HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 50,000 Max Cl/Cd: 35.66 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159b-il-50000-n5.txt Download as CSV file: xf-hq159b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5131 0.09372 0.08675 -0.0232 1.0000 0.0437
-9.000 -0.5166 0.08859 0.08170 -0.0264 1.0000 0.0429
-8.750 -0.5227 0.08282 0.07602 -0.0305 1.0000 0.0419
-8.500 -0.5373 0.07600 0.06927 -0.0365 1.0000 0.0404
-7.750 -0.5618 0.06094 0.05361 -0.0433 1.0000 0.0384
-7.500 -0.5596 0.05678 0.04920 -0.0436 1.0000 0.0384
-7.250 -0.5554 0.05253 0.04474 -0.0434 1.0000 0.0387
-7.000 -0.5478 0.04894 0.04097 -0.0430 1.0000 0.0399
-6.750 -0.5360 0.04657 0.03854 -0.0424 1.0000 0.0427
-6.500 -0.5246 0.04352 0.03513 -0.0416 1.0000 0.0457
-6.250 -0.5114 0.04021 0.03130 -0.0407 1.0000 0.0481
-6.000 -0.4954 0.03690 0.02740 -0.0394 1.0000 0.0498
-5.750 -0.4773 0.03393 0.02391 -0.0381 1.0000 0.0521
-5.500 -0.4600 0.03222 0.02215 -0.0372 1.0000 0.0591
-5.250 -0.4392 0.03012 0.01949 -0.0358 1.0000 0.0651
-5.000 -0.4190 0.02811 0.01744 -0.0344 1.0000 0.0697
-4.750 -0.3978 0.02658 0.01561 -0.0329 1.0000 0.0766
-4.500 -0.3786 0.02539 0.01438 -0.0315 1.0000 0.0881
-4.250 -0.3591 0.02413 0.01299 -0.0299 1.0000 0.0960
-4.000 -0.3398 0.02308 0.01179 -0.0283 1.0000 0.1055
-3.750 -0.3207 0.02208 0.01083 -0.0272 1.0000 0.1231
-3.500 -0.3011 0.02110 0.00992 -0.0262 1.0000 0.1468
-3.250 -0.2817 0.01986 0.00907 -0.0255 1.0000 0.2095
-3.000 -0.2671 0.01804 0.00867 -0.0239 1.0000 0.4541
-2.750 -0.2564 0.01772 0.00893 -0.0197 1.0000 0.6287
-2.500 -0.2440 0.01770 0.00898 -0.0159 1.0000 0.7132
-2.250 -0.2347 0.01768 0.00900 -0.0110 1.0000 0.7872
-2.000 -0.2239 0.01759 0.00901 -0.0061 1.0000 0.8603
-1.750 -0.1798 0.01758 0.00886 -0.0080 1.0000 0.9368
-1.500 -0.1141 0.01758 0.00847 -0.0158 1.0000 0.9991
-1.250 -0.0955 0.01755 0.00823 -0.0161 0.9953 1.0000
-1.000 -0.0598 0.01769 0.00811 -0.0191 0.9858 1.0000
-0.750 -0.0239 0.01788 0.00807 -0.0219 0.9766 1.0000
-0.500 0.0152 0.01812 0.00808 -0.0252 0.9679 1.0000
-0.250 0.0529 0.01833 0.00813 -0.0280 0.9574 1.0000
0.000 0.0900 0.01854 0.00820 -0.0306 0.9465 1.0000
0.250 0.1274 0.01876 0.00831 -0.0331 0.9364 1.0000
0.500 0.1673 0.01899 0.00846 -0.0360 0.9277 1.0000
0.750 0.1998 0.01921 0.00863 -0.0375 0.9170 1.0000
1.000 0.2342 0.01945 0.00884 -0.0393 0.9071 1.0000
1.250 0.2738 0.01967 0.00906 -0.0419 0.8988 1.0000
1.500 0.3066 0.01989 0.00931 -0.0431 0.8879 1.0000
1.750 0.3390 0.02009 0.00957 -0.0442 0.8762 1.0000
2.000 0.3767 0.02011 0.00965 -0.0457 0.8612 1.0000
2.250 0.4143 0.01997 0.00959 -0.0466 0.8426 1.0000
2.500 0.4453 0.01988 0.00961 -0.0464 0.8216 1.0000
2.750 0.4772 0.01982 0.00964 -0.0463 0.8041 1.0000
3.000 0.5053 0.01986 0.00980 -0.0458 0.7868 1.0000
3.250 0.5318 0.01994 0.01005 -0.0451 0.7678 1.0000
3.500 0.5600 0.01994 0.01019 -0.0444 0.7490 1.0000
3.750 0.5858 0.01999 0.01039 -0.0434 0.7274 1.0000
4.000 0.6132 0.01996 0.01051 -0.0424 0.7048 1.0000
4.250 0.6385 0.02001 0.01078 -0.0411 0.6781 1.0000
4.500 0.6627 0.02008 0.01101 -0.0396 0.6464 1.0000
4.750 0.6865 0.02010 0.01113 -0.0379 0.6055 1.0000
5.000 0.7086 0.02016 0.01116 -0.0357 0.5505 1.0000
5.250 0.7296 0.02046 0.01126 -0.0335 0.4869 1.0000
5.500 0.7496 0.02110 0.01166 -0.0315 0.4276 1.0000
5.750 0.7670 0.02198 0.01231 -0.0297 0.3617 1.0000
6.000 0.7801 0.02322 0.01313 -0.0277 0.2836 1.0000
6.250 0.7942 0.02460 0.01412 -0.0262 0.2114 1.0000
6.500 0.8103 0.02603 0.01531 -0.0250 0.1482 1.0000
6.750 0.8254 0.02784 0.01680 -0.0236 0.1127 1.0000
7.000 0.8425 0.02968 0.01858 -0.0223 0.0949 1.0000
7.250 0.8614 0.03151 0.02041 -0.0210 0.0848 1.0000
7.500 0.8836 0.03325 0.02238 -0.0200 0.0762 1.0000
7.750 0.9039 0.03499 0.02428 -0.0191 0.0665 1.0000
8.000 0.9252 0.03707 0.02640 -0.0184 0.0609 1.0000
8.250 0.9498 0.03976 0.02946 -0.0176 0.0571 1.0000
8.500 0.9699 0.04253 0.03265 -0.0165 0.0528 1.0000
8.750 0.9842 0.04488 0.03517 -0.0157 0.0477 1.0000
9.000 0.9958 0.04817 0.03901 -0.0143 0.0447 1.0000
9.250 1.0037 0.05196 0.04332 -0.0127 0.0432 1.0000
9.500 1.0062 0.05586 0.04769 -0.0110 0.0420 1.0000
9.750 1.0036 0.05967 0.05189 -0.0094 0.0409 1.0000
10.000 0.9968 0.06337 0.05591 -0.0079 0.0399 1.0000
10.250 0.9858 0.06681 0.05958 -0.0064 0.0391 1.0000
10.500 0.9726 0.07049 0.06344 -0.0056 0.0384 1.0000
10.750 0.9464 0.07603 0.06925 -0.0065 0.0394 1.0000
11.000 0.9198 0.08259 0.07600 -0.0095 0.0404 1.0000
11.250 0.8937 0.09047 0.08400 -0.0145 0.0418 1.0000
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Polar data table (+)
Polar graphs
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