HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8 AIRFOIL (hq158-il) Reynolds number: 100,000 Max Cl/Cd: 51.93 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq158-il-100000.txt Download as CSV file: xf-hq158-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4999 0.09357 0.08881 -0.0167 1.0000 0.0889
-8.250 -0.5107 0.09000 0.08535 -0.0216 1.0000 0.0920
-8.000 -0.5225 0.08591 0.08136 -0.0273 1.0000 0.0926
-7.750 -0.5065 0.08242 0.07787 -0.0224 1.0000 0.0984
-7.500 -0.5096 0.07847 0.07399 -0.0260 1.0000 0.1032
-7.250 -0.5240 0.07361 0.06900 -0.0359 1.0000 0.1063
-7.000 -0.5086 0.06984 0.06539 -0.0315 1.0000 0.1123
-6.750 -0.5217 0.06679 0.06185 -0.0397 1.0000 0.1205
-6.500 -0.5017 0.06187 0.05734 -0.0351 1.0000 0.1257
-6.250 -0.4990 0.05793 0.05326 -0.0372 1.0000 0.1364
-5.750 -0.4827 0.05151 0.04668 -0.0368 1.0000 0.1632
-5.500 -0.4721 0.04851 0.04363 -0.0355 1.0000 0.1780
-5.250 -0.4609 0.04582 0.04095 -0.0340 1.0000 0.1947
-5.000 -0.4213 0.03357 0.02666 -0.0370 1.0000 0.0637
-4.750 -0.3995 0.03044 0.02260 -0.0348 1.0000 0.0539
-4.500 -0.3800 0.02728 0.01911 -0.0334 1.0000 0.0524
-4.250 -0.3590 0.02488 0.01631 -0.0319 1.0000 0.0524
-4.000 -0.3385 0.02265 0.01385 -0.0307 1.0000 0.0569
-3.750 -0.3167 0.02111 0.01218 -0.0294 1.0000 0.0619
-3.500 -0.2935 0.01963 0.01043 -0.0278 1.0000 0.0662
-3.250 -0.2722 0.01802 0.00890 -0.0266 1.0000 0.0779
-3.000 -0.2518 0.01660 0.00765 -0.0252 1.0000 0.1042
-2.750 -0.2316 0.01507 0.00655 -0.0241 1.0000 0.1713
-2.500 -0.2255 0.01254 0.00656 -0.0195 1.0000 0.6879
-2.250 -0.2160 0.01251 0.00662 -0.0146 1.0000 0.7865
-2.000 -0.2051 0.01239 0.00654 -0.0101 1.0000 0.8550
-1.750 -0.1619 0.01226 0.00637 -0.0117 1.0000 0.9494
-1.500 -0.1172 0.01222 0.00604 -0.0162 1.0000 1.0000
-1.250 -0.1001 0.01226 0.00586 -0.0157 1.0000 1.0000
-1.000 -0.0799 0.01239 0.00574 -0.0155 1.0000 1.0000
-0.750 -0.0589 0.01257 0.00574 -0.0154 1.0000 1.0000
-0.500 -0.0377 0.01279 0.00580 -0.0152 1.0000 1.0000
-0.250 -0.0166 0.01306 0.00592 -0.0150 1.0000 1.0000
0.000 0.0300 0.01351 0.00621 -0.0196 0.9910 1.0000
0.250 0.0767 0.01398 0.00657 -0.0242 0.9825 1.0000
0.500 0.1197 0.01432 0.00684 -0.0279 0.9724 1.0000
0.750 0.1640 0.01465 0.00713 -0.0317 0.9622 1.0000
1.000 0.2106 0.01494 0.00739 -0.0359 0.9521 1.0000
1.250 0.2598 0.01512 0.00759 -0.0403 0.9416 1.0000
1.500 0.3064 0.01518 0.00770 -0.0441 0.9289 1.0000
1.750 0.3544 0.01514 0.00776 -0.0478 0.9163 1.0000
2.000 0.3997 0.01507 0.00778 -0.0509 0.9038 1.0000
2.250 0.4429 0.01491 0.00772 -0.0533 0.8900 1.0000
2.500 0.4815 0.01475 0.00768 -0.0546 0.8756 1.0000
2.750 0.5170 0.01456 0.00766 -0.0551 0.8604 1.0000
3.000 0.5453 0.01446 0.00767 -0.0542 0.8415 1.0000
3.250 0.5737 0.01425 0.00757 -0.0530 0.8213 1.0000
3.500 0.5991 0.01406 0.00749 -0.0512 0.7973 1.0000
3.750 0.6237 0.01382 0.00738 -0.0491 0.7690 1.0000
4.000 0.6472 0.01357 0.00718 -0.0466 0.7338 1.0000
4.250 0.6692 0.01340 0.00703 -0.0441 0.6868 1.0000
4.500 0.6906 0.01339 0.00692 -0.0415 0.6240 1.0000
4.750 0.7104 0.01368 0.00694 -0.0390 0.5393 1.0000
5.000 0.7285 0.01441 0.00721 -0.0367 0.4449 1.0000
5.250 0.7466 0.01538 0.00784 -0.0349 0.3606 1.0000
5.500 0.7632 0.01666 0.00868 -0.0331 0.2739 1.0000
5.750 0.7776 0.01841 0.00974 -0.0312 0.1715 1.0000
6.000 0.7951 0.02024 0.01120 -0.0295 0.1240 1.0000
6.250 0.8148 0.02195 0.01277 -0.0281 0.0978 1.0000
6.500 0.8365 0.02402 0.01475 -0.0269 0.0804 1.0000
6.750 0.8570 0.02609 0.01684 -0.0258 0.0613 1.0000
7.000 0.8800 0.02909 0.01992 -0.0247 0.0506 1.0000
7.250 0.9029 0.03138 0.02263 -0.0235 0.0441 1.0000
7.500 0.9214 0.03489 0.02635 -0.0225 0.0392 1.0000
7.750 0.9394 0.03818 0.03020 -0.0208 0.0384 1.0000
8.000 0.9531 0.04213 0.03470 -0.0190 0.0383 1.0000
8.250 0.9627 0.04652 0.03957 -0.0171 0.0387 1.0000
8.500 0.9686 0.05154 0.04497 -0.0156 0.0395 1.0000
8.750 0.9787 0.05507 0.04892 -0.0138 0.0413 1.0000
9.000 0.9546 0.06196 0.05674 -0.0107 0.0465 1.0000
9.250 0.9439 0.06709 0.06212 -0.0096 0.0489 1.0000
9.500 0.9259 0.07277 0.06810 -0.0085 0.0555 1.0000
9.750 0.8953 0.07797 0.07346 -0.0092 0.0567 1.0000
10.000 0.8690 0.08441 0.07998 -0.0130 0.0574 1.0000
10.250 0.7768 0.08142 0.07724 -0.0111 0.0486 1.0000
10.500 0.7555 0.08975 0.08561 -0.0160 0.0496 1.0000
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Polar data table (+)
Polar graphs
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