03019 0.01984 -0.0476 1.0000 0.1361
-3.250 -0.2416 0.02851 0.01787 -0.0470 1.0000 0.1387
-3.000 -0.2158 0.02726 0.01626 -0.0464 1.0000 0.1460
-2.750 -0.1917 0.02578 0.01479 -0.0454 1.0000 0.1539
-2.500 -0.1681 0.02468 0.01354 -0.0440 1.0000 0.1636
-2.250 -0.1450 0.02356 0.01252 -0.0430 1.0000 0.1854
-2.000 -0.1187 0.02221 0.01139 -0.0427 1.0000 0.2260
-1.750 -0.1124 0.01943 0.01150 -0.0361 1.0000 0.7458
-1.500 -0.1108 0.01862 0.01095 -0.0269 1.0000 1.0000
-1.250 -0.0848 0.01873 0.01051 -0.0278 1.0000 1.0000
-1.000 -0.0587 0.01890 0.01025 -0.0288 1.0000 1.0000
-0.750 -0.0329 0.01912 0.01012 -0.0296 1.0000 1.0000
-0.500 -0.0076 0.01939 0.01009 -0.0303 1.0000 1.0000
-0.250 0.0170 0.01969 0.01013 -0.0308 1.0000 1.0000
0.000 0.0412 0.02004 0.01026 -0.0312 1.0000 1.0000
0.250 0.0648 0.02042 0.01045 -0.0315 1.0000 1.0000
0.500 0.0879 0.02084 0.01071 -0.0318 1.0000 1.0000
0.750 0.1106 0.02130 0.01102 -0.0320 1.0000 1.0000
1.000 0.1328 0.02180 0.01141 -0.0322 1.0000 1.0000
1.250 0.1545 0.02235 0.01187 -0.0323 1.0000 1.0000
1.500 0.1757 0.02295 0.01240 -0.0325 1.0000 1.0000
1.750 0.1962 0.02361 0.01302 -0.0326 1.0000 1.0000
2.000 0.2159 0.02435 0.01373 -0.0328 1.0000 1.0000
2.250 0.2348 0.02518 0.01456 -0.0331 1.0000 1.0000
2.500 0.2941 0.02684 0.01627 -0.0408 0.9779 1.0000
2.750 0.3552 0.02830 0.01781 -0.0484 0.9530 1.0000
3.000 0.4166 0.02947 0.01912 -0.0553 0.9269 1.0000
3.250 0.4707 0.03024 0.02005 -0.0605 0.8987 1.0000
3.500 0.5243 0.03076 0.02076 -0.0650 0.8699 1.0000
3.750 0.5777 0.03097 0.02122 -0.0688 0.8407 1.0000
4.000 0.6313 0.03083 0.02133 -0.0720 0.8117 1.0000
4.250 0.6850 0.03030 0.02111 -0.0744 0.7831 1.0000
4.500 0.7334 0.02949 0.02057 -0.0754 0.7545 1.0000
4.750 0.7792 0.02838 0.01971 -0.0752 0.7251 1.0000
5.000 0.8243 0.02683 0.01842 -0.0742 0.6932 1.0000
5.250 0.8564 0.02575 0.01747 -0.0717 0.6546 1.0000
5.500 0.8880 0.02462 0.01639 -0.0690 0.6119 1.0000
5.750 0.9168 0.02390 0.01559 -0.0662 0.5639 1.0000
6.000 0.9403 0.02409 0.01556 -0.0635 0.5092 1.0000
6.250 0.9611 0.02499 0.01611 -0.0608 0.4475 1.0000
6.500 0.9765 0.02647 0.01720 -0.0578 0.3764 1.0000
6.750 0.9906 0.02827 0.01855 -0.0549 0.3068 1.0000
7.000 1.0061 0.02993 0.01982 -0.0525 0.2539 1.0000
7.250 1.0228 0.03159 0.02127 -0.0506 0.2132 1.0000
7.500 1.0432 0.03366 0.02316 -0.0493 0.1821 1.0000
7.750 1.0658 0.03608 0.02560 -0.0482 0.1592 1.0000
8.000 1.0902 0.03884 0.02833 -0.0475 0.1432 1.0000
8.250 1.1108 0.04211 0.03211 -0.0462 0.1341 1.0000
8.500 1.1296 0.04536 0.03558 -0.0451 0.1257 1.0000
8.750 1.1429 0.04879 0.03953 -0.0434 0.1201 1.0000
9.000 1.1590 0.05267 0.04368 -0.0422 0.1169 1.0000
9.250 1.1704 0.05730 0.04857 -0.0409 0.1145 1.0000
9.500 1.1674 0.06163 0.05351 -0.0384 0.1135 1.0000
9.750 1.1596 0.06620 0.05859 -0.0361 0.1129 1.0000
10.000 1.1477 0.07097 0.06375 -0.0341 0.1129 1.0000
10.250 1.1329 0.07587 0.06894 -0.0324 0.1133 1.0000
10.500 1.1174 0.08081 0.07408 -0.0310 0.1139 1.0000
10.750 1.1043 0.08593 0.07932 -0.0301 0.1146 1.0000
11.000 1.0148 0.09629 0.08994 -0.0348 0.1267 1.0000
11.250 1.0057 0.10306 0.09673 -0.0370 0.1281 1.0000
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Polar data table (+)
Polar graphs
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