HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 50,000 Max Cl/Cd: 27.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq010-il-50000-n5.txt Download as CSV file: xf-hq010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7094 0.09429 0.08749 -0.0095 1.0000 0.0531
-10.750 -0.7244 0.08695 0.08016 -0.0145 1.0000 0.0526
-10.500 -0.7431 0.08022 0.07341 -0.0190 1.0000 0.0521
-10.250 -0.7636 0.07447 0.06759 -0.0222 1.0000 0.0517
-10.000 -0.7835 0.06970 0.06271 -0.0235 1.0000 0.0513
-9.750 -0.8022 0.06557 0.05841 -0.0232 1.0000 0.0513
-9.500 -0.8153 0.06130 0.05387 -0.0226 1.0000 0.0515
-9.250 -0.8228 0.05706 0.04927 -0.0217 1.0000 0.0518
-9.000 -0.8252 0.05291 0.04468 -0.0205 1.0000 0.0525
-8.750 -0.8220 0.04901 0.04024 -0.0192 1.0000 0.0533
-8.500 -0.8136 0.04543 0.03606 -0.0179 1.0000 0.0545
-8.250 -0.7988 0.04251 0.03302 -0.0171 1.0000 0.0569
-8.000 -0.7824 0.04045 0.03068 -0.0163 1.0000 0.0614
-7.750 -0.7644 0.03798 0.02773 -0.0153 1.0000 0.0654
-7.500 -0.7423 0.03544 0.02480 -0.0144 1.0000 0.0682
-7.250 -0.7194 0.03337 0.02269 -0.0138 1.0000 0.0719
-7.000 -0.6958 0.03162 0.02072 -0.0130 1.0000 0.0776
-6.750 -0.6741 0.03009 0.01915 -0.0122 1.0000 0.0863
-6.500 -0.6514 0.02860 0.01751 -0.0113 1.0000 0.0958
-6.250 -0.6301 0.02716 0.01599 -0.0101 1.0000 0.1063
-6.000 -0.6116 0.02575 0.01463 -0.0090 1.0000 0.1233
-5.750 -0.5939 0.02440 0.01348 -0.0078 1.0000 0.1496
-5.500 -0.5768 0.02308 0.01240 -0.0065 1.0000 0.1918
-5.250 -0.5615 0.02168 0.01137 -0.0051 1.0000 0.2575
-5.000 -0.5477 0.02040 0.01063 -0.0032 1.0000 0.3373
-4.750 -0.5328 0.01952 0.01023 -0.0009 1.0000 0.4330
-4.500 -0.5168 0.01910 0.01020 0.0020 1.0000 0.5152
-4.250 -0.5000 0.01900 0.01021 0.0050 1.0000 0.5833
-4.000 -0.4841 0.01908 0.01033 0.0083 1.0000 0.6410
-3.750 -0.4683 0.01919 0.01042 0.0116 1.0000 0.6858
-3.500 -0.4516 0.01921 0.01036 0.0145 1.0000 0.7179
-3.250 -0.4329 0.01917 0.01020 0.0168 1.0000 0.7409
-3.000 -0.4149 0.01908 0.01000 0.0189 1.0000 0.7620
-2.750 -0.3968 0.01900 0.00977 0.0210 1.0000 0.7820
-2.500 -0.3798 0.01889 0.00955 0.0231 1.0000 0.8018
-2.250 -0.3602 0.01885 0.00942 0.0248 1.0000 0.8208
-2.000 -0.3408 0.01886 0.00936 0.0267 1.0000 0.8448
-1.750 -0.3162 0.01896 0.00939 0.0278 1.0000 0.8710
-1.500 -0.2809 0.01913 0.00944 0.0267 1.0000 0.8943
-1.250 -0.2473 0.01918 0.00939 0.0252 1.0000 0.9131
-1.000 -0.2121 0.01918 0.00930 0.0230 1.0000 0.9276
-0.750 -0.1639 0.01923 0.00924 0.0182 0.9930 0.9386
-0.500 -0.1092 0.01929 0.00922 0.0121 0.9844 0.9474
-0.250 -0.0555 0.01933 0.00920 0.0062 0.9751 0.9569
0.000 0.0000 0.01936 0.00921 0.0000 0.9662 0.9662
0.250 0.0555 0.01933 0.00920 -0.0062 0.9569 0.9751
0.500 0.1092 0.01929 0.00922 -0.0121 0.9474 0.9844
0.750 0.1639 0.01923 0.00923 -0.0182 0.9386 0.9931
1.000 0.2122 0.01917 0.00930 -0.0230 0.9275 1.0000
1.250 0.2473 0.01918 0.00939 -0.0252 0.9131 1.0000
1.500 0.2809 0.01913 0.00944 -0.0267 0.8944 1.0000
1.750 0.3161 0.01896 0.00940 -0.0277 0.8710 1.0000
2.000 0.3407 0.01886 0.00936 -0.0267 0.8449 1.0000
2.250 0.3602 0.01885 0.00942 -0.0248 0.8209 1.0000
2.500 0.3798 0.01889 0.00956 -0.0231 0.8019 1.0000
2.750 0.3968 0.01900 0.00977 -0.0210 0.7820 1.0000
3.000 0.4149 0.01908 0.00999 -0.0189 0.7620 1.0000
3.250 0.4329 0.01917 0.01020 -0.0168 0.7410 1.0000
3.500 0.4515 0.01921 0.01036 -0.0145 0.7179 1.0000
3.750 0.4683 0.01919 0.01042 -0.0116 0.6857 1.0000
4.000 0.4841 0.01908 0.01033 -0.0083 0.6410 1.0000
4.250 0.5000 0.01900 0.01021 -0.0050 0.5834 1.0000
4.500 0.5168 0.01910 0.01020 -0.0020 0.5152 1.0000
4.750 0.5328 0.01952 0.01023 0.0009 0.4332 1.0000
5.000 0.5477 0.02039 0.01063 0.0032 0.3375 1.0000
5.250 0.5615 0.02168 0.01137 0.0051 0.2575 1.0000
5.500 0.5768 0.02308 0.01240 0.0065 0.1919 1.0000
5.750 0.5939 0.02440 0.01348 0.0078 0.1495 1.0000
6.000 0.6115 0.02576 0.01463 0.0090 0.1232 1.0000
6.250 0.6301 0.02716 0.01599 0.0101 0.1063 1.0000
6.500 0.6514 0.02861 0.01751 0.0113 0.0957 1.0000
6.750 0.6741 0.03009 0.01915 0.0122 0.0862 1.0000
7.000 0.6957 0.03162 0.02072 0.0130 0.0775 1.0000
7.250 0.7193 0.03338 0.02270 0.0138 0.0718 1.0000
7.500 0.7423 0.03545 0.02481 0.0144 0.0681 1.0000
7.750 0.7643 0.03798 0.02774 0.0153 0.0654 1.0000
8.000 0.7824 0.04046 0.03069 0.0163 0.0614 1.0000
8.250 0.7987 0.04252 0.03302 0.0171 0.0569 1.0000
8.500 0.8136 0.04541 0.03604 0.0179 0.0545 1.0000
8.750 0.8221 0.04899 0.04023 0.0192 0.0534 1.0000
9.000 0.8250 0.05294 0.04471 0.0205 0.0524 1.0000
9.250 0.8230 0.05705 0.04926 0.0217 0.0519 1.0000
9.500 0.8154 0.06129 0.05386 0.0226 0.0515 1.0000
9.750 0.8023 0.06556 0.05840 0.0232 0.0513 1.0000
10.000 0.7836 0.06972 0.06274 0.0235 0.0513 1.0000
10.250 0.7632 0.07453 0.06765 0.0221 0.0516 1.0000
10.500 0.7431 0.08027 0.07346 0.0189 0.0521 1.0000
10.750 0.7249 0.08695 0.08016 0.0144 0.0526 1.0000
11.000 0.7095 0.09439 0.08759 0.0094 0.0531 1.0000
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