HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 50,000 Max Cl/Cd: 35.92 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2511-il-50000.txt Download as CSV file: xf-hq2511-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3800 0.10546 0.09871 -0.0249 1.0000 0.2632
-8.750 -0.3916 0.10421 0.09757 -0.0250 1.0000 0.2752
-8.500 -0.3894 0.10138 0.09483 -0.0240 1.0000 0.2902
-8.250 -0.3905 0.09886 0.09240 -0.0228 1.0000 0.3055
-8.000 -0.3602 0.09373 0.08722 -0.0206 1.0000 0.3259
-7.750 -0.3596 0.09131 0.08488 -0.0188 1.0000 0.3461
-7.500 -0.3677 0.08957 0.08327 -0.0169 1.0000 0.3631
-7.250 -0.3785 0.08809 0.08193 -0.0144 1.0000 0.3788
-7.000 -0.3565 0.08401 0.07786 -0.0121 1.0000 0.4059
-6.750 -0.3468 0.08106 0.07496 -0.0093 1.0000 0.4331
-6.000 -0.5069 0.05613 0.04946 -0.0417 1.0000 0.1303
-5.750 -0.4961 0.05196 0.04509 -0.0413 1.0000 0.1228
-5.500 -0.4829 0.04692 0.03907 -0.0426 1.0000 0.1134
-5.250 -0.4666 0.04338 0.03503 -0.0424 1.0000 0.1136
-5.000 -0.4487 0.03984 0.03123 -0.0421 1.0000 0.1163
-4.750 -0.4291 0.03719 0.02831 -0.0416 1.0000 0.1236
-4.500 -0.4085 0.03481 0.02563 -0.0412 1.0000 0.1373
-4.250 -0.3854 0.03248 0.02296 -0.0407 1.0000 0.1527
-4.000 -0.3609 0.03036 0.02050 -0.0401 1.0000 0.1653
-3.750 -0.3369 0.02872 0.01862 -0.0394 1.0000 0.1783
-3.500 -0.3139 0.02742 0.01720 -0.0385 1.0000 0.1935
-3.250 -0.2914 0.02628 0.01602 -0.0374 1.0000 0.2112
-3.000 -0.2695 0.02521 0.01500 -0.0362 1.0000 0.2355
-2.750 -0.2466 0.02406 0.01405 -0.0355 1.0000 0.2777
-2.500 -0.2327 0.02177 0.01411 -0.0318 1.0000 0.5900
-2.250 -0.2421 0.02211 0.01482 -0.0209 1.0000 0.7704
-2.000 -0.2453 0.02206 0.01480 -0.0126 1.0000 0.8484
-1.750 -0.1585 0.02260 0.01489 -0.0195 1.0000 1.0000
-1.500 -0.1615 0.02210 0.01422 -0.0170 1.0000 1.0000
-1.250 -0.1502 0.02192 0.01379 -0.0166 1.0000 1.0000
-1.000 -0.1311 0.02199 0.01357 -0.0173 1.0000 1.0000
-0.750 -0.1092 0.02222 0.01351 -0.0182 1.0000 1.0000
-0.500 -0.0864 0.02254 0.01356 -0.0192 1.0000 1.0000
-0.250 -0.0635 0.02295 0.01373 -0.0201 1.0000 1.0000
0.000 -0.0410 0.02342 0.01397 -0.0209 1.0000 1.0000
0.250 -0.0189 0.02395 0.01431 -0.0216 1.0000 1.0000
0.500 0.0027 0.02454 0.01470 -0.0223 1.0000 1.0000
0.750 0.0236 0.02518 0.01519 -0.0228 1.0000 1.0000
1.000 0.0441 0.02588 0.01576 -0.0233 1.0000 1.0000
1.250 0.0812 0.02709 0.01684 -0.0270 0.9919 1.0000
1.500 0.1263 0.02852 0.01814 -0.0320 0.9781 1.0000
1.750 0.1695 0.02987 0.01941 -0.0365 0.9634 1.0000
2.000 0.2146 0.03120 0.02067 -0.0412 0.9464 1.0000
2.250 0.2660 0.03253 0.02195 -0.0465 0.9267 1.0000
2.500 0.3042 0.03343 0.02286 -0.0494 0.9061 1.0000
2.750 0.3484 0.03441 0.02385 -0.0531 0.8872 1.0000
3.000 0.3955 0.03535 0.02483 -0.0569 0.8695 1.0000
3.250 0.4240 0.03613 0.02567 -0.0578 0.8500 1.0000
3.500 0.4617 0.03685 0.02646 -0.0598 0.8305 1.0000
3.750 0.5080 0.03736 0.02708 -0.0626 0.8117 1.0000
4.000 0.5389 0.03790 0.02774 -0.0632 0.7903 1.0000
4.250 0.5821 0.03806 0.02804 -0.0649 0.7697 1.0000
4.500 0.6243 0.03805 0.02819 -0.0662 0.7490 1.0000
4.750 0.6653 0.03777 0.02813 -0.0669 0.7266 1.0000
5.000 0.7194 0.03657 0.02718 -0.0681 0.7049 1.0000
5.250 0.7689 0.03494 0.02581 -0.0680 0.6814 1.0000
5.500 0.8124 0.03334 0.02442 -0.0669 0.6555 1.0000
5.750 0.8592 0.03131 0.02261 -0.0658 0.6277 1.0000
6.000 0.9017 0.02954 0.02097 -0.0644 0.5960 1.0000
6.250 0.9418 0.02808 0.01952 -0.0629 0.5605 1.0000
6.500 0.9703 0.02769 0.01911 -0.0609 0.5211 1.0000
6.750 0.9969 0.02786 0.01915 -0.0591 0.4812 1.0000
7.000 1.0241 0.02851 0.01957 -0.0578 0.4432 1.0000
7.250 1.0457 0.02974 0.02076 -0.0563 0.4095 1.0000
7.500 1.0682 0.03105 0.02207 -0.0551 0.3808 1.0000
7.750 1.0932 0.03231 0.02324 -0.0542 0.3563 1.0000
8.000 1.1126 0.03399 0.02513 -0.0529 0.3361 1.0000
8.250 1.1358 0.03558 0.02679 -0.0520 0.3171 1.0000
8.500 1.1579 0.03721 0.02845 -0.0510 0.2974 1.0000
8.750 1.1723 0.03792 0.02908 -0.0489 0.2685 1.0000
9.000 1.1780 0.03830 0.02940 -0.0458 0.2381 1.0000
9.250 1.1851 0.03926 0.03035 -0.0430 0.2098 1.0000
9.500 1.1854 0.04089 0.03199 -0.0393 0.1773 1.0000
9.750 1.1866 0.04301 0.03386 -0.0359 0.1448 1.0000
10.000 1.1960 0.04620 0.03706 -0.0337 0.1242 1.0000
10.250 1.2077 0.04933 0.04030 -0.0319 0.1118 1.0000
10.500 1.2238 0.05226 0.04314 -0.0309 0.1014 1.0000
10.750 1.2192 0.05585 0.04736 -0.0279 0.0978 1.0000
11.000 1.2164 0.05965 0.05162 -0.0254 0.0949 1.0000
11.250 1.2125 0.06331 0.05557 -0.0231 0.0927 1.0000
11.500 1.2098 0.06707 0.05952 -0.0212 0.0908 1.0000
11.750 1.2136 0.07161 0.06410 -0.0203 0.0886 1.0000
12.000 1.1934 0.07575 0.06854 -0.0181 0.0886 1.0000
12.250 1.1146 0.08255 0.07596 -0.0179 0.0942 1.0000
12.500 1.0763 0.09010 0.08371 -0.0207 0.0964 1.0000
12.750 1.0426 0.09858 0.09230 -0.0249 0.0984 1.0000
13.000 1.0167 0.10737 0.10114 -0.0295 0.1001 1.0000
13.250 0.9967 0.11630 0.11007 -0.0341 0.1012 1.0000
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