HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| 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: 84.56 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2590sm-il-500000-n5.txt Download as CSV file: xf-hq2590sm-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4671 0.08507 0.08274 -0.0354 1.0000 0.0084
-9.500 -0.4796 0.07859 0.07630 -0.0384 1.0000 0.0085
-9.250 -0.4945 0.07232 0.07009 -0.0416 1.0000 0.0085
-8.750 -0.5585 0.04515 0.04268 -0.0662 0.9894 0.0085
-8.500 -0.5524 0.03291 0.02980 -0.0743 0.9800 0.0089
-8.250 -0.5317 0.02746 0.02386 -0.0774 0.9735 0.0094
-8.000 -0.5064 0.02314 0.01898 -0.0798 0.9687 0.0102
-7.750 -0.4812 0.02037 0.01572 -0.0808 0.9617 0.0112
-7.500 -0.4516 0.01853 0.01351 -0.0821 0.9567 0.0119
-7.250 -0.4238 0.01732 0.01213 -0.0829 0.9499 0.0124
-7.000 -0.3941 0.01663 0.01134 -0.0837 0.9435 0.0128
-6.750 -0.3657 0.01589 0.01048 -0.0842 0.9366 0.0134
-6.500 -0.3377 0.01515 0.00959 -0.0845 0.9292 0.0142
-6.250 -0.3102 0.01452 0.00880 -0.0846 0.9216 0.0150
-6.000 -0.2827 0.01394 0.00808 -0.0846 0.9139 0.0156
-5.750 -0.2566 0.01310 0.00709 -0.0844 0.9059 0.0161
-5.500 -0.2304 0.01232 0.00622 -0.0843 0.8981 0.0168
-5.250 -0.2039 0.01188 0.00573 -0.0842 0.8902 0.0175
-4.750 -0.1500 0.01115 0.00486 -0.0839 0.8760 0.0194
-4.500 -0.1231 0.01075 0.00438 -0.0838 0.8695 0.0201
-4.250 -0.0960 0.01040 0.00396 -0.0836 0.8631 0.0207
-4.000 -0.0688 0.01010 0.00358 -0.0835 0.8569 0.0212
-3.750 -0.0416 0.00968 0.00310 -0.0835 0.8511 0.0226
-3.500 -0.0142 0.00943 0.00283 -0.0834 0.8449 0.0245
-3.250 0.0134 0.00924 0.00258 -0.0833 0.8395 0.0265
-3.000 0.0410 0.00905 0.00234 -0.0833 0.8322 0.0284
-2.750 0.0683 0.00885 0.00210 -0.0831 0.8232 0.0334
-2.500 0.0956 0.00869 0.00192 -0.0829 0.8130 0.0414
-2.250 0.1231 0.00853 0.00177 -0.0828 0.8046 0.0571
-2.000 0.1505 0.00832 0.00164 -0.0828 0.7968 0.0881
-1.750 0.1779 0.00803 0.00152 -0.0828 0.7895 0.1498
-1.500 0.2043 0.00732 0.00135 -0.0831 0.7819 0.3311
-1.250 0.2305 0.00676 0.00134 -0.0831 0.7741 0.5110
-0.750 0.2846 0.00653 0.00137 -0.0826 0.7576 0.6235
-0.500 0.3118 0.00650 0.00139 -0.0823 0.7499 0.6590
-0.250 0.3391 0.00647 0.00142 -0.0821 0.7422 0.6899
0.000 0.3667 0.00648 0.00142 -0.0819 0.7350 0.7024
0.250 0.3946 0.00650 0.00142 -0.0818 0.7268 0.7114
0.500 0.4222 0.00651 0.00143 -0.0817 0.7182 0.7206
0.750 0.4497 0.00654 0.00145 -0.0815 0.7085 0.7296
1.250 0.5044 0.00659 0.00151 -0.0811 0.6839 0.7489
1.500 0.5313 0.00664 0.00155 -0.0808 0.6671 0.7595
1.750 0.5577 0.00671 0.00159 -0.0804 0.6418 0.7708
2.250 0.6043 0.00731 0.00176 -0.0785 0.5209 0.7968
2.750 0.6487 0.00824 0.00221 -0.0764 0.3993 0.8288
3.000 0.6725 0.00853 0.00239 -0.0757 0.3638 0.8468
3.250 0.6969 0.00871 0.00255 -0.0750 0.3424 0.8674
3.500 0.7209 0.00886 0.00270 -0.0742 0.3224 0.8916
3.750 0.7454 0.00897 0.00284 -0.0734 0.3045 0.9290
4.000 0.7771 0.00919 0.00301 -0.0744 0.2835 1.0000
4.250 0.8026 0.00951 0.00322 -0.0741 0.2570 1.0000
4.500 0.8277 0.00986 0.00344 -0.0738 0.2264 1.0000
4.750 0.8514 0.01037 0.00373 -0.0732 0.1822 1.0000
5.000 0.8746 0.01093 0.00408 -0.0727 0.1410 1.0000
5.250 0.8984 0.01144 0.00445 -0.0721 0.1111 1.0000
5.750 0.9472 0.01229 0.00514 -0.0712 0.0776 1.0000
6.000 0.9717 0.01269 0.00550 -0.0708 0.0664 1.0000
6.250 0.9963 0.01307 0.00587 -0.0703 0.0577 1.0000
6.500 1.0207 0.01346 0.00625 -0.0699 0.0503 1.0000
6.750 1.0446 0.01390 0.00666 -0.0693 0.0418 1.0000
7.000 1.0684 0.01434 0.00708 -0.0688 0.0344 1.0000
7.250 1.0919 0.01481 0.00757 -0.0682 0.0295 1.0000
7.500 1.1148 0.01532 0.00807 -0.0675 0.0260 1.0000
7.750 1.1376 0.01584 0.00862 -0.0668 0.0237 1.0000
8.000 1.1606 0.01631 0.00916 -0.0661 0.0223 1.0000
8.250 1.1829 0.01683 0.00972 -0.0654 0.0208 1.0000
8.500 1.2043 0.01743 0.01037 -0.0645 0.0194 1.0000
8.750 1.2241 0.01818 0.01117 -0.0634 0.0180 1.0000
9.000 1.2457 0.01869 0.01176 -0.0626 0.0173 1.0000
9.250 1.2663 0.01929 0.01244 -0.0616 0.0164 1.0000
9.500 1.2863 0.01990 0.01312 -0.0606 0.0155 1.0000
9.750 1.3054 0.02056 0.01385 -0.0594 0.0146 1.0000
10.000 1.3216 0.02147 0.01481 -0.0579 0.0135 1.0000
10.250 1.3393 0.02217 0.01560 -0.0566 0.0128 1.0000
10.500 1.3564 0.02287 0.01641 -0.0552 0.0122 1.0000
10.750 1.3714 0.02359 0.01722 -0.0535 0.0115 1.0000
11.000 1.3849 0.02434 0.01805 -0.0515 0.0109 1.0000
11.250 1.3977 0.02513 0.01889 -0.0496 0.0103 1.0000
11.500 1.4068 0.02617 0.02001 -0.0473 0.0097 1.0000
11.750 1.4171 0.02714 0.02111 -0.0452 0.0092 1.0000
12.000 1.4276 0.02812 0.02219 -0.0433 0.0087 1.0000
12.250 1.4381 0.02912 0.02329 -0.0415 0.0082 1.0000
12.500 1.4463 0.03032 0.02460 -0.0397 0.0078 1.0000
12.750 1.4538 0.03162 0.02600 -0.0379 0.0075 1.0000
13.000 1.4603 0.03305 0.02751 -0.0363 0.0072 1.0000
13.250 1.4627 0.03490 0.02946 -0.0346 0.0069 1.0000
13.500 1.4640 0.03694 0.03163 -0.0330 0.0067 1.0000
13.750 1.4655 0.03906 0.03390 -0.0318 0.0065 1.0000
14.000 1.4652 0.04146 0.03646 -0.0307 0.0063 1.0000
14.250 1.4641 0.04407 0.03922 -0.0299 0.0062 1.0000
14.500 1.4612 0.04702 0.04234 -0.0294 0.0060 1.0000
14.750 1.4568 0.05033 0.04580 -0.0293 0.0059 1.0000
15.000 1.4509 0.05401 0.04964 -0.0297 0.0057 1.0000
15.250 1.4436 0.05814 0.05393 -0.0305 0.0056 1.0000
15.500 1.4341 0.06288 0.05883 -0.0320 0.0055 1.0000
15.750 1.4233 0.06828 0.06439 -0.0342 0.0054 1.0000
16.000 1.4092 0.07472 0.07101 -0.0373 0.0054 1.0000
16.250 1.3943 0.08176 0.07822 -0.0411 0.0054 1.0000
16.500 1.3771 0.08961 0.08625 -0.0454 0.0054 1.0000
16.750 1.3570 0.09826 0.09507 -0.0503 0.0054 1.0000
17.000 1.3357 0.10739 0.10436 -0.0556 0.0053 1.0000
17.250 1.3121 0.11723 0.11437 -0.0613 0.0054 1.0000
17.500 1.2882 0.12744 0.12473 -0.0673 0.0054 1.0000
17.750 1.2638 0.13819 0.13564 -0.0737 0.0055 1.0000
18.000 1.2393 0.14941 0.14699 -0.0805 0.0055 1.0000
18.250 1.2136 0.16147 0.15919 -0.0879 0.0056 1.0000
18.500 1.1829 0.17565 0.17353 -0.0966 0.0057 1.0000
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Polar data table (+)
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