HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 100,000 Max Cl/Cd: 55.18 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq209-il-100000.txt Download as CSV file: xf-hq209-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4477 0.09892 0.09405 -0.0241 1.0000 0.0896
-8.750 -0.4572 0.09577 0.09100 -0.0283 1.0000 0.0930
-8.500 -0.4768 0.09262 0.08799 -0.0344 1.0000 0.0940
-8.250 -0.4548 0.08791 0.08326 -0.0298 1.0000 0.0975
-8.000 -0.4501 0.08483 0.08023 -0.0296 1.0000 0.1014
-7.750 -0.4594 0.08160 0.07710 -0.0318 1.0000 0.1048
-7.500 -0.4867 0.07705 0.07256 -0.0422 1.0000 0.1075
-7.250 -0.4771 0.07271 0.06833 -0.0395 1.0000 0.1103
-7.000 -0.4692 0.07002 0.06564 -0.0375 1.0000 0.1147
-6.750 -0.4938 0.06658 0.06192 -0.0442 1.0000 0.1220
-6.500 -0.4764 0.06269 0.05828 -0.0398 1.0000 0.1256
-6.250 -0.4860 0.05990 0.05520 -0.0419 1.0000 0.1362
-6.000 -0.4750 0.05666 0.05218 -0.0385 1.0000 0.1401
-5.750 -0.4746 0.05369 0.04906 -0.0384 1.0000 0.1517
-5.500 -0.4698 0.05102 0.04630 -0.0374 1.0000 0.1650
-5.250 -0.4623 0.04859 0.04391 -0.0354 1.0000 0.1805
-5.000 -0.4172 0.02437 0.01811 -0.0370 1.0000 0.0666
-4.750 -0.4008 0.02064 0.01411 -0.0365 1.0000 0.0654
-4.500 -0.3815 0.01724 0.01036 -0.0358 1.0000 0.0634
-4.250 -0.3591 0.01397 0.00660 -0.0351 1.0000 0.0605
-4.000 -0.3353 0.01139 0.00355 -0.0343 1.0000 0.0600
-3.750 -0.3115 0.00943 0.00127 -0.0334 1.0000 0.0620
-3.500 -0.2895 0.02108 0.01211 -0.0337 1.0000 0.0700
-3.250 -0.2662 0.01991 0.01083 -0.0327 1.0000 0.0799
-3.000 -0.2441 0.01853 0.00960 -0.0319 1.0000 0.0996
-2.750 -0.2223 0.01749 0.00871 -0.0311 1.0000 0.1334
-2.500 -0.2001 0.01608 0.00786 -0.0306 1.0000 0.2120
-2.250 -0.1913 0.01424 0.00821 -0.0264 1.0000 0.6928
-2.000 -0.1808 0.01434 0.00841 -0.0221 1.0000 0.7755
-1.750 -0.1704 0.01435 0.00846 -0.0181 1.0000 0.8340
-1.500 -0.1565 0.01425 0.00842 -0.0147 1.0000 0.8982
-1.250 -0.0957 0.01434 0.00829 -0.0218 0.9947 1.0000
-1.000 -0.0511 0.01468 0.00835 -0.0264 0.9867 1.0000
-0.750 -0.0063 0.01508 0.00848 -0.0309 0.9792 1.0000
-0.500 0.0377 0.01545 0.00865 -0.0351 0.9710 1.0000
-0.250 0.0781 0.01577 0.00880 -0.0384 0.9620 1.0000
0.000 0.1254 0.01615 0.00902 -0.0429 0.9547 1.0000
0.250 0.1620 0.01640 0.00917 -0.0453 0.9445 1.0000
0.500 0.2005 0.01667 0.00936 -0.0479 0.9350 1.0000
0.750 0.2480 0.01692 0.00955 -0.0521 0.9277 1.0000
1.000 0.2866 0.01706 0.00966 -0.0544 0.9160 1.0000
1.250 0.3337 0.01700 0.00959 -0.0579 0.9034 1.0000
1.500 0.3852 0.01675 0.00936 -0.0618 0.8905 1.0000
1.750 0.4275 0.01658 0.00924 -0.0640 0.8784 1.0000
2.000 0.4665 0.01647 0.00916 -0.0656 0.8676 1.0000
2.250 0.5066 0.01625 0.00900 -0.0672 0.8573 1.0000
2.500 0.5401 0.01610 0.00894 -0.0675 0.8448 1.0000
2.750 0.5707 0.01597 0.00887 -0.0672 0.8310 1.0000
3.000 0.5993 0.01583 0.00879 -0.0665 0.8158 1.0000
3.250 0.6252 0.01574 0.00878 -0.0653 0.7984 1.0000
3.500 0.6527 0.01552 0.00868 -0.0642 0.7805 1.0000
3.750 0.6813 0.01521 0.00843 -0.0630 0.7623 1.0000
4.000 0.7061 0.01503 0.00833 -0.0614 0.7385 1.0000
4.250 0.7315 0.01480 0.00816 -0.0597 0.7118 1.0000
4.500 0.7569 0.01457 0.00797 -0.0580 0.6796 1.0000
4.750 0.7799 0.01447 0.00783 -0.0559 0.6365 1.0000
5.000 0.8013 0.01454 0.00777 -0.0537 0.5792 1.0000
5.250 0.8211 0.01488 0.00785 -0.0515 0.5120 1.0000
5.500 0.8400 0.01553 0.00815 -0.0495 0.4456 1.0000
5.750 0.8588 0.01632 0.00865 -0.0479 0.3884 1.0000
6.000 0.8779 0.01715 0.00934 -0.0464 0.3375 1.0000
6.250 0.8958 0.01811 0.01009 -0.0449 0.2868 1.0000
6.500 0.9103 0.01943 0.01106 -0.0430 0.2221 1.0000
6.750 0.9245 0.02100 0.01223 -0.0410 0.1589 1.0000
7.000 0.9416 0.02261 0.01358 -0.0394 0.1306 1.0000
7.250 0.9614 0.02418 0.01505 -0.0381 0.1131 1.0000
7.500 0.9829 0.02582 0.01665 -0.0372 0.1005 1.0000
7.750 1.0070 0.02768 0.01857 -0.0365 0.0913 1.0000
8.000 1.0302 0.02967 0.02079 -0.0356 0.0816 1.0000
8.250 1.0454 0.03096 0.02209 -0.0344 0.0669 1.0000
8.500 1.0625 0.03330 0.02458 -0.0331 0.0545 1.0000
8.750 1.0795 0.03653 0.02817 -0.0314 0.0458 1.0000
9.000 1.0939 0.04022 0.03192 -0.0304 0.0400 1.0000
9.250 1.1046 0.04315 0.03547 -0.0281 0.0380 1.0000
9.500 1.1110 0.04693 0.03979 -0.0257 0.0370 1.0000
9.750 1.1115 0.05100 0.04436 -0.0231 0.0365 1.0000
10.000 1.1071 0.05510 0.04890 -0.0206 0.0365 1.0000
10.250 1.0971 0.05919 0.05336 -0.0180 0.0367 1.0000
10.500 1.0815 0.06293 0.05738 -0.0151 0.0370 1.0000
10.750 1.0627 0.06678 0.06147 -0.0131 0.0373 1.0000
11.000 1.0425 0.07107 0.06596 -0.0123 0.0376 1.0000
11.250 1.0221 0.07585 0.07092 -0.0129 0.0380 1.0000
11.500 1.0011 0.08134 0.07657 -0.0149 0.0384 1.0000
11.750 0.9787 0.08782 0.08318 -0.0183 0.0387 1.0000
12.000 0.9588 0.09501 0.09045 -0.0227 0.0393 1.0000
12.250 0.9419 0.10274 0.09823 -0.0273 0.0398 1.0000
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