HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/9 AIRFOIL (hq09-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.37 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq09-il-1000000-n5.txt Download as CSV file: xf-hq09-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.9177 0.04166 0.03959 -0.0168 1.0000 0.0017
-9.750 -0.9427 0.03392 0.03136 -0.0142 1.0000 0.0017
-9.500 -0.9483 0.02845 0.02536 -0.0119 1.0000 0.0017
-9.250 -0.9410 0.02484 0.02128 -0.0101 1.0000 0.0016
-9.000 -0.9282 0.02202 0.01808 -0.0086 1.0000 0.0016
-8.750 -0.9116 0.01982 0.01557 -0.0074 1.0000 0.0016
-8.500 -0.8924 0.01813 0.01361 -0.0064 1.0000 0.0016
-8.250 -0.8716 0.01675 0.01203 -0.0055 1.0000 0.0016
-8.000 -0.8500 0.01551 0.01060 -0.0047 1.0000 0.0016
-7.750 -0.8274 0.01451 0.00944 -0.0040 1.0000 0.0016
-7.500 -0.8042 0.01365 0.00844 -0.0034 1.0000 0.0016
-7.250 -0.7804 0.01289 0.00756 -0.0028 1.0000 0.0016
-7.000 -0.7561 0.01224 0.00680 -0.0022 1.0000 0.0016
-6.750 -0.7314 0.01168 0.00615 -0.0018 1.0000 0.0017
-6.500 -0.7064 0.01119 0.00554 -0.0013 1.0000 0.0017
-6.250 -0.6812 0.01075 0.00504 -0.0009 1.0000 0.0017
-6.000 -0.6558 0.01036 0.00459 -0.0005 1.0000 0.0018
-5.750 -0.6303 0.01001 0.00419 -0.0001 1.0000 0.0019
-5.500 -0.6030 0.00970 0.00383 -0.0001 0.9971 0.0021
-5.250 -0.5694 0.00938 0.00347 -0.0015 0.9812 0.0024
-5.000 -0.5353 0.00895 0.00311 -0.0032 0.9655 0.0099
-4.750 -0.5035 0.00876 0.00288 -0.0041 0.9455 0.0109
-4.500 -0.4762 0.00862 0.00265 -0.0039 0.9216 0.0125
-4.250 -0.4508 0.00848 0.00245 -0.0034 0.8971 0.0154
-4.000 -0.4253 0.00834 0.00226 -0.0029 0.8755 0.0198
-3.750 -0.3997 0.00815 0.00206 -0.0024 0.8575 0.0334
-3.500 -0.3737 0.00791 0.00188 -0.0021 0.8416 0.0536
-3.250 -0.3472 0.00775 0.00172 -0.0019 0.8266 0.0696
-3.000 -0.3207 0.00756 0.00155 -0.0017 0.8110 0.0926
-2.750 -0.2945 0.00731 0.00136 -0.0014 0.7945 0.1285
-2.250 -0.2423 0.00667 0.00107 -0.0011 0.7671 0.2473
-2.000 -0.2158 0.00638 0.00095 -0.0010 0.7560 0.3031
-1.750 -0.1898 0.00601 0.00083 -0.0008 0.7457 0.3860
-1.500 -0.1634 0.00572 0.00072 -0.0007 0.7365 0.4540
-1.250 -0.1371 0.00544 0.00065 -0.0005 0.7265 0.5249
-1.000 -0.1106 0.00520 0.00062 -0.0003 0.7164 0.5932
-0.750 -0.0830 0.00515 0.00060 -0.0002 0.7062 0.6173
-0.500 -0.0554 0.00515 0.00058 -0.0001 0.6908 0.6323
-0.250 -0.0278 0.00515 0.00057 0.0000 0.6738 0.6469
0.000 0.0000 0.00515 0.00057 0.0000 0.6603 0.6603
0.250 0.0278 0.00515 0.00057 0.0000 0.6470 0.6739
0.500 0.0554 0.00515 0.00058 0.0001 0.6322 0.6908
0.750 0.0830 0.00515 0.00060 0.0002 0.6173 0.7062
1.000 0.1107 0.00521 0.00062 0.0003 0.5932 0.7163
1.250 0.1371 0.00543 0.00065 0.0005 0.5253 0.7266
1.500 0.1634 0.00572 0.00072 0.0007 0.4539 0.7365
1.750 0.1898 0.00601 0.00083 0.0008 0.3865 0.7458
2.000 0.2158 0.00638 0.00095 0.0010 0.3033 0.7563
2.250 0.2424 0.00667 0.00107 0.0011 0.2472 0.7671
2.500 0.2689 0.00693 0.00120 0.0012 0.2038 0.7792
2.750 0.2946 0.00731 0.00136 0.0014 0.1284 0.7943
3.000 0.3208 0.00756 0.00155 0.0017 0.0926 0.8108
3.250 0.3472 0.00775 0.00172 0.0019 0.0695 0.8266
3.500 0.3737 0.00791 0.00188 0.0021 0.0537 0.8415
3.750 0.3997 0.00814 0.00206 0.0024 0.0338 0.8577
4.000 0.4254 0.00835 0.00226 0.0029 0.0194 0.8759
4.250 0.4508 0.00848 0.00245 0.0034 0.0155 0.8975
4.500 0.4763 0.00862 0.00265 0.0039 0.0124 0.9217
4.750 0.5035 0.00876 0.00288 0.0041 0.0109 0.9454
5.000 0.5352 0.00895 0.00311 0.0032 0.0096 0.9655
5.250 0.5694 0.00939 0.00348 0.0015 0.0024 0.9812
5.500 0.6030 0.00969 0.00382 0.0001 0.0021 0.9970
5.750 0.6302 0.01001 0.00419 0.0001 0.0019 1.0000
6.000 0.6557 0.01037 0.00460 0.0005 0.0018 1.0000
6.250 0.6812 0.01075 0.00504 0.0009 0.0017 1.0000
6.500 0.7064 0.01119 0.00555 0.0013 0.0017 1.0000
6.750 0.7315 0.01169 0.00616 0.0018 0.0017 1.0000
7.000 0.7562 0.01224 0.00680 0.0022 0.0016 1.0000
7.250 0.7805 0.01290 0.00757 0.0027 0.0016 1.0000
7.500 0.8043 0.01366 0.00844 0.0033 0.0016 1.0000
7.750 0.8276 0.01450 0.00943 0.0040 0.0016 1.0000
8.000 0.8503 0.01551 0.01059 0.0047 0.0016 1.0000
8.250 0.8720 0.01670 0.01197 0.0055 0.0016 1.0000
8.500 0.8924 0.01819 0.01368 0.0064 0.0016 1.0000
8.750 0.9117 0.01987 0.01562 0.0074 0.0016 1.0000
9.000 0.9283 0.02209 0.01816 0.0086 0.0016 1.0000
9.250 0.9418 0.02477 0.02120 0.0100 0.0016 1.0000
9.500 0.9482 0.02859 0.02552 0.0118 0.0017 1.0000
9.750 0.9439 0.03382 0.03126 0.0140 0.0017 1.0000
10.000 0.9165 0.04197 0.03992 0.0167 0.0017 1.0000
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Polar data table (+)
Polar graphs
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