HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 100,000 Max Cl/Cd: 50.5 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1511-il-100000.txt Download as CSV file: xf-hq1511-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/11 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4831 0.11132 0.10622 -0.0193 1.0000 0.1061
-10.250 -0.5030 0.10729 0.10230 -0.0252 1.0000 0.1114
-10.000 -0.5149 0.10199 0.09710 -0.0291 1.0000 0.1130
-9.750 -0.4856 0.09924 0.09430 -0.0245 1.0000 0.1169
-9.500 -0.4854 0.09578 0.09088 -0.0260 1.0000 0.1226
-9.250 -0.5289 0.08977 0.08505 -0.0365 1.0000 0.1261
-9.000 -0.4873 0.08808 0.08329 -0.0284 1.0000 0.1337
-8.750 -0.5043 0.08343 0.07876 -0.0329 1.0000 0.1385
-8.500 -0.4996 0.08006 0.07543 -0.0321 1.0000 0.1459
-8.250 -0.5984 0.05845 0.05333 -0.0483 1.0000 0.0677
-8.000 -0.6221 0.05126 0.04541 -0.0466 1.0000 0.0567
-7.750 -0.6194 0.04722 0.04125 -0.0450 1.0000 0.0553
-7.500 -0.6178 0.04360 0.03737 -0.0428 1.0000 0.0543
-7.250 -0.6153 0.04041 0.03383 -0.0403 1.0000 0.0544
-7.000 -0.6106 0.03762 0.03063 -0.0376 1.0000 0.0551
-6.750 -0.6035 0.03533 0.02781 -0.0348 1.0000 0.0567
-6.500 -0.5943 0.03254 0.02457 -0.0325 1.0000 0.0582
-6.250 -0.5813 0.02994 0.02185 -0.0308 1.0000 0.0608
-6.000 -0.5658 0.02808 0.01979 -0.0289 1.0000 0.0654
-5.750 -0.5488 0.02588 0.01718 -0.0271 1.0000 0.0723
-5.500 -0.5329 0.02527 0.01637 -0.0255 1.0000 0.0842
-5.250 -0.5162 0.02424 0.01532 -0.0244 1.0000 0.0973
-5.000 -0.4969 0.02272 0.01384 -0.0234 1.0000 0.1062
-4.750 -0.4760 0.02173 0.01264 -0.0221 1.0000 0.1126
-4.500 -0.4565 0.02063 0.01168 -0.0210 1.0000 0.1222
-4.250 -0.4371 0.01973 0.01085 -0.0199 1.0000 0.1329
-4.000 -0.4181 0.01897 0.01018 -0.0187 1.0000 0.1463
-3.750 -0.3989 0.01833 0.00965 -0.0176 1.0000 0.1699
-3.500 -0.3801 0.01732 0.00905 -0.0167 1.0000 0.2245
-3.250 -0.3690 0.01539 0.00897 -0.0143 1.0000 0.5313
-3.000 -0.3449 0.01574 0.00957 -0.0130 0.9959 0.6495
-2.750 -0.3146 0.01626 0.01005 -0.0129 0.9890 0.7072
-2.500 -0.2823 0.01678 0.01051 -0.0131 0.9824 0.7489
-2.250 -0.2539 0.01714 0.01086 -0.0124 0.9737 0.7834
-2.000 -0.2266 0.01747 0.01116 -0.0112 0.9649 0.8188
-1.750 -0.1979 0.01777 0.01143 -0.0101 0.9569 0.8543
-1.500 -0.1754 0.01785 0.01147 -0.0084 0.9481 0.8815
-1.250 -0.1348 0.01804 0.01155 -0.0106 0.9425 0.9011
-1.000 -0.1016 0.01815 0.01159 -0.0115 0.9351 0.9231
-0.750 -0.0444 0.01844 0.01178 -0.0169 0.9306 0.9443
-0.500 0.0262 0.01872 0.01193 -0.0252 0.9278 0.9584
-0.250 0.0875 0.01887 0.01199 -0.0322 0.9226 0.9702
0.000 0.1550 0.01886 0.01192 -0.0404 0.9171 0.9776
0.250 0.2268 0.01869 0.01170 -0.0489 0.9126 0.9826
0.500 0.2867 0.01841 0.01140 -0.0554 0.9027 0.9893
0.750 0.3504 0.01788 0.01088 -0.0620 0.8929 0.9943
1.000 0.4134 0.01721 0.01021 -0.0682 0.8836 0.9995
1.250 0.4378 0.01700 0.01002 -0.0678 0.8699 1.0000
1.500 0.4571 0.01687 0.00992 -0.0664 0.8561 1.0000
1.750 0.4734 0.01682 0.00988 -0.0645 0.8427 1.0000
2.000 0.4877 0.01682 0.00990 -0.0623 0.8295 1.0000
2.250 0.5017 0.01680 0.00991 -0.0599 0.8164 1.0000
2.500 0.5172 0.01675 0.00987 -0.0575 0.8033 1.0000
2.750 0.5357 0.01666 0.00980 -0.0555 0.7899 1.0000
3.000 0.5571 0.01654 0.00969 -0.0538 0.7762 1.0000
3.250 0.5802 0.01642 0.00958 -0.0523 0.7616 1.0000
3.500 0.6039 0.01632 0.00953 -0.0509 0.7458 1.0000
3.750 0.6280 0.01621 0.00945 -0.0496 0.7285 1.0000
4.000 0.6533 0.01603 0.00929 -0.0482 0.7096 1.0000
4.250 0.6799 0.01575 0.00901 -0.0469 0.6892 1.0000
4.500 0.7036 0.01548 0.00875 -0.0451 0.6605 1.0000
4.750 0.7257 0.01528 0.00853 -0.0431 0.6245 1.0000
5.000 0.7485 0.01518 0.00834 -0.0413 0.5841 1.0000
5.250 0.7702 0.01530 0.00834 -0.0395 0.5367 1.0000
5.500 0.7913 0.01567 0.00846 -0.0379 0.4887 1.0000
5.750 0.8121 0.01627 0.00882 -0.0364 0.4464 1.0000
6.000 0.8330 0.01695 0.00929 -0.0351 0.4101 1.0000
6.250 0.8535 0.01757 0.00985 -0.0339 0.3753 1.0000
6.500 0.8732 0.01820 0.01038 -0.0326 0.3415 1.0000
6.750 0.8914 0.01902 0.01098 -0.0311 0.3069 1.0000
7.000 0.9083 0.01995 0.01179 -0.0296 0.2676 1.0000
7.250 0.9234 0.02098 0.01266 -0.0278 0.2267 1.0000
7.500 0.9377 0.02207 0.01360 -0.0260 0.1868 1.0000
7.750 0.9522 0.02307 0.01445 -0.0242 0.1511 1.0000
8.000 0.9660 0.02460 0.01574 -0.0224 0.1246 1.0000
8.250 0.9820 0.02654 0.01747 -0.0209 0.1062 1.0000
8.500 1.0015 0.02843 0.01928 -0.0199 0.0929 1.0000
8.750 1.0221 0.03009 0.02096 -0.0189 0.0833 1.0000
9.000 1.0464 0.03239 0.02345 -0.0184 0.0769 1.0000
9.250 1.0674 0.03420 0.02532 -0.0176 0.0710 1.0000
9.500 1.0894 0.03698 0.02826 -0.0171 0.0669 1.0000
9.750 1.1066 0.03955 0.03125 -0.0157 0.0643 1.0000
10.000 1.1213 0.04220 0.03423 -0.0142 0.0620 1.0000
10.250 1.1357 0.04454 0.03671 -0.0131 0.0592 1.0000
10.500 1.1476 0.04912 0.04142 -0.0125 0.0568 1.0000
10.750 1.1474 0.05212 0.04490 -0.0099 0.0563 1.0000
11.000 1.1431 0.05559 0.04879 -0.0072 0.0560 1.0000
11.250 1.1348 0.05932 0.05287 -0.0047 0.0560 1.0000
11.500 1.1215 0.06299 0.05683 -0.0019 0.0561 1.0000
11.750 1.1057 0.06688 0.06095 0.0004 0.0563 1.0000
12.000 1.0878 0.07110 0.06538 0.0018 0.0565 1.0000
12.250 1.0714 0.07614 0.07059 0.0022 0.0568 1.0000
12.500 1.0480 0.07964 0.07434 0.0021 0.0572 1.0000
12.750 0.9370 0.09476 0.09002 -0.0097 0.0618 1.0000
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Polar data table (+)
Polar graphs
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