HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9 AIRFOIL (hq259-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.38 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq259-il-1000000-n5.txt Download as CSV file: xf-hq259-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4226 0.08165 0.08009 -0.0333 1.0000 0.0025
-8.500 -0.4248 0.07789 0.07636 -0.0349 1.0000 0.0025
-8.250 -0.4344 0.07330 0.07181 -0.0365 1.0000 0.0025
-8.000 -0.4299 0.06656 0.06509 -0.0450 0.9857 0.0024
-7.750 -0.4092 0.05335 0.05175 -0.0674 0.9731 0.0024
-7.500 -0.3957 0.04364 0.04177 -0.0771 0.9554 0.0023
-7.250 -0.4218 0.02055 0.01727 -0.0796 0.9221 0.0021
-7.000 -0.4042 0.01680 0.01293 -0.0789 0.9111 0.0021
-6.750 -0.3820 0.01475 0.01048 -0.0783 0.9024 0.0021
-6.500 -0.3584 0.01322 0.00862 -0.0778 0.8939 0.0022
-6.250 -0.3335 0.01214 0.00731 -0.0774 0.8862 0.0023
-5.750 -0.2816 0.01086 0.00574 -0.0769 0.8715 0.0026
-5.500 -0.2560 0.01008 0.00480 -0.0766 0.8646 0.0030
-5.250 -0.2293 0.00966 0.00432 -0.0765 0.8576 0.0033
-5.000 -0.2024 0.00938 0.00397 -0.0763 0.8512 0.0038
-4.750 -0.1753 0.00905 0.00357 -0.0763 0.8444 0.0042
-4.250 -0.1206 0.00855 0.00292 -0.0761 0.8313 0.0053
-4.000 -0.0935 0.00823 0.00252 -0.0760 0.8247 0.0069
-3.750 -0.0659 0.00799 0.00224 -0.0759 0.8178 0.0081
-3.250 -0.0107 0.00766 0.00178 -0.0758 0.8025 0.0101
-3.000 0.0168 0.00749 0.00158 -0.0757 0.7934 0.0163
-2.500 0.0720 0.00722 0.00130 -0.0757 0.7743 0.0377
-2.250 0.0997 0.00712 0.00119 -0.0756 0.7663 0.0474
-2.000 0.1275 0.00703 0.00109 -0.0756 0.7580 0.0603
-1.750 0.1552 0.00689 0.00100 -0.0757 0.7489 0.0864
-1.500 0.1822 0.00656 0.00089 -0.0757 0.7380 0.1723
-1.250 0.2093 0.00631 0.00081 -0.0757 0.7260 0.2475
-1.000 0.2360 0.00599 0.00074 -0.0757 0.7116 0.3540
-0.750 0.2628 0.00578 0.00070 -0.0757 0.6954 0.4356
-0.500 0.2899 0.00568 0.00067 -0.0756 0.6803 0.4897
-0.250 0.3166 0.00547 0.00071 -0.0755 0.6680 0.5876
0.000 0.3435 0.00539 0.00076 -0.0753 0.6556 0.6475
0.250 0.3707 0.00542 0.00078 -0.0752 0.6393 0.6717
0.500 0.3978 0.00549 0.00081 -0.0750 0.6198 0.6865
0.750 0.4251 0.00557 0.00084 -0.0749 0.5990 0.6962
1.000 0.4522 0.00568 0.00088 -0.0748 0.5785 0.7045
1.500 0.5056 0.00597 0.00100 -0.0744 0.5225 0.7222
1.750 0.5315 0.00621 0.00110 -0.0741 0.4830 0.7311
2.250 0.5837 0.00665 0.00132 -0.0736 0.4146 0.7507
2.500 0.6098 0.00686 0.00145 -0.0734 0.3846 0.7610
2.750 0.6359 0.00707 0.00158 -0.0731 0.3552 0.7722
3.000 0.6615 0.00733 0.00173 -0.0728 0.3204 0.7841
3.250 0.6869 0.00759 0.00190 -0.0725 0.2867 0.7970
3.500 0.7122 0.00785 0.00209 -0.0721 0.2576 0.8110
3.750 0.7379 0.00802 0.00225 -0.0718 0.2396 0.8272
4.000 0.7623 0.00830 0.00245 -0.0712 0.2064 0.8477
4.250 0.7849 0.00862 0.00268 -0.0704 0.1659 0.8789
4.500 0.8139 0.00881 0.00290 -0.0708 0.1359 1.0000
4.750 0.8365 0.00946 0.00326 -0.0701 0.0836 1.0000
5.000 0.8589 0.01015 0.00371 -0.0694 0.0372 1.0000
5.250 0.8813 0.01086 0.00423 -0.0686 0.0045 1.0000
5.500 0.9070 0.01114 0.00453 -0.0683 0.0032 1.0000
5.750 0.9325 0.01143 0.00486 -0.0680 0.0028 1.0000
6.000 0.9578 0.01175 0.00521 -0.0676 0.0025 1.0000
6.250 0.9825 0.01213 0.00564 -0.0672 0.0021 1.0000
6.500 1.0060 0.01267 0.00627 -0.0665 0.0017 1.0000
6.750 1.0284 0.01336 0.00708 -0.0656 0.0015 1.0000
7.000 1.0519 0.01386 0.00763 -0.0649 0.0015 1.0000
7.250 1.0746 0.01445 0.00830 -0.0642 0.0014 1.0000
7.500 1.0964 0.01514 0.00907 -0.0632 0.0014 1.0000
7.750 1.1176 0.01587 0.00988 -0.0622 0.0014 1.0000
8.000 1.1376 0.01671 0.01082 -0.0611 0.0013 1.0000
8.250 1.1567 0.01762 0.01182 -0.0598 0.0013 1.0000
8.500 1.1744 0.01866 0.01298 -0.0583 0.0013 1.0000
8.750 1.1912 0.01977 0.01419 -0.0567 0.0013 1.0000
9.000 1.2070 0.02096 0.01554 -0.0550 0.0013 1.0000
9.250 1.2214 0.02229 0.01700 -0.0531 0.0013 1.0000
9.500 1.2350 0.02365 0.01850 -0.0512 0.0013 1.0000
9.750 1.2465 0.02523 0.02023 -0.0491 0.0013 1.0000
10.000 1.2564 0.02682 0.02198 -0.0467 0.0013 1.0000
10.250 1.2617 0.02849 0.02382 -0.0437 0.0013 1.0000
10.500 1.2642 0.03028 0.02578 -0.0405 0.0013 1.0000
10.750 1.2649 0.03219 0.02786 -0.0374 0.0013 1.0000
11.000 1.2622 0.03446 0.03033 -0.0343 0.0013 1.0000
11.250 1.2620 0.03635 0.03237 -0.0319 0.0013 1.0000
11.500 1.2538 0.03930 0.03554 -0.0293 0.0013 1.0000
11.750 1.2487 0.04194 0.03834 -0.0275 0.0013 1.0000
12.000 1.2423 0.04487 0.04143 -0.0262 0.0013 1.0000
12.250 1.2295 0.04882 0.04559 -0.0254 0.0013 1.0000
12.500 1.2203 0.05257 0.04950 -0.0254 0.0013 1.0000
12.750 1.2064 0.05735 0.05445 -0.0262 0.0013 1.0000
13.000 1.1893 0.06309 0.06038 -0.0280 0.0013 1.0000
13.250 1.1768 0.06864 0.06607 -0.0305 0.0013 1.0000
13.500 1.1561 0.07632 0.07393 -0.0346 0.0013 1.0000
13.750 1.1464 0.08261 0.08034 -0.0384 0.0013 1.0000
14.000 1.1236 0.09248 0.09037 -0.0445 0.0013 1.0000
14.250 1.1072 0.10162 0.09964 -0.0503 0.0013 1.0000
14.500 1.0889 0.11174 0.10988 -0.0564 0.0013 1.0000
14.750 1.0707 0.12218 0.12043 -0.0626 0.0014 1.0000
15.000 1.0466 0.13464 0.13299 -0.0697 0.0014 1.0000
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Polar data table (+)
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