HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.23 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2590sm-il-1000000.txt Download as CSV file: xf-hq2590sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4448 0.08268 0.08105 -0.0364 1.0000 0.0122
-9.000 -0.4630 0.07549 0.07391 -0.0397 1.0000 0.0124
-8.750 -0.4680 0.07252 0.07097 -0.0407 1.0000 0.0127
-8.500 -0.4934 0.06576 0.06428 -0.0436 1.0000 0.0124
-7.750 -0.4820 0.02345 0.02027 -0.0795 0.9821 0.0113
-7.500 -0.4570 0.01919 0.01541 -0.0811 0.9764 0.0119
-7.250 -0.4247 0.01831 0.01433 -0.0824 0.9728 0.0122
-7.000 -0.3984 0.01485 0.01046 -0.0837 0.9674 0.0131
-6.750 -0.3693 0.01446 0.01002 -0.0843 0.9605 0.0137
-6.500 -0.3393 0.01401 0.00951 -0.0850 0.9543 0.0144
-6.250 -0.3124 0.01339 0.00877 -0.0849 0.9452 0.0151
-6.000 -0.2857 0.01270 0.00794 -0.0847 0.9364 0.0157
-5.750 -0.2588 0.01223 0.00735 -0.0845 0.9276 0.0161
-5.500 -0.2345 0.01089 0.00585 -0.0840 0.9180 0.0169
-5.250 -0.2087 0.01026 0.00516 -0.0837 0.9095 0.0178
-5.000 -0.1820 0.00998 0.00484 -0.0835 0.9008 0.0187
-4.750 -0.1552 0.00963 0.00443 -0.0833 0.8928 0.0195
-4.500 -0.1285 0.00926 0.00398 -0.0831 0.8848 0.0202
-4.250 -0.1015 0.00893 0.00359 -0.0829 0.8771 0.0209
-4.000 -0.0744 0.00870 0.00329 -0.0827 0.8696 0.0214
-3.750 -0.0479 0.00811 0.00261 -0.0825 0.8608 0.0233
-3.500 -0.0208 0.00790 0.00235 -0.0823 0.8516 0.0249
-3.250 0.0065 0.00771 0.00211 -0.0821 0.8423 0.0265
-3.000 0.0342 0.00757 0.00191 -0.0820 0.8345 0.0281
-2.750 0.0617 0.00732 0.00163 -0.0819 0.8268 0.0331
-2.500 0.0895 0.00714 0.00145 -0.0818 0.8200 0.0435
-2.250 0.1172 0.00692 0.00131 -0.0818 0.8128 0.0739
-2.000 0.1446 0.00662 0.00120 -0.0819 0.8061 0.1371
-1.750 0.1713 0.00597 0.00104 -0.0821 0.7989 0.3063
-1.500 0.1978 0.00541 0.00097 -0.0822 0.7923 0.4793
-1.250 0.2253 0.00523 0.00095 -0.0821 0.7850 0.5444
-1.000 0.2529 0.00514 0.00095 -0.0820 0.7788 0.5891
-0.750 0.2807 0.00505 0.00097 -0.0819 0.7726 0.6358
-0.500 0.3085 0.00504 0.00099 -0.0818 0.7666 0.6636
-0.250 0.3365 0.00502 0.00101 -0.0817 0.7604 0.6831
0.000 0.3642 0.00502 0.00103 -0.0815 0.7537 0.7082
0.250 0.3919 0.00501 0.00105 -0.0814 0.7472 0.7250
0.500 0.4198 0.00501 0.00106 -0.0813 0.7395 0.7351
0.750 0.4477 0.00502 0.00108 -0.0812 0.7317 0.7446
1.000 0.4754 0.00504 0.00109 -0.0811 0.7228 0.7545
1.250 0.5032 0.00505 0.00112 -0.0810 0.7128 0.7653
1.500 0.5306 0.00506 0.00115 -0.0808 0.7011 0.7767
1.750 0.5577 0.00510 0.00119 -0.0806 0.6850 0.7889
2.000 0.5836 0.00520 0.00122 -0.0801 0.6500 0.8029
2.250 0.6055 0.00562 0.00131 -0.0788 0.5536 0.8189
2.500 0.6274 0.00615 0.00153 -0.0778 0.4723 0.8367
2.750 0.6518 0.00644 0.00169 -0.0771 0.4297 0.8556
3.000 0.6762 0.00665 0.00183 -0.0764 0.3965 0.8765
3.250 0.7004 0.00679 0.00195 -0.0757 0.3730 0.9022
3.500 0.7262 0.00684 0.00206 -0.0751 0.3523 0.9546
3.750 0.7564 0.00708 0.00220 -0.0758 0.3269 1.0000
4.000 0.7830 0.00730 0.00235 -0.0757 0.3057 1.0000
4.250 0.8090 0.00758 0.00251 -0.0754 0.2795 1.0000
4.500 0.8348 0.00788 0.00270 -0.0752 0.2518 1.0000
4.750 0.8596 0.00827 0.00291 -0.0748 0.2143 1.0000
5.000 0.8835 0.00876 0.00319 -0.0742 0.1712 1.0000
5.250 0.9070 0.00930 0.00352 -0.0736 0.1303 1.0000
5.500 0.9310 0.00978 0.00386 -0.0731 0.1010 1.0000
5.750 0.9558 0.01017 0.00416 -0.0727 0.0824 1.0000
6.000 0.9806 0.01056 0.00447 -0.0723 0.0684 1.0000
6.250 1.0056 0.01090 0.00478 -0.0719 0.0579 1.0000
6.500 1.0302 0.01129 0.00511 -0.0714 0.0461 1.0000
6.750 1.0535 0.01184 0.00555 -0.0708 0.0314 1.0000
7.000 1.0777 0.01227 0.00594 -0.0702 0.0266 1.0000
7.250 1.1015 0.01274 0.00645 -0.0696 0.0235 1.0000
7.500 1.1259 0.01311 0.00686 -0.0691 0.0220 1.0000
7.750 1.1496 0.01355 0.00731 -0.0685 0.0204 1.0000
8.000 1.1717 0.01419 0.00799 -0.0676 0.0186 1.0000
8.250 1.1938 0.01478 0.00865 -0.0668 0.0176 1.0000
8.500 1.2174 0.01518 0.00911 -0.0662 0.0169 1.0000
8.750 1.2403 0.01563 0.00958 -0.0655 0.0159 1.0000
9.000 1.2626 0.01613 0.01012 -0.0647 0.0150 1.0000
9.250 1.2820 0.01692 0.01095 -0.0636 0.0139 1.0000
9.500 1.2987 0.01795 0.01209 -0.0619 0.0131 1.0000
9.750 1.3205 0.01840 0.01261 -0.0611 0.0126 1.0000
10.000 1.3412 0.01894 0.01320 -0.0602 0.0120 1.0000
10.250 1.3614 0.01948 0.01379 -0.0592 0.0114 1.0000
10.500 1.3814 0.02000 0.01434 -0.0582 0.0108 1.0000
10.750 1.3962 0.02095 0.01533 -0.0564 0.0101 1.0000
11.000 1.4052 0.02233 0.01684 -0.0539 0.0096 1.0000
11.250 1.4221 0.02283 0.01742 -0.0523 0.0093 1.0000
11.500 1.4341 0.02358 0.01826 -0.0501 0.0090 1.0000
11.750 1.4461 0.02432 0.01907 -0.0479 0.0086 1.0000
12.000 1.4576 0.02509 0.01991 -0.0458 0.0083 1.0000
12.250 1.4674 0.02600 0.02089 -0.0436 0.0080 1.0000
12.500 1.4772 0.02692 0.02188 -0.0416 0.0077 1.0000
12.750 1.4846 0.02806 0.02310 -0.0395 0.0075 1.0000
13.000 1.4870 0.02963 0.02476 -0.0371 0.0073 1.0000
13.250 1.4766 0.03240 0.02770 -0.0339 0.0070 1.0000
13.500 1.4710 0.03495 0.03042 -0.0316 0.0068 1.0000
13.750 1.4783 0.03642 0.03199 -0.0305 0.0067 1.0000
14.000 1.4806 0.03843 0.03412 -0.0293 0.0066 1.0000
14.250 1.4815 0.04068 0.03649 -0.0283 0.0065 1.0000
14.500 1.4821 0.04308 0.03902 -0.0276 0.0064 1.0000
14.750 1.4780 0.04615 0.04222 -0.0271 0.0063 1.0000
15.000 1.4773 0.04898 0.04517 -0.0271 0.0061 1.0000
15.250 1.4693 0.05288 0.04922 -0.0274 0.0061 1.0000
15.500 1.4643 0.05668 0.05314 -0.0282 0.0060 1.0000
15.750 1.4548 0.06141 0.05801 -0.0297 0.0059 1.0000
16.000 1.4461 0.06643 0.06317 -0.0318 0.0058 1.0000
16.250 1.4322 0.07279 0.06968 -0.0348 0.0058 1.0000
16.500 1.4173 0.07979 0.07683 -0.0386 0.0057 1.0000
16.750 1.4013 0.08738 0.08457 -0.0429 0.0057 1.0000
17.000 1.3826 0.09574 0.09308 -0.0477 0.0057 1.0000
17.250 1.3559 0.10595 0.10346 -0.0536 0.0057 1.0000
17.500 1.3353 0.11515 0.11280 -0.0590 0.0057 1.0000
17.750 1.3068 0.12637 0.12419 -0.0657 0.0058 1.0000
18.000 1.2799 0.13775 0.13573 -0.0726 0.0058 1.0000
18.250 1.2530 0.14960 0.14773 -0.0800 0.0059 1.0000
18.500 1.2185 0.16414 0.16245 -0.0890 0.0060 1.0000
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Polar data table (+)
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