HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/9 AIRFOIL (hq09-il) Reynolds number: 500,000 Max Cl/Cd: 53.38 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq09-il-500000-n5.txt Download as CSV file: xf-hq09-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.8622 0.04430 0.04164 -0.0162 1.0000 0.0025
-9.250 -0.8797 0.03761 0.03449 -0.0145 1.0000 0.0024
-9.000 -0.8850 0.03199 0.02832 -0.0126 1.0000 0.0024
-8.750 -0.8796 0.02778 0.02358 -0.0109 1.0000 0.0024
-8.500 -0.8672 0.02468 0.02005 -0.0095 1.0000 0.0024
-8.250 -0.8508 0.02228 0.01728 -0.0083 1.0000 0.0024
-8.000 -0.8323 0.02023 0.01491 -0.0072 1.0000 0.0024
-7.750 -0.8120 0.01862 0.01304 -0.0062 1.0000 0.0024
-7.500 -0.7907 0.01727 0.01147 -0.0054 1.0000 0.0024
-7.250 -0.7687 0.01610 0.01011 -0.0046 1.0000 0.0025
-7.000 -0.7459 0.01513 0.00898 -0.0039 1.0000 0.0025
-6.750 -0.7224 0.01431 0.00802 -0.0033 1.0000 0.0026
-6.500 -0.6990 0.01345 0.00696 -0.0026 1.0000 0.0028
-6.250 -0.6747 0.01280 0.00618 -0.0020 1.0000 0.0031
-6.000 -0.6501 0.01223 0.00556 -0.0015 1.0000 0.0041
-5.750 -0.6256 0.01172 0.00510 -0.0010 1.0000 0.0081
-5.500 -0.6000 0.01146 0.00480 -0.0007 1.0000 0.0110
-5.250 -0.5750 0.01107 0.00442 -0.0003 1.0000 0.0145
-5.000 -0.5498 0.01076 0.00409 0.0001 1.0000 0.0164
-4.750 -0.5246 0.01050 0.00380 0.0005 1.0000 0.0192
-4.500 -0.4994 0.01018 0.00347 0.0009 0.9995 0.0248
-4.250 -0.4662 0.00986 0.00316 -0.0005 0.9869 0.0321
-4.000 -0.4322 0.00953 0.00287 -0.0020 0.9737 0.0450
-3.750 -0.3982 0.00920 0.00260 -0.0035 0.9601 0.0652
-3.500 -0.3660 0.00887 0.00236 -0.0047 0.9444 0.0921
-3.250 -0.3378 0.00837 0.00210 -0.0051 0.9255 0.1569
-3.000 -0.3120 0.00796 0.00188 -0.0048 0.9041 0.2253
-2.750 -0.2875 0.00756 0.00167 -0.0042 0.8841 0.2917
-2.500 -0.2637 0.00709 0.00149 -0.0036 0.8657 0.3868
-2.250 -0.2388 0.00679 0.00135 -0.0031 0.8491 0.4522
-2.000 -0.2145 0.00645 0.00125 -0.0024 0.8332 0.5333
-1.750 -0.1891 0.00625 0.00121 -0.0019 0.8192 0.5963
-1.250 -0.1362 0.00610 0.00113 -0.0011 0.7934 0.6624
-1.000 -0.1089 0.00608 0.00109 -0.0009 0.7812 0.6755
-0.750 -0.0816 0.00606 0.00106 -0.0007 0.7704 0.6895
-0.500 -0.0543 0.00604 0.00104 -0.0005 0.7590 0.7038
-0.250 -0.0270 0.00603 0.00103 -0.0003 0.7479 0.7179
0.000 0.0000 0.00602 0.00103 0.0000 0.7338 0.7339
0.250 0.0270 0.00603 0.00103 0.0003 0.7179 0.7479
0.500 0.0543 0.00604 0.00104 0.0005 0.7037 0.7590
0.750 0.0816 0.00606 0.00106 0.0007 0.6894 0.7705
1.000 0.1089 0.00608 0.00109 0.0009 0.6754 0.7812
1.250 0.1363 0.00610 0.00113 0.0011 0.6624 0.7933
1.750 0.1892 0.00625 0.00121 0.0019 0.5963 0.8191
2.000 0.2145 0.00645 0.00125 0.0024 0.5328 0.8332
2.250 0.2389 0.00679 0.00135 0.0031 0.4524 0.8491
2.500 0.2637 0.00709 0.00149 0.0036 0.3870 0.8658
2.750 0.2875 0.00756 0.00167 0.0042 0.2918 0.8842
3.000 0.3120 0.00796 0.00188 0.0048 0.2251 0.9042
3.250 0.3378 0.00837 0.00210 0.0050 0.1566 0.9257
3.500 0.3660 0.00887 0.00236 0.0047 0.0922 0.9445
3.750 0.3982 0.00920 0.00260 0.0036 0.0656 0.9601
4.000 0.4321 0.00953 0.00287 0.0020 0.0452 0.9737
4.250 0.4662 0.00987 0.00317 0.0005 0.0317 0.9870
4.500 0.4994 0.01019 0.00347 -0.0009 0.0247 0.9996
4.750 0.5245 0.01050 0.00381 -0.0005 0.0194 1.0000
5.000 0.5497 0.01076 0.00408 -0.0001 0.0163 1.0000
5.250 0.5750 0.01106 0.00441 0.0003 0.0144 1.0000
5.500 0.6000 0.01146 0.00482 0.0007 0.0112 1.0000
5.750 0.6256 0.01172 0.00510 0.0010 0.0082 1.0000
6.000 0.6501 0.01224 0.00557 0.0015 0.0040 1.0000
6.250 0.6747 0.01280 0.00618 0.0020 0.0031 1.0000
6.500 0.6990 0.01347 0.00698 0.0026 0.0027 1.0000
6.750 0.7225 0.01431 0.00802 0.0032 0.0026 1.0000
7.000 0.7460 0.01513 0.00898 0.0038 0.0025 1.0000
7.250 0.7688 0.01612 0.01013 0.0046 0.0025 1.0000
7.500 0.7910 0.01727 0.01148 0.0053 0.0024 1.0000
7.750 0.8124 0.01861 0.01303 0.0062 0.0024 1.0000
8.000 0.8326 0.02024 0.01492 0.0071 0.0024 1.0000
8.250 0.8513 0.02222 0.01721 0.0082 0.0024 1.0000
8.500 0.8673 0.02478 0.02016 0.0094 0.0024 1.0000
8.750 0.8798 0.02786 0.02368 0.0108 0.0024 1.0000
9.000 0.8851 0.03212 0.02846 0.0125 0.0024 1.0000
9.250 0.8806 0.03757 0.03444 0.0144 0.0024 1.0000
9.500 0.8609 0.04467 0.04204 0.0161 0.0025 1.0000
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Polar data table (+)
Polar graphs
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