HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il) Reynolds number: 50,000 Max Cl/Cd: 36.13 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3011-il-50000.txt Download as CSV file: xf-hq3011-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/11 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 -0.3450 0.10170 0.09514 -0.0274 1.0000 0.2673
-8.250 -0.3442 0.09923 0.09276 -0.0260 1.0000 0.2820
-8.000 -0.3442 0.09679 0.09041 -0.0243 1.0000 0.2972
-7.750 -0.3449 0.09448 0.08819 -0.0224 1.0000 0.3124
-7.500 -0.3474 0.09235 0.08617 -0.0201 1.0000 0.3282
-7.250 -0.3539 0.09059 0.08452 -0.0174 1.0000 0.3446
-7.000 -0.3660 0.08935 0.08342 -0.0140 1.0000 0.3607
-6.750 -0.3802 0.08832 0.08252 -0.0100 1.0000 0.3759
-6.500 -0.3608 0.08446 0.07867 -0.0076 1.0000 0.3983
-6.250 -0.3750 0.08357 0.07790 -0.0031 1.0000 0.4176
-6.000 -0.4023 0.08357 0.07807 0.0026 1.0000 0.4341
-5.750 -0.4010 0.08158 0.07614 0.0069 1.0000 0.4630
-4.750 -0.4233 0.04661 0.03878 -0.0443 1.0000 0.1300
-4.500 -0.4029 0.04277 0.03480 -0.0443 1.0000 0.1263
-4.250 -0.3784 0.03948 0.03095 -0.0449 1.0000 0.1259
-4.000 -0.3518 0.03679 0.02751 -0.0453 1.0000 0.1292
-3.750 -0.3268 0.03412 0.02455 -0.0452 1.0000 0.1332
-3.500 -0.3014 0.03242 0.02231 -0.0449 1.0000 0.1446
-3.250 -0.2778 0.03059 0.02038 -0.0444 1.0000 0.1575
-3.000 -0.2538 0.02913 0.01870 -0.0436 1.0000 0.1734
-2.750 -0.2317 0.02781 0.01751 -0.0427 1.0000 0.1935
-2.500 -0.2091 0.02679 0.01641 -0.0415 1.0000 0.2159
-2.250 -0.1855 0.02569 0.01554 -0.0409 1.0000 0.2559
-2.000 -0.1628 0.02321 0.01526 -0.0394 1.0000 0.5671
-1.750 -0.1758 0.02300 0.01584 -0.0275 1.0000 0.7985
-1.500 -0.1583 0.02244 0.01534 -0.0230 1.0000 0.9837
-1.250 -0.1347 0.02258 0.01500 -0.0244 1.0000 1.0000
-1.000 -0.1102 0.02287 0.01487 -0.0258 1.0000 1.0000
-0.750 -0.0858 0.02325 0.01488 -0.0270 1.0000 1.0000
-0.500 -0.0620 0.02370 0.01500 -0.0281 1.0000 1.0000
-0.250 -0.0390 0.02421 0.01520 -0.0289 1.0000 1.0000
0.000 -0.0167 0.02477 0.01551 -0.0295 1.0000 1.0000
0.250 0.0049 0.02538 0.01590 -0.0301 1.0000 1.0000
0.500 0.0260 0.02605 0.01635 -0.0305 1.0000 1.0000
0.750 0.0466 0.02676 0.01688 -0.0309 1.0000 1.0000
1.000 0.0713 0.02764 0.01761 -0.0322 0.9976 1.0000
1.250 0.1208 0.02931 0.01908 -0.0379 0.9838 1.0000
1.500 0.1673 0.03084 0.02045 -0.0430 0.9696 1.0000
1.750 0.2101 0.03219 0.02168 -0.0473 0.9547 1.0000
2.000 0.2483 0.03332 0.02273 -0.0506 0.9383 1.0000
2.250 0.2865 0.03442 0.02378 -0.0537 0.9209 1.0000
2.500 0.3274 0.03551 0.02484 -0.0570 0.9028 1.0000
2.750 0.3730 0.03660 0.02592 -0.0609 0.8849 1.0000
3.000 0.4066 0.03747 0.02679 -0.0626 0.8658 1.0000
3.250 0.4419 0.03830 0.02765 -0.0645 0.8469 1.0000
3.500 0.4840 0.03904 0.02846 -0.0671 0.8286 1.0000
3.750 0.5205 0.03970 0.02918 -0.0687 0.8098 1.0000
4.000 0.5524 0.04029 0.02985 -0.0695 0.7895 1.0000
4.250 0.5991 0.04046 0.03017 -0.0718 0.7708 1.0000
4.500 0.6285 0.04087 0.03067 -0.0718 0.7492 1.0000
4.750 0.6742 0.04057 0.03053 -0.0732 0.7293 1.0000
5.000 0.7129 0.04027 0.03042 -0.0734 0.7080 1.0000
5.250 0.7608 0.03923 0.02959 -0.0741 0.6875 1.0000
5.500 0.8260 0.03685 0.02751 -0.0756 0.6700 1.0000
5.750 0.8573 0.03621 0.02704 -0.0742 0.6456 1.0000
6.000 0.9089 0.03416 0.02520 -0.0740 0.6232 1.0000
6.250 0.9638 0.03182 0.02305 -0.0740 0.5982 1.0000
6.500 0.9992 0.03087 0.02219 -0.0727 0.5680 1.0000
6.750 1.0295 0.03043 0.02179 -0.0711 0.5357 1.0000
7.000 1.0604 0.03020 0.02156 -0.0697 0.5030 1.0000
7.250 1.0917 0.03022 0.02145 -0.0685 0.4700 1.0000
7.500 1.1143 0.03097 0.02214 -0.0669 0.4383 1.0000
7.750 1.1357 0.03194 0.02307 -0.0652 0.4079 1.0000
8.000 1.1561 0.03302 0.02410 -0.0636 0.3783 1.0000
8.250 1.1756 0.03421 0.02528 -0.0619 0.3497 1.0000
8.500 1.1945 0.03552 0.02654 -0.0602 0.3221 1.0000
8.750 1.2129 0.03695 0.02788 -0.0585 0.2949 1.0000
9.000 1.2320 0.03853 0.02933 -0.0570 0.2684 1.0000
9.250 1.2423 0.04056 0.03158 -0.0546 0.2460 1.0000
9.500 1.2590 0.04247 0.03343 -0.0530 0.2239 1.0000
9.750 1.2694 0.04479 0.03595 -0.0508 0.2061 1.0000
10.000 1.2817 0.04739 0.03878 -0.0489 0.1912 1.0000
10.250 1.2912 0.04986 0.04143 -0.0468 0.1776 1.0000
10.500 1.3007 0.05271 0.04446 -0.0448 0.1666 1.0000
10.750 1.3178 0.05578 0.04756 -0.0438 0.1562 1.0000
11.000 1.3016 0.05951 0.05190 -0.0398 0.1522 1.0000
11.250 1.3135 0.06218 0.05457 -0.0384 0.1419 1.0000
11.500 1.2915 0.06626 0.05911 -0.0346 0.1402 1.0000
11.750 1.2668 0.07032 0.06348 -0.0311 0.1396 1.0000
12.000 1.2388 0.07489 0.06830 -0.0285 0.1397 1.0000
12.250 1.2086 0.08016 0.07378 -0.0274 0.1403 1.0000
12.500 1.1777 0.08631 0.08008 -0.0276 0.1413 1.0000
12.750 1.1474 0.09341 0.08728 -0.0292 0.1424 1.0000
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Polar data table (+)
Polar graphs
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