HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.39 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hh02-il-1000000-n5.txt Download as CSV file: xf-hh02-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HUGHES HELICOPTERS HH-02 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
------ -------- --------- --------- -------- -------- --------
-11.750 -1.1815 0.04132 0.03885 0.0118 0.8026 0.0050
-11.500 -1.1831 0.03608 0.03322 0.0115 0.8000 0.0051
-11.250 -1.1738 0.03268 0.02949 0.0117 0.7975 0.0051
-11.000 -1.1595 0.03011 0.02664 0.0121 0.7949 0.0052
-10.750 -1.1422 0.02804 0.02432 0.0126 0.7924 0.0052
-10.500 -1.1228 0.02630 0.02235 0.0131 0.7902 0.0053
-10.250 -1.1018 0.02483 0.02068 0.0135 0.7879 0.0053
-10.000 -1.0796 0.02352 0.01920 0.0139 0.7856 0.0054
-9.750 -1.0592 0.02164 0.01706 0.0145 0.7831 0.0056
-9.500 -1.0359 0.02042 0.01568 0.0149 0.7805 0.0057
-9.250 -1.0115 0.01950 0.01462 0.0152 0.7780 0.0059
-9.000 -0.9864 0.01873 0.01373 0.0155 0.7756 0.0061
-8.750 -0.9608 0.01804 0.01294 0.0158 0.7733 0.0062
-8.500 -0.9347 0.01739 0.01220 0.0160 0.7708 0.0064
-8.250 -0.9085 0.01676 0.01148 0.0162 0.7680 0.0066
-8.000 -0.8822 0.01615 0.01078 0.0165 0.7653 0.0068
-7.750 -0.8556 0.01556 0.01008 0.0167 0.7626 0.0070
-7.500 -0.8288 0.01504 0.00946 0.0169 0.7600 0.0073
-7.250 -0.8016 0.01457 0.00891 0.0170 0.7574 0.0076
-7.000 -0.7742 0.01416 0.00843 0.0171 0.7544 0.0077
-6.750 -0.7473 0.01350 0.00769 0.0173 0.7512 0.0082
-6.500 -0.7198 0.01307 0.00721 0.0174 0.7481 0.0086
-6.250 -0.6920 0.01272 0.00679 0.0175 0.7452 0.0090
-6.000 -0.6641 0.01237 0.00640 0.0175 0.7421 0.0095
-5.750 -0.6361 0.01202 0.00600 0.0176 0.7387 0.0099
-5.500 -0.6079 0.01169 0.00562 0.0176 0.7350 0.0104
-5.250 -0.5797 0.01140 0.00526 0.0177 0.7315 0.0107
-5.000 -0.5516 0.01100 0.00481 0.0177 0.7282 0.0115
-4.750 -0.5231 0.01072 0.00452 0.0177 0.7243 0.0122
-4.500 -0.4946 0.01048 0.00425 0.0177 0.7200 0.0129
-4.250 -0.4660 0.01027 0.00399 0.0176 0.7159 0.0138
-4.000 -0.4373 0.01006 0.00376 0.0176 0.7120 0.0145
-3.750 -0.4086 0.00977 0.00345 0.0175 0.7072 0.0159
-3.500 -0.3798 0.00956 0.00322 0.0175 0.7024 0.0170
-3.250 -0.3509 0.00939 0.00301 0.0174 0.6981 0.0183
-3.000 -0.3219 0.00920 0.00280 0.0173 0.6929 0.0198
-2.750 -0.2929 0.00901 0.00260 0.0172 0.6875 0.0220
-2.500 -0.2639 0.00886 0.00244 0.0171 0.6826 0.0241
-2.250 -0.2347 0.00870 0.00227 0.0170 0.6768 0.0272
-2.000 -0.2056 0.00856 0.00213 0.0168 0.6711 0.0316
-1.750 -0.1764 0.00843 0.00199 0.0167 0.6644 0.0361
-1.500 -0.1471 0.00832 0.00186 0.0165 0.6533 0.0422
-1.250 -0.1177 0.00820 0.00173 0.0163 0.6389 0.0538
-0.750 -0.0591 0.00776 0.00151 0.0157 0.6181 0.1322
-0.500 -0.0298 0.00752 0.00142 0.0154 0.6095 0.1890
-0.250 -0.0006 0.00723 0.00134 0.0151 0.6005 0.2626
0.000 0.0283 0.00681 0.00127 0.0147 0.5917 0.3792
0.250 0.0573 0.00654 0.00125 0.0144 0.5820 0.4690
0.500 0.0866 0.00642 0.00125 0.0141 0.5719 0.5159
0.750 0.1160 0.00635 0.00126 0.0139 0.5615 0.5562
1.000 0.1455 0.00633 0.00127 0.0136 0.5491 0.5836
1.250 0.1752 0.00634 0.00130 0.0132 0.5349 0.6058
1.500 0.2049 0.00636 0.00133 0.0129 0.5182 0.6310
1.750 0.2347 0.00640 0.00136 0.0125 0.4987 0.6520
2.000 0.2648 0.00648 0.00140 0.0120 0.4765 0.6648
2.250 0.2949 0.00659 0.00145 0.0115 0.4529 0.6744
2.500 0.3253 0.00674 0.00151 0.0109 0.4223 0.6843
2.750 0.3559 0.00693 0.00160 0.0102 0.3870 0.6948
3.000 0.3863 0.00713 0.00170 0.0095 0.3556 0.7070
3.500 0.4464 0.00741 0.00191 0.0082 0.3055 0.7417
3.750 0.4744 0.00724 0.00197 0.0081 0.2850 0.8265
4.000 0.4984 0.00722 0.00213 0.0090 0.2673 0.9429
4.250 0.5269 0.00736 0.00226 0.0089 0.2519 0.9614
4.500 0.5576 0.00753 0.00238 0.0082 0.2375 0.9740
4.750 0.5892 0.00775 0.00254 0.0073 0.2191 0.9831
5.000 0.6221 0.00802 0.00272 0.0060 0.1976 0.9894
5.250 0.6542 0.00829 0.00290 0.0048 0.1791 0.9946
5.500 0.6864 0.00852 0.00309 0.0036 0.1659 0.9988
5.750 0.7165 0.00876 0.00328 0.0030 0.1542 1.0000
6.000 0.7457 0.00900 0.00349 0.0025 0.1430 1.0000
6.250 0.7751 0.00930 0.00372 0.0019 0.1279 1.0000
6.500 0.8043 0.00960 0.00396 0.0013 0.1154 1.0000
6.750 0.8333 0.00990 0.00422 0.0007 0.1050 1.0000
7.000 0.8623 0.01023 0.00450 0.0001 0.0929 1.0000
7.250 0.8912 0.01056 0.00479 -0.0004 0.0829 1.0000
7.500 0.9199 0.01090 0.00510 -0.0010 0.0735 1.0000
7.750 0.9484 0.01128 0.00544 -0.0015 0.0634 1.0000
8.000 0.9768 0.01171 0.00582 -0.0021 0.0536 1.0000
8.250 1.0049 0.01217 0.00622 -0.0027 0.0443 1.0000
8.500 1.0327 0.01265 0.00666 -0.0033 0.0362 1.0000
8.750 1.0604 0.01303 0.00705 -0.0038 0.0323 1.0000
9.000 1.0878 0.01351 0.00750 -0.0043 0.0272 1.0000
9.250 1.1149 0.01396 0.00796 -0.0047 0.0236 1.0000
9.500 1.1418 0.01445 0.00845 -0.0052 0.0203 1.0000
9.750 1.1683 0.01497 0.00898 -0.0056 0.0173 1.0000
10.000 1.1944 0.01551 0.00953 -0.0060 0.0146 1.0000
10.250 1.2200 0.01614 0.01015 -0.0064 0.0119 1.0000
10.500 1.2453 0.01673 0.01077 -0.0068 0.0100 1.0000
10.750 1.2700 0.01742 0.01148 -0.0072 0.0082 1.0000
11.000 1.2944 0.01811 0.01221 -0.0076 0.0070 1.0000
11.250 1.3179 0.01890 0.01304 -0.0080 0.0059 1.0000
11.500 1.3410 0.01965 0.01385 -0.0084 0.0053 1.0000
11.750 1.3630 0.02050 0.01475 -0.0087 0.0048 1.0000
12.000 1.3835 0.02147 0.01577 -0.0090 0.0044 1.0000
12.250 1.4025 0.02252 0.01689 -0.0093 0.0041 1.0000
12.500 1.4206 0.02353 0.01799 -0.0094 0.0039 1.0000
12.750 1.4349 0.02464 0.01918 -0.0091 0.0038 1.0000
13.000 1.4460 0.02584 0.02046 -0.0083 0.0037 1.0000
13.250 1.4566 0.02716 0.02186 -0.0077 0.0036 1.0000
13.500 1.4664 0.02860 0.02338 -0.0071 0.0035 1.0000
13.750 1.4752 0.03017 0.02503 -0.0066 0.0034 1.0000
14.000 1.4826 0.03190 0.02685 -0.0062 0.0033 1.0000
14.250 1.4887 0.03381 0.02885 -0.0059 0.0032 1.0000
14.500 1.4932 0.03592 0.03106 -0.0057 0.0032 1.0000
14.750 1.4963 0.03825 0.03348 -0.0057 0.0031 1.0000
15.000 1.4976 0.04086 0.03621 -0.0058 0.0030 1.0000
15.250 1.4971 0.04376 0.03922 -0.0062 0.0030 1.0000
15.500 1.4944 0.04703 0.04260 -0.0068 0.0030 1.0000
15.750 1.4901 0.05065 0.04634 -0.0077 0.0029 1.0000
16.000 1.4835 0.05476 0.05056 -0.0089 0.0029 1.0000
16.250 1.4749 0.05937 0.05531 -0.0106 0.0029 1.0000
16.500 1.4637 0.06456 0.06063 -0.0126 0.0028 1.0000
16.750 1.4498 0.07045 0.06665 -0.0152 0.0028 1.0000
17.000 1.4331 0.07697 0.07332 -0.0182 0.0028 1.0000
17.250 1.4138 0.08424 0.08073 -0.0216 0.0028 1.0000
17.500 1.3919 0.09213 0.08877 -0.0254 0.0028 1.0000
17.750 1.3672 0.10072 0.09751 -0.0295 0.0028 1.0000
18.000 1.3407 0.10978 0.10672 -0.0339 0.0028 1.0000
18.250 1.3133 0.11915 0.11623 -0.0385 0.0029 1.0000
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