HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/9 AIRFOIL (hq09-il) Reynolds number: 100,000 Max Cl/Cd: 33.41 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq09-il-100000-n5.txt Download as CSV file: xf-hq09-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/9 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6829 0.08853 0.08378 0.0012 1.0000 0.0160
-9.500 -0.6932 0.08038 0.07579 -0.0045 1.0000 0.0151
-9.250 -0.7368 0.06447 0.05972 -0.0154 1.0000 0.0117
-9.000 -0.7546 0.05976 0.05485 -0.0163 1.0000 0.0115
-8.750 -0.7664 0.05528 0.05014 -0.0164 1.0000 0.0116
-8.500 -0.7720 0.05094 0.04551 -0.0161 1.0000 0.0117
-8.250 -0.7720 0.04697 0.04123 -0.0155 1.0000 0.0119
-8.000 -0.7616 0.04539 0.03950 -0.0152 1.0000 0.0136
-7.750 -0.7516 0.04254 0.03634 -0.0145 1.0000 0.0151
-7.500 -0.7409 0.03894 0.03224 -0.0135 1.0000 0.0168
-7.250 -0.7273 0.03509 0.02776 -0.0121 1.0000 0.0186
-7.000 -0.7096 0.03174 0.02365 -0.0107 1.0000 0.0201
-6.750 -0.6924 0.02893 0.02064 -0.0100 1.0000 0.0236
-6.500 -0.6705 0.02736 0.01870 -0.0092 1.0000 0.0294
-6.250 -0.6475 0.02497 0.01595 -0.0082 1.0000 0.0325
-6.000 -0.6254 0.02372 0.01464 -0.0077 1.0000 0.0381
-5.750 -0.6017 0.02211 0.01284 -0.0067 1.0000 0.0406
-5.500 -0.5786 0.02078 0.01133 -0.0058 1.0000 0.0432
-5.250 -0.5575 0.01943 0.00996 -0.0048 1.0000 0.0467
-5.000 -0.5352 0.01846 0.00890 -0.0039 1.0000 0.0524
-4.750 -0.5129 0.01757 0.00798 -0.0031 1.0000 0.0636
-4.500 -0.4906 0.01667 0.00699 -0.0022 1.0000 0.0820
-4.250 -0.4695 0.01560 0.00614 -0.0013 1.0000 0.1169
-4.000 -0.4497 0.01445 0.00555 -0.0004 1.0000 0.2203
-3.750 -0.4318 0.01327 0.00507 0.0008 1.0000 0.3512
-3.500 -0.4145 0.01240 0.00486 0.0027 1.0000 0.4942
-3.250 -0.3956 0.01201 0.00483 0.0048 1.0000 0.5959
-3.000 -0.3757 0.01184 0.00478 0.0068 1.0000 0.6603
-2.750 -0.3568 0.01174 0.00478 0.0091 1.0000 0.7126
-2.500 -0.3377 0.01168 0.00469 0.0113 1.0000 0.7499
-2.250 -0.3172 0.01162 0.00460 0.0130 1.0000 0.7732
-2.000 -0.2964 0.01156 0.00448 0.0143 1.0000 0.7927
-1.750 -0.2762 0.01152 0.00441 0.0158 1.0000 0.8103
-1.500 -0.2413 0.01153 0.00436 0.0143 0.9895 0.8303
-1.250 -0.2045 0.01158 0.00434 0.0127 0.9802 0.8534
-1.000 -0.1674 0.01162 0.00437 0.0112 0.9708 0.8764
-0.750 -0.1263 0.01167 0.00439 0.0087 0.9617 0.8941
-0.500 -0.0833 0.01169 0.00439 0.0057 0.9519 0.9078
-0.250 -0.0405 0.01170 0.00436 0.0026 0.9413 0.9190
0.000 0.0000 0.01169 0.00435 0.0000 0.9299 0.9299
0.250 0.0406 0.01170 0.00436 -0.0026 0.9191 0.9413
0.500 0.0833 0.01169 0.00439 -0.0057 0.9079 0.9519
0.750 0.1263 0.01167 0.00439 -0.0087 0.8941 0.9617
1.000 0.1673 0.01162 0.00437 -0.0112 0.8765 0.9708
1.250 0.2045 0.01158 0.00434 -0.0127 0.8535 0.9802
1.500 0.2413 0.01153 0.00436 -0.0143 0.8304 0.9895
1.750 0.2761 0.01152 0.00440 -0.0158 0.8103 1.0000
2.000 0.2963 0.01155 0.00447 -0.0143 0.7927 1.0000
2.250 0.3170 0.01161 0.00460 -0.0129 0.7732 1.0000
2.500 0.3375 0.01168 0.00469 -0.0113 0.7500 1.0000
2.750 0.3566 0.01174 0.00478 -0.0091 0.7127 1.0000
3.000 0.3755 0.01184 0.00478 -0.0068 0.6604 1.0000
3.250 0.3955 0.01201 0.00483 -0.0048 0.5959 1.0000
3.500 0.4143 0.01240 0.00486 -0.0027 0.4947 1.0000
3.750 0.4317 0.01327 0.00507 -0.0008 0.3513 1.0000
4.000 0.4497 0.01444 0.00555 0.0005 0.2211 1.0000
4.250 0.4694 0.01560 0.00615 0.0013 0.1167 1.0000
4.500 0.4905 0.01667 0.00699 0.0022 0.0819 1.0000
4.750 0.5128 0.01757 0.00799 0.0031 0.0636 1.0000
5.000 0.5352 0.01846 0.00889 0.0039 0.0524 1.0000
5.250 0.5575 0.01942 0.00995 0.0048 0.0469 1.0000
5.500 0.5786 0.02078 0.01132 0.0057 0.0432 1.0000
5.750 0.6018 0.02210 0.01283 0.0067 0.0407 1.0000
6.000 0.6254 0.02372 0.01465 0.0077 0.0381 1.0000
6.250 0.6476 0.02498 0.01596 0.0082 0.0325 1.0000
6.500 0.6706 0.02737 0.01871 0.0092 0.0294 1.0000
6.750 0.6925 0.02891 0.02061 0.0100 0.0235 1.0000
7.000 0.7097 0.03175 0.02366 0.0107 0.0201 1.0000
7.250 0.7275 0.03514 0.02782 0.0121 0.0186 1.0000
7.500 0.7412 0.03894 0.03225 0.0134 0.0168 1.0000
7.750 0.7519 0.04259 0.03639 0.0144 0.0152 1.0000
8.000 0.7609 0.04575 0.03990 0.0151 0.0138 1.0000
8.250 0.7703 0.04780 0.04214 0.0155 0.0123 1.0000
8.500 0.7722 0.05089 0.04544 0.0159 0.0115 1.0000
8.750 0.7666 0.05530 0.05015 0.0162 0.0115 1.0000
9.000 0.7546 0.05978 0.05487 0.0162 0.0114 1.0000
9.250 0.7344 0.06536 0.06065 0.0149 0.0119 1.0000
9.500 0.6937 0.08053 0.07593 0.0043 0.0150 1.0000
9.750 0.6835 0.08859 0.08384 -0.0013 0.0163 1.0000
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Polar data table (+)
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