HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 50,000 Max Cl/Cd: 37.91 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2090sm-il-50000-n5.txt Download as CSV file: xf-hq2090sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ-2.0/9 9.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4616 0.09506 0.08809 -0.0281 1.0000 0.0444
-8.750 -0.4624 0.09081 0.08392 -0.0301 1.0000 0.0435
-8.500 -0.4646 0.08647 0.07967 -0.0325 1.0000 0.0425
-8.250 -0.4693 0.08188 0.07517 -0.0353 1.0000 0.0417
-8.000 -0.4768 0.07669 0.07008 -0.0393 1.0000 0.0407
-7.750 -0.4832 0.07151 0.06491 -0.0428 1.0000 0.0398
-7.500 -0.4894 0.06643 0.05976 -0.0454 1.0000 0.0389
-7.250 -0.4917 0.06207 0.05530 -0.0466 1.0000 0.0388
-7.000 -0.4909 0.05814 0.05122 -0.0471 1.0000 0.0390
-6.750 -0.4868 0.05477 0.04770 -0.0470 1.0000 0.0401
-6.500 -0.4809 0.05137 0.04408 -0.0467 1.0000 0.0415
-6.250 -0.4729 0.04791 0.04033 -0.0464 1.0000 0.0430
-6.000 -0.4625 0.04439 0.03642 -0.0458 1.0000 0.0443
-5.750 -0.4493 0.04092 0.03251 -0.0451 1.0000 0.0450
-5.500 -0.4335 0.03762 0.02869 -0.0442 1.0000 0.0460
-5.250 -0.4151 0.03456 0.02506 -0.0432 1.0000 0.0476
-5.000 -0.3956 0.03209 0.02211 -0.0422 1.0000 0.0512
-4.750 -0.3768 0.03047 0.02034 -0.0412 1.0000 0.0574
-4.500 -0.3547 0.02844 0.01783 -0.0399 1.0000 0.0617
-4.250 -0.3344 0.02692 0.01619 -0.0387 1.0000 0.0693
-4.000 -0.3136 0.02561 0.01471 -0.0374 1.0000 0.0786
-3.750 -0.2925 0.02442 0.01331 -0.0358 1.0000 0.0870
-3.500 -0.2723 0.02348 0.01232 -0.0347 1.0000 0.1021
-3.250 -0.2513 0.02249 0.01127 -0.0338 1.0000 0.1168
-3.000 -0.2296 0.02154 0.01037 -0.0332 1.0000 0.1449
-2.750 -0.2062 0.02024 0.00946 -0.0334 1.0000 0.2089
-2.500 -0.1906 0.01841 0.00941 -0.0315 1.0000 0.5485
-2.250 -0.1788 0.01832 0.00957 -0.0275 1.0000 0.6884
-2.000 -0.1680 0.01826 0.00958 -0.0233 0.9999 0.7698
-1.750 -0.1473 0.01812 0.00960 -0.0200 0.9922 0.8728
-1.500 -0.0851 0.01800 0.00921 -0.0262 0.9878 1.0000
-1.250 -0.0484 0.01817 0.00902 -0.0293 0.9795 1.0000
-1.000 -0.0117 0.01837 0.00891 -0.0322 0.9712 1.0000
-0.750 0.0260 0.01861 0.00888 -0.0352 0.9634 1.0000
-0.500 0.0625 0.01886 0.00887 -0.0377 0.9550 1.0000
-0.250 0.0974 0.01910 0.00892 -0.0399 0.9459 1.0000
0.000 0.1367 0.01938 0.00903 -0.0428 0.9380 1.0000
0.250 0.1707 0.01962 0.00913 -0.0447 0.9280 1.0000
0.500 0.2052 0.01986 0.00927 -0.0465 0.9180 1.0000
0.750 0.2436 0.02009 0.00944 -0.0489 0.9091 1.0000
1.000 0.2796 0.02031 0.00961 -0.0508 0.8990 1.0000
1.250 0.3129 0.02053 0.00981 -0.0522 0.8881 1.0000
1.750 0.3841 0.02088 0.01020 -0.0553 0.8672 1.0000
2.000 0.4197 0.02098 0.01034 -0.0566 0.8557 1.0000
2.250 0.4532 0.02103 0.01045 -0.0574 0.8417 1.0000
2.500 0.4874 0.02099 0.01052 -0.0579 0.8268 1.0000
2.750 0.5161 0.02102 0.01063 -0.0576 0.8095 1.0000
3.000 0.5456 0.02103 0.01074 -0.0574 0.7926 1.0000
3.250 0.5753 0.02102 0.01089 -0.0571 0.7757 1.0000
3.500 0.6057 0.02094 0.01094 -0.0567 0.7580 1.0000
3.750 0.6324 0.02093 0.01106 -0.0557 0.7370 1.0000
4.000 0.6608 0.02081 0.01108 -0.0548 0.7151 1.0000
4.250 0.6860 0.02079 0.01126 -0.0535 0.6890 1.0000
4.500 0.7116 0.02076 0.01137 -0.0521 0.6605 1.0000
4.750 0.7369 0.02075 0.01147 -0.0507 0.6279 1.0000
5.000 0.7612 0.02081 0.01162 -0.0491 0.5892 1.0000
5.250 0.7849 0.02094 0.01175 -0.0474 0.5441 1.0000
5.500 0.8067 0.02128 0.01203 -0.0455 0.4905 1.0000
5.750 0.8259 0.02191 0.01241 -0.0435 0.4306 1.0000
6.000 0.8428 0.02279 0.01305 -0.0416 0.3702 1.0000
6.250 0.8593 0.02383 0.01387 -0.0399 0.3165 1.0000
6.500 0.8753 0.02500 0.01487 -0.0383 0.2674 1.0000
6.750 0.8906 0.02632 0.01600 -0.0368 0.2211 1.0000
7.000 0.9064 0.02774 0.01731 -0.0354 0.1809 1.0000
7.250 0.9220 0.02930 0.01881 -0.0341 0.1466 1.0000
7.500 0.9389 0.03098 0.02042 -0.0328 0.1246 1.0000
7.750 0.9576 0.03267 0.02218 -0.0317 0.1064 1.0000
8.000 0.9760 0.03445 0.02404 -0.0305 0.0914 1.0000
8.250 0.9960 0.03651 0.02621 -0.0295 0.0801 1.0000
8.500 1.0126 0.03855 0.02837 -0.0283 0.0684 1.0000
8.750 1.0286 0.04084 0.03072 -0.0272 0.0593 1.0000
9.000 1.0439 0.04326 0.03348 -0.0260 0.0514 1.0000
9.250 1.0594 0.04641 0.03687 -0.0249 0.0469 1.0000
9.500 1.0688 0.04950 0.04056 -0.0232 0.0421 1.0000
9.750 1.0751 0.05225 0.04358 -0.0217 0.0388 1.0000
10.000 1.0795 0.05552 0.04704 -0.0203 0.0370 1.0000
10.250 1.0792 0.05965 0.05138 -0.0188 0.0359 1.0000
10.500 1.0701 0.06333 0.05545 -0.0167 0.0355 1.0000
10.750 1.0571 0.06725 0.05971 -0.0151 0.0353 1.0000
11.000 1.0418 0.07152 0.06426 -0.0145 0.0352 1.0000
11.250 1.0240 0.07632 0.06931 -0.0150 0.0351 1.0000
11.500 1.0057 0.08167 0.07486 -0.0167 0.0352 1.0000
11.750 0.9870 0.08766 0.08102 -0.0195 0.0354 1.0000
12.000 0.9678 0.09447 0.08796 -0.0234 0.0356 1.0000
12.250 0.9495 0.10205 0.09563 -0.0282 0.0358 1.0000
12.500 0.9132 0.11651 0.11022 -0.0392 0.0378 1.0000
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Polar data table (+)
Polar graphs
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