HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 50,000 Max Cl/Cd: 35.23 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq159b-il-50000.txt Download as CSV file: xf-hq159b-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4754 0.09945 0.09265 -0.0013 1.0000 0.3123
-8.250 -0.4735 0.09652 0.08977 -0.0010 1.0000 0.3289
-8.000 -0.4805 0.09440 0.08775 -0.0008 1.0000 0.3456
-7.750 -0.4594 0.09001 0.08335 0.0010 1.0000 0.3707
-7.500 -0.4485 0.08661 0.07997 0.0025 1.0000 0.3960
-7.000 -0.4378 0.08046 0.07389 0.0046 1.0000 0.4351
-6.750 -0.4316 0.07715 0.07063 0.0054 1.0000 0.4505
-6.500 -0.5369 0.05724 0.05022 -0.0383 1.0000 0.1618
-6.250 -0.5226 0.05124 0.04403 -0.0387 1.0000 0.1419
-6.000 -0.5109 0.04605 0.03827 -0.0392 1.0000 0.1292
-5.750 -0.4967 0.04193 0.03365 -0.0388 1.0000 0.1259
-5.500 -0.4802 0.03863 0.02992 -0.0379 1.0000 0.1281
-5.250 -0.4612 0.03534 0.02610 -0.0368 1.0000 0.1283
-5.000 -0.4404 0.03247 0.02270 -0.0356 1.0000 0.1310
-4.750 -0.4200 0.03013 0.02011 -0.0344 1.0000 0.1403
-4.500 -0.3968 0.02795 0.01746 -0.0331 1.0000 0.1470
-4.250 -0.3748 0.02616 0.01550 -0.0317 1.0000 0.1605
-4.000 -0.3521 0.02453 0.01377 -0.0303 1.0000 0.1763
-3.750 -0.3302 0.02293 0.01232 -0.0286 1.0000 0.1974
-3.500 -0.3090 0.02141 0.01099 -0.0272 1.0000 0.2374
-3.250 -0.2915 0.01880 0.00959 -0.0256 1.0000 0.3647
-3.000 -0.3049 0.01795 0.01062 -0.0130 1.0000 0.7441
-2.750 -0.0690 0.01903 0.01008 -0.0362 1.0000 1.0000
-2.500 -0.0698 0.01867 0.00967 -0.0335 1.0000 1.0000
-2.250 -0.0750 0.01838 0.00934 -0.0299 1.0000 1.0000
-2.000 -0.0845 0.01813 0.00905 -0.0256 1.0000 1.0000
-1.750 -0.0967 0.01786 0.00875 -0.0209 1.0000 1.0000
-1.500 -0.1073 0.01758 0.00842 -0.0164 1.0000 1.0000
-1.250 -0.1080 0.01741 0.00810 -0.0133 1.0000 1.0000
-1.000 -0.0969 0.01740 0.00789 -0.0120 1.0000 1.0000
-0.750 -0.0803 0.01748 0.00778 -0.0114 1.0000 1.0000
-0.500 -0.0616 0.01765 0.00773 -0.0111 1.0000 1.0000
-0.250 -0.0420 0.01787 0.00777 -0.0109 1.0000 1.0000
0.000 -0.0219 0.01813 0.00789 -0.0108 1.0000 1.0000
0.250 -0.0016 0.01844 0.00807 -0.0106 1.0000 1.0000
0.500 0.0186 0.01879 0.00829 -0.0105 1.0000 1.0000
0.750 0.0388 0.01918 0.00859 -0.0104 1.0000 1.0000
1.000 0.0588 0.01961 0.00895 -0.0103 1.0000 1.0000
1.250 0.0786 0.02009 0.00937 -0.0103 1.0000 1.0000
1.500 0.0981 0.02062 0.00986 -0.0102 1.0000 1.0000
1.750 0.1173 0.02119 0.01041 -0.0103 1.0000 1.0000
2.000 0.1361 0.02183 0.01103 -0.0103 1.0000 1.0000
2.250 0.1545 0.02252 0.01174 -0.0104 1.0000 1.0000
2.500 0.1954 0.02370 0.01299 -0.0149 0.9885 1.0000
2.750 0.2683 0.02524 0.01470 -0.0247 0.9590 1.0000
3.000 0.3299 0.02629 0.01594 -0.0317 0.9316 1.0000
3.250 0.3841 0.02708 0.01698 -0.0370 0.9059 1.0000
3.500 0.4383 0.02764 0.01781 -0.0417 0.8798 1.0000
3.750 0.4940 0.02794 0.01842 -0.0461 0.8524 1.0000
4.000 0.5517 0.02785 0.01875 -0.0499 0.8226 1.0000
4.250 0.6050 0.02734 0.01863 -0.0518 0.7908 1.0000
4.500 0.6564 0.02630 0.01802 -0.0521 0.7565 1.0000
4.750 0.6959 0.02493 0.01695 -0.0495 0.7138 1.0000
5.000 0.7262 0.02363 0.01581 -0.0453 0.6629 1.0000
5.250 0.7520 0.02277 0.01497 -0.0413 0.6068 1.0000
5.500 0.7739 0.02236 0.01448 -0.0373 0.5427 1.0000
5.750 0.7882 0.02237 0.01402 -0.0326 0.4599 1.0000
6.000 0.7967 0.02336 0.01441 -0.0285 0.3634 1.0000
6.250 0.8042 0.02594 0.01599 -0.0249 0.2496 1.0000
6.500 0.8235 0.02881 0.01827 -0.0230 0.1811 1.0000
6.750 0.8467 0.03085 0.02022 -0.0218 0.1508 1.0000
7.000 0.8755 0.03348 0.02300 -0.0211 0.1356 1.0000
7.250 0.9018 0.03632 0.02595 -0.0205 0.1249 1.0000
7.500 0.9248 0.03905 0.02881 -0.0197 0.1143 1.0000
7.750 0.9445 0.04285 0.03321 -0.0183 0.1112 1.0000
8.000 0.9585 0.04676 0.03777 -0.0166 0.1084 1.0000
8.250 0.9714 0.05026 0.04164 -0.0153 0.1036 1.0000
8.500 0.9881 0.05482 0.04617 -0.0147 0.1002 1.0000
8.750 0.9826 0.05928 0.05157 -0.0123 0.1025 1.0000
9.000 0.9687 0.06500 0.05791 -0.0109 0.1058 1.0000
9.250 0.9551 0.07051 0.06376 -0.0101 0.1085 1.0000
9.500 0.9443 0.07583 0.06926 -0.0098 0.1109 1.0000
9.750 0.9570 0.08175 0.07521 -0.0098 0.1136 1.0000
10.000 0.8786 0.08786 0.08154 -0.0134 0.1179 1.0000
10.250 0.8514 0.09646 0.09010 -0.0191 0.1238 1.0000
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Polar data table (+)
Polar graphs
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