HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 500,000 Max Cl/Cd: 105.67 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2590sm-il-500000.txt Download as CSV file: xf-hq2590sm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4303 0.08427 0.08200 -0.0388 1.0000 0.0214
-8.750 -0.4341 0.07953 0.07730 -0.0414 1.0000 0.0215
-8.500 -0.4397 0.07516 0.07298 -0.0437 1.0000 0.0215
-8.250 -0.4543 0.07058 0.06846 -0.0463 1.0000 0.0215
-8.000 -0.4693 0.06637 0.06422 -0.0482 1.0000 0.0215
-7.750 -0.4758 0.06157 0.05933 -0.0506 0.9985 0.0215
-7.500 -0.4665 0.05210 0.04971 -0.0600 0.9932 0.0223
-7.250 -0.4431 0.04885 0.04638 -0.0640 0.9888 0.0229
-7.000 -0.4159 0.04507 0.04245 -0.0688 0.9853 0.0238
-6.750 -0.3874 0.04049 0.03762 -0.0734 0.9814 0.0256
-6.500 -0.3521 0.03737 0.03389 -0.0762 0.9760 0.0283
-6.250 -0.3290 0.02941 0.02560 -0.0810 0.9726 0.0300
-6.000 -0.2959 0.02804 0.02420 -0.0836 0.9706 0.0320
-5.750 -0.2701 0.01776 0.01252 -0.0837 0.9631 0.0229
-5.500 -0.2376 0.01621 0.01079 -0.0849 0.9591 0.0235
-5.250 -0.2041 0.01540 0.00989 -0.0863 0.9559 0.0250
-5.000 -0.1769 0.01442 0.00877 -0.0862 0.9483 0.0261
-4.750 -0.1468 0.01335 0.00756 -0.0865 0.9431 0.0268
-4.500 -0.1191 0.01259 0.00669 -0.0864 0.9363 0.0276
-4.250 -0.0911 0.01211 0.00612 -0.0863 0.9298 0.0283
-4.000 -0.0656 0.01087 0.00482 -0.0860 0.9230 0.0304
-3.750 -0.0390 0.01039 0.00431 -0.0858 0.9158 0.0322
-3.500 -0.0116 0.00999 0.00386 -0.0856 0.9097 0.0341
-3.250 0.0153 0.00967 0.00348 -0.0854 0.9027 0.0363
-3.000 0.0423 0.00922 0.00297 -0.0851 0.8958 0.0406
-2.750 0.0688 0.00897 0.00269 -0.0847 0.8865 0.0473
-2.500 0.0955 0.00855 0.00231 -0.0844 0.8777 0.0711
-2.250 0.1218 0.00790 0.00205 -0.0844 0.8700 0.1894
-2.000 0.1460 0.00678 0.00191 -0.0845 0.8625 0.4916
-1.750 0.1725 0.00656 0.00188 -0.0841 0.8555 0.5744
-1.500 0.1993 0.00647 0.00190 -0.0837 0.8483 0.6239
-1.250 0.2262 0.00644 0.00191 -0.0833 0.8411 0.6657
-1.000 0.2530 0.00642 0.00192 -0.0828 0.8336 0.6959
-0.750 0.2800 0.00639 0.00191 -0.0824 0.8265 0.7169
-0.500 0.3067 0.00638 0.00194 -0.0819 0.8202 0.7424
-0.250 0.3334 0.00636 0.00196 -0.0815 0.8136 0.7647
0.000 0.3607 0.00635 0.00195 -0.0812 0.8075 0.7771
0.250 0.3880 0.00633 0.00196 -0.0809 0.8003 0.7884
0.500 0.4154 0.00634 0.00195 -0.0807 0.7938 0.8003
0.750 0.4424 0.00633 0.00197 -0.0803 0.7859 0.8131
1.000 0.4695 0.00633 0.00198 -0.0800 0.7785 0.8263
1.250 0.4960 0.00631 0.00200 -0.0795 0.7695 0.8404
1.500 0.5224 0.00630 0.00202 -0.0790 0.7605 0.8559
1.750 0.5481 0.00629 0.00204 -0.0784 0.7506 0.8727
2.000 0.5732 0.00624 0.00205 -0.0775 0.7387 0.8930
2.250 0.5974 0.00617 0.00204 -0.0765 0.7252 0.9206
2.500 0.6309 0.00611 0.00200 -0.0775 0.7029 0.9739
2.750 0.6583 0.00623 0.00198 -0.0773 0.6632 1.0000
3.000 0.6826 0.00649 0.00200 -0.0766 0.5977 1.0000
3.250 0.7038 0.00706 0.00216 -0.0754 0.5140 1.0000
3.500 0.7267 0.00759 0.00241 -0.0746 0.4574 1.0000
3.750 0.7512 0.00800 0.00264 -0.0741 0.4185 1.0000
4.000 0.7766 0.00833 0.00285 -0.0737 0.3911 1.0000
4.250 0.8020 0.00865 0.00307 -0.0734 0.3656 1.0000
4.500 0.8270 0.00899 0.00331 -0.0730 0.3374 1.0000
4.750 0.8520 0.00934 0.00354 -0.0726 0.3078 1.0000
5.000 0.8770 0.00968 0.00378 -0.0722 0.2798 1.0000
5.250 0.9013 0.01009 0.00405 -0.0717 0.2437 1.0000
5.500 0.9243 0.01065 0.00439 -0.0711 0.1958 1.0000
5.750 0.9460 0.01137 0.00482 -0.0703 0.1438 1.0000
6.000 0.9684 0.01202 0.00529 -0.0696 0.1088 1.0000
6.250 0.9914 0.01260 0.00575 -0.0689 0.0872 1.0000
6.500 1.0149 0.01311 0.00622 -0.0683 0.0715 1.0000
6.750 1.0378 0.01369 0.00672 -0.0676 0.0560 1.0000
7.000 1.0597 0.01440 0.00735 -0.0667 0.0420 1.0000
7.250 1.0825 0.01498 0.00796 -0.0659 0.0361 1.0000
7.500 1.1028 0.01583 0.00882 -0.0648 0.0313 1.0000
7.750 1.1258 0.01633 0.00939 -0.0641 0.0293 1.0000
8.000 1.1475 0.01695 0.01006 -0.0632 0.0273 1.0000
8.250 1.1673 0.01776 0.01090 -0.0620 0.0253 1.0000
8.500 1.1839 0.01890 0.01213 -0.0604 0.0235 1.0000
8.750 1.2043 0.01959 0.01292 -0.0593 0.0225 1.0000
9.000 1.2235 0.02039 0.01380 -0.0581 0.0213 1.0000
9.250 1.2420 0.02120 0.01466 -0.0568 0.0201 1.0000
9.500 1.2578 0.02228 0.01579 -0.0553 0.0189 1.0000
9.750 1.2676 0.02429 0.01793 -0.0529 0.0178 1.0000
10.000 1.2857 0.02501 0.01878 -0.0516 0.0171 1.0000
10.250 1.3009 0.02608 0.01996 -0.0499 0.0164 1.0000
10.500 1.3138 0.02714 0.02114 -0.0479 0.0156 1.0000
10.750 1.3250 0.02826 0.02235 -0.0458 0.0150 1.0000
11.000 1.3346 0.02945 0.02362 -0.0435 0.0145 1.0000
11.250 1.3415 0.03107 0.02531 -0.0412 0.0139 1.0000
11.500 1.3411 0.03477 0.02926 -0.0386 0.0132 1.0000
11.750 1.3476 0.03560 0.03024 -0.0363 0.0129 1.0000
12.000 1.3524 0.03700 0.03181 -0.0342 0.0125 1.0000
12.250 1.3544 0.03897 0.03398 -0.0322 0.0122 1.0000
12.500 1.3548 0.04112 0.03631 -0.0303 0.0118 1.0000
12.750 1.3532 0.04357 0.03893 -0.0287 0.0116 1.0000
13.000 1.3505 0.04618 0.04172 -0.0274 0.0113 1.0000
13.250 1.3467 0.04899 0.04468 -0.0265 0.0111 1.0000
13.500 1.3388 0.05252 0.04840 -0.0259 0.0110 1.0000
13.750 1.3323 0.05593 0.05196 -0.0259 0.0108 1.0000
14.000 1.3230 0.05999 0.05618 -0.0264 0.0106 1.0000
14.250 1.3103 0.06486 0.06123 -0.0276 0.0106 1.0000
14.500 1.2991 0.06983 0.06635 -0.0294 0.0105 1.0000
14.750 1.2823 0.07621 0.07293 -0.0324 0.0104 1.0000
15.000 1.2606 0.08427 0.08121 -0.0368 0.0105 1.0000
15.250 1.2359 0.09373 0.09091 -0.0426 0.0106 1.0000
15.500 1.2016 0.10628 0.10372 -0.0506 0.0108 1.0000
15.750 1.1393 0.12750 0.12531 -0.0646 0.0114 1.0000
16.000 1.0073 0.17787 0.17585 -0.0927 0.0137 1.0000
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Polar data table (+)
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