HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 50,000 Max Cl/Cd: 38.51 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq208-il-50000-n5.txt Download as CSV file: xf-hq208-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4709 0.11712 0.11007 -0.0139 1.0000 0.0938
-9.500 -0.4698 0.11399 0.10700 -0.0158 1.0000 0.0966
-9.250 -0.4851 0.11226 0.10544 -0.0211 1.0000 0.0995
-9.000 -0.4800 0.10788 0.10113 -0.0219 1.0000 0.1003
-8.750 -0.4703 0.10346 0.09673 -0.0216 1.0000 0.1013
-8.500 -0.4568 0.09633 0.08952 -0.0239 1.0000 0.0549
-8.000 -0.4597 0.08745 0.08080 -0.0296 1.0000 0.0442
-7.750 -0.4590 0.08369 0.07712 -0.0307 1.0000 0.0427
-7.500 -0.4581 0.07942 0.07292 -0.0336 1.0000 0.0414
-7.250 -0.4574 0.07482 0.06836 -0.0368 1.0000 0.0401
-7.000 -0.4561 0.07030 0.06383 -0.0395 1.0000 0.0388
-6.750 -0.4541 0.06561 0.05908 -0.0420 1.0000 0.0375
-6.500 -0.4507 0.06082 0.05415 -0.0441 1.0000 0.0362
-6.250 -0.4445 0.05576 0.04870 -0.0460 1.0000 0.0344
-5.750 -0.4211 0.04856 0.04081 -0.0461 1.0000 0.0334
-5.500 -0.4077 0.04492 0.03683 -0.0458 1.0000 0.0334
-5.250 -0.3932 0.04134 0.03293 -0.0455 1.0000 0.0340
-5.000 -0.3788 0.03872 0.03024 -0.0450 1.0000 0.0370
-4.750 -0.3605 0.03625 0.02741 -0.0444 1.0000 0.0400
-4.500 -0.3398 0.03357 0.02415 -0.0437 1.0000 0.0417
-4.250 -0.3177 0.03099 0.02108 -0.0427 1.0000 0.0427
-4.000 -0.2946 0.02874 0.01835 -0.0416 1.0000 0.0442
-3.750 -0.2713 0.02687 0.01603 -0.0402 1.0000 0.0462
-3.500 -0.2502 0.02509 0.01424 -0.0389 1.0000 0.0502
-3.250 -0.2286 0.02398 0.01290 -0.0376 1.0000 0.0604
-3.000 -0.2069 0.02274 0.01152 -0.0363 1.0000 0.0717
-2.750 -0.1849 0.02156 0.01036 -0.0357 1.0000 0.0953
-2.500 -0.1607 0.02014 0.00914 -0.0355 1.0000 0.1456
-2.250 -0.1412 0.01751 0.00855 -0.0347 1.0000 0.5412
-2.000 -0.1334 0.01715 0.00866 -0.0292 1.0000 0.7380
-1.750 -0.1229 0.01676 0.00848 -0.0240 1.0000 0.8709
-1.500 -0.0850 0.01650 0.00791 -0.0263 1.0000 1.0000
-1.250 -0.0627 0.01661 0.00765 -0.0263 1.0000 1.0000
-1.000 -0.0378 0.01679 0.00749 -0.0268 0.9987 1.0000
-0.750 0.0010 0.01710 0.00740 -0.0298 0.9905 1.0000
-0.500 0.0394 0.01743 0.00743 -0.0327 0.9825 1.0000
-0.250 0.0780 0.01776 0.00753 -0.0356 0.9742 1.0000
0.000 0.1143 0.01806 0.00763 -0.0380 0.9649 1.0000
0.250 0.1518 0.01838 0.00777 -0.0405 0.9560 1.0000
0.500 0.1906 0.01871 0.00797 -0.0433 0.9471 1.0000
0.750 0.2255 0.01899 0.00817 -0.0452 0.9366 1.0000
1.000 0.2615 0.01927 0.00840 -0.0473 0.9262 1.0000
1.250 0.2995 0.01954 0.00864 -0.0496 0.9162 1.0000
1.500 0.3397 0.01978 0.00889 -0.0522 0.9063 1.0000
1.750 0.3754 0.02000 0.00915 -0.0540 0.8944 1.0000
2.000 0.4134 0.02012 0.00937 -0.0557 0.8807 1.0000
2.250 0.4530 0.02006 0.00939 -0.0573 0.8640 1.0000
2.500 0.4862 0.02001 0.00943 -0.0577 0.8441 1.0000
2.750 0.5207 0.01993 0.00946 -0.0581 0.8263 1.0000
3.000 0.5512 0.01994 0.00968 -0.0580 0.8087 1.0000
3.250 0.5792 0.01998 0.00987 -0.0574 0.7893 1.0000
3.500 0.6100 0.01991 0.00995 -0.0571 0.7704 1.0000
3.750 0.6361 0.01994 0.01016 -0.0561 0.7471 1.0000
4.000 0.6630 0.01992 0.01032 -0.0550 0.7220 1.0000
4.250 0.6897 0.01988 0.01056 -0.0538 0.6932 1.0000
4.500 0.7160 0.01986 0.01069 -0.0524 0.6593 1.0000
4.750 0.7410 0.01990 0.01085 -0.0508 0.6173 1.0000
5.000 0.7648 0.02004 0.01100 -0.0489 0.5643 1.0000
5.250 0.7859 0.02041 0.01119 -0.0466 0.4954 1.0000
5.500 0.8037 0.02116 0.01156 -0.0443 0.4174 1.0000
5.750 0.8201 0.02222 0.01239 -0.0423 0.3437 1.0000
6.000 0.8361 0.02344 0.01331 -0.0407 0.2809 1.0000
6.250 0.8527 0.02477 0.01447 -0.0393 0.2210 1.0000
6.500 0.8696 0.02629 0.01584 -0.0380 0.1674 1.0000
6.750 0.8864 0.02797 0.01729 -0.0368 0.1276 1.0000
7.000 0.9044 0.02973 0.01895 -0.0356 0.1056 1.0000
7.250 0.9248 0.03164 0.02097 -0.0344 0.0919 1.0000
7.500 0.9442 0.03353 0.02303 -0.0333 0.0750 1.0000
7.750 0.9661 0.03613 0.02579 -0.0321 0.0642 1.0000
8.000 0.9817 0.03841 0.02829 -0.0309 0.0497 1.0000
8.250 0.9956 0.04082 0.03105 -0.0296 0.0392 1.0000
8.500 1.0127 0.04406 0.03466 -0.0283 0.0346 1.0000
8.750 1.0251 0.04762 0.03838 -0.0272 0.0318 1.0000
9.000 1.0339 0.05145 0.04278 -0.0254 0.0301 1.0000
9.250 1.0367 0.05536 0.04727 -0.0236 0.0284 1.0000
9.500 1.0343 0.05928 0.05164 -0.0219 0.0272 1.0000
9.750 1.0265 0.06323 0.05595 -0.0202 0.0264 1.0000
10.000 1.0134 0.06707 0.06008 -0.0186 0.0261 1.0000
10.250 0.9971 0.07135 0.06459 -0.0180 0.0261 1.0000
10.500 0.9783 0.07638 0.06983 -0.0189 0.0263 1.0000
10.750 0.9586 0.08232 0.07595 -0.0214 0.0271 1.0000
11.000 0.9400 0.08897 0.08271 -0.0252 0.0279 1.0000
11.250 0.9225 0.09650 0.09031 -0.0301 0.0288 1.0000
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Polar data table (+)
Polar graphs
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