HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 AIRFOIL (hq259-il) Reynolds number: 50,000 Max Cl/Cd: 39.6 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259-il-50000-n5.txt Download as CSV file: xf-hq259-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4050 0.09841 0.09157 -0.0321 1.0000 0.0470
-8.500 -0.4078 0.09432 0.08758 -0.0345 1.0000 0.0439
-8.250 -0.4133 0.08999 0.08335 -0.0378 1.0000 0.0401
-8.000 -0.4131 0.08664 0.08008 -0.0379 1.0000 0.0393
-7.750 -0.4167 0.08324 0.07679 -0.0385 1.0000 0.0386
-7.500 -0.4196 0.07955 0.07319 -0.0402 1.0000 0.0380
-7.250 -0.4230 0.07551 0.06922 -0.0423 1.0000 0.0376
-7.000 -0.4259 0.07172 0.06547 -0.0437 1.0000 0.0371
-6.750 -0.4281 0.06799 0.06174 -0.0446 1.0000 0.0366
-6.500 -0.4297 0.06415 0.05785 -0.0455 1.0000 0.0366
-6.250 -0.4291 0.06036 0.05395 -0.0460 1.0000 0.0369
-6.000 -0.4256 0.05667 0.05010 -0.0463 1.0000 0.0371
-5.750 -0.4190 0.05295 0.04613 -0.0467 1.0000 0.0376
-5.500 -0.4090 0.04915 0.04197 -0.0470 1.0000 0.0386
-5.250 -0.3956 0.04554 0.03793 -0.0471 1.0000 0.0393
-5.000 -0.3794 0.04209 0.03403 -0.0471 1.0000 0.0396
-4.750 -0.3608 0.03887 0.03033 -0.0469 1.0000 0.0398
-4.500 -0.3397 0.03587 0.02679 -0.0465 1.0000 0.0403
-4.250 -0.3171 0.03325 0.02360 -0.0459 1.0000 0.0410
-4.000 -0.2952 0.03068 0.02079 -0.0455 1.0000 0.0429
-3.750 -0.2729 0.02894 0.01872 -0.0448 1.0000 0.0463
-3.500 -0.2495 0.02766 0.01697 -0.0438 1.0000 0.0539
-3.250 -0.2276 0.02614 0.01545 -0.0429 1.0000 0.0610
-3.000 -0.2052 0.02488 0.01404 -0.0418 1.0000 0.0719
-2.750 -0.1830 0.02386 0.01290 -0.0409 1.0000 0.0904
-2.500 -0.1485 0.02271 0.01170 -0.0427 0.9952 0.1244
-2.250 -0.1126 0.02129 0.01060 -0.0451 0.9902 0.1941
-2.000 -0.0893 0.01947 0.01081 -0.0441 0.9857 0.6378
-1.750 -0.0698 0.01938 0.01082 -0.0411 0.9778 0.7709
-1.500 -0.0302 0.01885 0.01048 -0.0410 0.9718 1.0000
-1.250 0.0055 0.01903 0.01022 -0.0437 0.9637 1.0000
-1.000 0.0427 0.01927 0.01007 -0.0464 0.9564 1.0000
-0.750 0.0793 0.01952 0.00994 -0.0490 0.9486 1.0000
-0.500 0.1138 0.01978 0.00992 -0.0511 0.9402 1.0000
-0.250 0.1529 0.02006 0.00995 -0.0539 0.9330 1.0000
0.000 0.1850 0.02031 0.01001 -0.0553 0.9235 1.0000
0.250 0.2203 0.02057 0.01007 -0.0573 0.9149 1.0000
0.500 0.2582 0.02082 0.01019 -0.0596 0.9067 1.0000
0.750 0.2900 0.02107 0.01034 -0.0608 0.8965 1.0000
1.000 0.3247 0.02131 0.01050 -0.0625 0.8871 1.0000
1.250 0.3642 0.02150 0.01064 -0.0649 0.8789 1.0000
1.500 0.3945 0.02173 0.01085 -0.0656 0.8678 1.0000
1.750 0.4260 0.02194 0.01105 -0.0664 0.8568 1.0000
2.000 0.4590 0.02210 0.01124 -0.0673 0.8457 1.0000
2.250 0.4928 0.02215 0.01133 -0.0682 0.8331 1.0000
2.500 0.5255 0.02214 0.01137 -0.0686 0.8186 1.0000
2.750 0.5574 0.02208 0.01139 -0.0688 0.8034 1.0000
3.000 0.5886 0.02203 0.01147 -0.0687 0.7881 1.0000
3.250 0.6195 0.02196 0.01150 -0.0686 0.7727 1.0000
3.500 0.6506 0.02183 0.01149 -0.0684 0.7568 1.0000
3.750 0.6768 0.02183 0.01161 -0.0675 0.7374 1.0000
4.000 0.7056 0.02170 0.01169 -0.0667 0.7176 1.0000
4.250 0.7318 0.02164 0.01177 -0.0656 0.6945 1.0000
4.500 0.7586 0.02154 0.01180 -0.0645 0.6691 1.0000
4.750 0.7844 0.02149 0.01189 -0.0632 0.6400 1.0000
5.000 0.8103 0.02146 0.01194 -0.0619 0.6070 1.0000
5.250 0.8344 0.02156 0.01220 -0.0603 0.5677 1.0000
5.500 0.8579 0.02177 0.01239 -0.0587 0.5237 1.0000
5.750 0.8796 0.02221 0.01275 -0.0570 0.4758 1.0000
6.000 0.9000 0.02286 0.01327 -0.0554 0.4294 1.0000
6.250 0.9190 0.02371 0.01401 -0.0538 0.3855 1.0000
6.500 0.9373 0.02468 0.01488 -0.0522 0.3459 1.0000
6.750 0.9555 0.02573 0.01590 -0.0508 0.3104 1.0000
7.000 0.9734 0.02686 0.01700 -0.0494 0.2792 1.0000
7.250 0.9918 0.02805 0.01834 -0.0481 0.2512 1.0000
7.500 1.0102 0.02928 0.01968 -0.0469 0.2246 1.0000
7.750 1.0261 0.03055 0.02104 -0.0453 0.1970 1.0000
8.000 1.0359 0.03181 0.02239 -0.0433 0.1608 1.0000
8.250 1.0388 0.03332 0.02355 -0.0414 0.1049 1.0000
8.500 1.0447 0.03582 0.02566 -0.0395 0.0572 1.0000
8.750 1.0500 0.03849 0.02827 -0.0372 0.0433 1.0000
9.000 1.0567 0.04090 0.03084 -0.0349 0.0367 1.0000
9.250 1.0617 0.04328 0.03331 -0.0330 0.0320 1.0000
9.500 1.0683 0.04577 0.03603 -0.0311 0.0288 1.0000
9.750 1.0756 0.04831 0.03888 -0.0294 0.0259 1.0000
10.000 1.0810 0.05101 0.04184 -0.0278 0.0242 1.0000
10.250 1.0849 0.05400 0.04509 -0.0264 0.0232 1.0000
10.500 1.0862 0.05723 0.04857 -0.0252 0.0224 1.0000
10.750 1.0851 0.06076 0.05235 -0.0242 0.0219 1.0000
11.000 1.0806 0.06470 0.05668 -0.0237 0.0215 1.0000
11.250 1.0745 0.06886 0.06112 -0.0236 0.0214 1.0000
11.500 1.0643 0.07362 0.06613 -0.0241 0.0211 1.0000
11.750 1.0524 0.07877 0.07155 -0.0255 0.0211 1.0000
12.000 1.0391 0.08441 0.07743 -0.0277 0.0212 1.0000
12.250 1.0234 0.09092 0.08417 -0.0309 0.0212 1.0000
12.500 1.0069 0.09827 0.09177 -0.0353 0.0216 1.0000
12.750 0.9876 0.10725 0.10086 -0.0410 0.0220 1.0000
13.000 0.9652 0.11837 0.11217 -0.0482 0.0228 1.0000
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Polar data table (+)
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