HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 200,000 Max Cl/Cd: 79.26 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3013-il-200000.txt Download as CSV file: xf-hq3013-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3630 0.09312 0.08975 -0.0488 1.0000 0.0590
-9.500 -0.3823 0.08907 0.08580 -0.0503 1.0000 0.0608
-8.500 -0.5358 0.04629 0.04188 -0.0767 0.9738 0.0327
-8.250 -0.5163 0.04064 0.03586 -0.0803 0.9698 0.0320
-8.000 -0.5045 0.03615 0.03087 -0.0809 0.9613 0.0320
-7.750 -0.4785 0.03230 0.02637 -0.0831 0.9571 0.0325
-7.500 -0.4569 0.02875 0.02252 -0.0840 0.9519 0.0338
-7.250 -0.4275 0.02797 0.02173 -0.0852 0.9466 0.0363
-7.000 -0.3935 0.02594 0.01929 -0.0870 0.9434 0.0392
-6.750 -0.3577 0.02341 0.01641 -0.0891 0.9414 0.0423
-6.500 -0.3334 0.02261 0.01558 -0.0889 0.9347 0.0462
-6.250 -0.3001 0.02133 0.01412 -0.0903 0.9309 0.0532
-6.000 -0.2632 0.02061 0.01331 -0.0922 0.9282 0.0607
-5.750 -0.2267 0.01953 0.01221 -0.0943 0.9260 0.0688
-5.500 -0.2045 0.01936 0.01188 -0.0933 0.9180 0.0750
-5.250 -0.1726 0.01825 0.01084 -0.0944 0.9144 0.0825
-5.000 -0.1368 0.01771 0.01017 -0.0958 0.9117 0.0892
-4.750 -0.1162 0.01690 0.00946 -0.0947 0.9043 0.0956
-4.500 -0.0862 0.01632 0.00883 -0.0951 0.8997 0.1045
-4.250 -0.0542 0.01563 0.00817 -0.0959 0.8965 0.1183
-4.000 -0.0340 0.01509 0.00775 -0.0948 0.8888 0.1365
-3.750 -0.0074 0.01419 0.00720 -0.0950 0.8839 0.1990
-3.500 0.0143 0.01278 0.00692 -0.0946 0.8796 0.4606
-3.250 0.0355 0.01280 0.00711 -0.0931 0.8718 0.5457
-3.000 0.0653 0.01280 0.00709 -0.0930 0.8676 0.5896
-2.750 0.0914 0.01291 0.00718 -0.0922 0.8619 0.6177
-2.500 0.1172 0.01299 0.00725 -0.0914 0.8555 0.6394
-2.250 0.1475 0.01296 0.00717 -0.0913 0.8514 0.6571
-2.000 0.1712 0.01308 0.00727 -0.0902 0.8441 0.6726
-1.750 0.1988 0.01310 0.00727 -0.0896 0.8385 0.6895
-1.500 0.2261 0.01318 0.00734 -0.0888 0.8337 0.7098
-1.250 0.2488 0.01332 0.00749 -0.0874 0.8260 0.7263
-1.000 0.2777 0.01325 0.00739 -0.0871 0.8214 0.7366
-0.750 0.3024 0.01331 0.00743 -0.0864 0.8144 0.7471
-0.500 0.3296 0.01329 0.00738 -0.0860 0.8085 0.7593
-0.250 0.3579 0.01322 0.00729 -0.0856 0.8039 0.7681
0.000 0.3825 0.01324 0.00730 -0.0850 0.7959 0.7762
0.250 0.4121 0.01309 0.00712 -0.0850 0.7908 0.7832
0.500 0.4372 0.01304 0.00705 -0.0844 0.7816 0.7916
0.750 0.4672 0.01280 0.00676 -0.0842 0.7749 0.7995
1.000 0.4916 0.01273 0.00671 -0.0834 0.7650 0.8081
1.250 0.5213 0.01260 0.00652 -0.0834 0.7593 0.8175
1.500 0.5446 0.01257 0.00655 -0.0825 0.7500 0.8272
1.750 0.5734 0.01244 0.00639 -0.0823 0.7436 0.8379
2.000 0.5974 0.01238 0.00638 -0.0815 0.7339 0.8499
2.250 0.6230 0.01224 0.00627 -0.0807 0.7254 0.8623
2.500 0.6483 0.01206 0.00612 -0.0798 0.7160 0.8766
2.750 0.6720 0.01192 0.00604 -0.0787 0.7050 0.8939
3.000 0.6983 0.01174 0.00590 -0.0780 0.6946 0.9134
3.250 0.7323 0.01158 0.00575 -0.0789 0.6844 0.9394
3.500 0.7755 0.01148 0.00569 -0.0821 0.6710 0.9766
3.750 0.8075 0.01150 0.00568 -0.0833 0.6575 1.0000
4.000 0.8342 0.01155 0.00570 -0.0833 0.6435 1.0000
4.250 0.8606 0.01162 0.00573 -0.0831 0.6283 1.0000
4.500 0.8864 0.01171 0.00576 -0.0827 0.6117 1.0000
4.750 0.9117 0.01182 0.00581 -0.0822 0.5939 1.0000
5.000 0.9354 0.01196 0.00593 -0.0815 0.5729 1.0000
5.250 0.9589 0.01214 0.00603 -0.0806 0.5509 1.0000
5.500 0.9813 0.01238 0.00621 -0.0796 0.5263 1.0000
5.750 1.0028 0.01268 0.00641 -0.0784 0.5001 1.0000
6.000 1.0229 0.01306 0.00666 -0.0771 0.4720 1.0000
6.250 1.0420 0.01352 0.00697 -0.0756 0.4435 1.0000
6.500 1.0603 0.01403 0.00736 -0.0740 0.4155 1.0000
6.750 1.0779 0.01456 0.00778 -0.0723 0.3881 1.0000
7.000 1.0951 0.01513 0.00824 -0.0706 0.3624 1.0000
7.250 1.1111 0.01574 0.00872 -0.0688 0.3394 1.0000
7.500 1.1276 0.01633 0.00925 -0.0671 0.3174 1.0000
7.750 1.1428 0.01698 0.00980 -0.0652 0.2982 1.0000
8.000 1.1576 0.01766 0.01039 -0.0632 0.2811 1.0000
8.250 1.1713 0.01832 0.01098 -0.0611 0.2655 1.0000
8.500 1.1848 0.01896 0.01159 -0.0590 0.2511 1.0000
8.750 1.1982 0.01960 0.01223 -0.0569 0.2373 1.0000
9.000 1.2117 0.02025 0.01289 -0.0549 0.2242 1.0000
9.250 1.2251 0.02094 0.01359 -0.0529 0.2123 1.0000
9.500 1.2377 0.02169 0.01434 -0.0510 0.2010 1.0000
9.750 1.2491 0.02254 0.01514 -0.0490 0.1905 1.0000
10.000 1.2611 0.02335 0.01598 -0.0471 0.1798 1.0000
10.250 1.2730 0.02419 0.01690 -0.0454 0.1694 1.0000
10.500 1.2832 0.02519 0.01789 -0.0435 0.1596 1.0000
10.750 1.2919 0.02629 0.01895 -0.0416 0.1499 1.0000
11.000 1.3024 0.02726 0.02003 -0.0400 0.1395 1.0000
11.250 1.3111 0.02842 0.02123 -0.0383 0.1295 1.0000
11.500 1.3174 0.02980 0.02258 -0.0366 0.1205 1.0000
11.750 1.3250 0.03111 0.02395 -0.0351 0.1111 1.0000
12.000 1.3325 0.03250 0.02541 -0.0337 0.1017 1.0000
12.250 1.3364 0.03423 0.02710 -0.0322 0.0944 1.0000
12.500 1.3437 0.03574 0.02871 -0.0310 0.0871 1.0000
12.750 1.3475 0.03761 0.03060 -0.0298 0.0809 1.0000
13.000 1.3537 0.03933 0.03241 -0.0288 0.0756 1.0000
13.250 1.3535 0.04168 0.03471 -0.0276 0.0712 1.0000
13.500 1.3607 0.04345 0.03666 -0.0268 0.0673 1.0000
13.750 1.3641 0.04557 0.03887 -0.0261 0.0634 1.0000
14.000 1.3624 0.04826 0.04155 -0.0254 0.0599 1.0000
14.250 1.3678 0.05037 0.04386 -0.0250 0.0567 1.0000
14.500 1.3701 0.05283 0.04645 -0.0248 0.0535 1.0000
14.750 1.3676 0.05591 0.04955 -0.0247 0.0505 1.0000
15.000 1.3676 0.05885 0.05263 -0.0247 0.0478 1.0000
15.250 1.3678 0.06189 0.05583 -0.0250 0.0445 1.0000
15.500 1.3634 0.06558 0.05959 -0.0257 0.0417 1.0000
15.750 1.3574 0.06965 0.06378 -0.0265 0.0386 1.0000
16.000 1.3525 0.07382 0.06811 -0.0276 0.0352 1.0000
16.250 1.3394 0.07925 0.07355 -0.0295 0.0321 1.0000
16.500 1.3307 0.08439 0.07890 -0.0313 0.0287 1.0000
16.750 1.3193 0.09007 0.08467 -0.0336 0.0264 1.0000
17.000 1.3060 0.09598 0.09061 -0.0359 0.0251 1.0000
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