NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.44 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n8h12-il-1000000.txt Download as CSV file: xf-n8h12-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 8-H-12 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5039 0.11126 0.10883 0.0179 0.6956 0.0142
-10.250 -0.5019 0.10696 0.10453 0.0157 0.6901 0.0151
-9.000 -0.7826 0.02889 0.02498 -0.0078 0.6839 0.0126
-8.750 -0.7658 0.02699 0.02275 -0.0066 0.6777 0.0128
-8.500 -0.7612 0.02239 0.01760 -0.0042 0.6721 0.0133
-8.250 -0.7382 0.02165 0.01675 -0.0036 0.6656 0.0135
-8.000 -0.7147 0.02092 0.01591 -0.0030 0.6592 0.0138
-7.750 -0.6905 0.02030 0.01517 -0.0024 0.6528 0.0141
-7.500 -0.6669 0.01939 0.01411 -0.0017 0.6469 0.0145
-7.250 -0.6431 0.01842 0.01296 -0.0010 0.6402 0.0149
-7.000 -0.6186 0.01760 0.01194 -0.0003 0.6340 0.0154
-6.750 -0.5931 0.01695 0.01115 0.0002 0.6276 0.0158
-6.500 -0.5694 0.01573 0.00970 0.0010 0.6215 0.0163
-6.250 -0.5442 0.01499 0.00892 0.0014 0.6157 0.0169
-6.000 -0.5176 0.01469 0.00858 0.0017 0.6094 0.0174
-5.750 -0.4910 0.01432 0.00812 0.0020 0.6031 0.0180
-5.500 -0.4645 0.01384 0.00756 0.0024 0.5970 0.0187
-5.250 -0.4377 0.01341 0.00703 0.0028 0.5905 0.0192
-5.000 -0.4104 0.01315 0.00668 0.0030 0.5846 0.0196
-4.750 -0.3859 0.01212 0.00558 0.0037 0.5787 0.0205
-4.500 -0.3594 0.01175 0.00516 0.0041 0.5727 0.0212
-4.250 -0.3321 0.01148 0.00488 0.0043 0.5672 0.0220
-4.000 -0.3050 0.01121 0.00456 0.0046 0.5613 0.0229
-3.750 -0.2780 0.01093 0.00421 0.0049 0.5556 0.0235
-3.500 -0.2504 0.01072 0.00396 0.0051 0.5502 0.0240
-3.250 -0.2250 0.01014 0.00332 0.0057 0.5444 0.0253
-3.000 -0.1979 0.00992 0.00308 0.0059 0.5389 0.0265
-2.750 -0.1704 0.00971 0.00285 0.0062 0.5336 0.0277
-2.500 -0.1428 0.00954 0.00264 0.0064 0.5283 0.0287
-2.250 -0.1155 0.00935 0.00239 0.0066 0.5234 0.0299
-2.000 -0.0881 0.00912 0.00216 0.0068 0.5187 0.0322
-1.750 -0.0603 0.00900 0.00201 0.0070 0.5138 0.0348
-1.500 -0.0328 0.00885 0.00185 0.0072 0.5089 0.0397
-1.250 -0.0054 0.00864 0.00173 0.0074 0.5048 0.0567
-1.000 0.0219 0.00845 0.00163 0.0076 0.5001 0.0875
-0.750 0.0487 0.00825 0.00155 0.0078 0.4954 0.1331
-0.500 0.0743 0.00787 0.00148 0.0081 0.4915 0.2322
-0.250 0.0979 0.00729 0.00141 0.0088 0.4878 0.3896
0.000 0.1170 0.00647 0.00133 0.0104 0.4841 0.6246
0.250 0.1318 0.00573 0.00131 0.0133 0.4805 0.8359
0.500 0.1958 0.00568 0.00154 0.0060 0.4762 0.9541
0.750 0.2316 0.00584 0.00167 0.0046 0.4727 0.9707
1.000 0.2822 0.00605 0.00181 -0.0001 0.4685 0.9787
1.250 0.3227 0.00623 0.00193 -0.0026 0.4644 0.9849
1.500 0.3817 0.00639 0.00204 -0.0092 0.4608 0.9910
1.750 0.4244 0.00646 0.00208 -0.0123 0.4576 0.9948
2.000 0.4666 0.00645 0.00204 -0.0154 0.4543 0.9973
2.250 0.5045 0.00647 0.00201 -0.0176 0.4511 0.9994
2.500 0.5344 0.00653 0.00203 -0.0181 0.4476 1.0000
2.750 0.5603 0.00654 0.00205 -0.0178 0.4453 1.0000
3.000 0.5863 0.00656 0.00208 -0.0174 0.4429 1.0000
3.250 0.6123 0.00659 0.00211 -0.0171 0.4403 1.0000
3.500 0.6384 0.00665 0.00216 -0.0168 0.4377 1.0000
3.750 0.6645 0.00672 0.00221 -0.0165 0.4347 1.0000
4.000 0.6906 0.00681 0.00229 -0.0163 0.4318 1.0000
4.250 0.7170 0.00684 0.00235 -0.0160 0.4294 1.0000
4.500 0.7434 0.00686 0.00239 -0.0158 0.4255 1.0000
4.750 0.7697 0.00693 0.00245 -0.0155 0.4212 1.0000
5.000 0.7959 0.00703 0.00254 -0.0153 0.4164 1.0000
5.250 0.8225 0.00704 0.00258 -0.0151 0.4108 1.0000
5.500 0.8487 0.00714 0.00265 -0.0149 0.4036 1.0000
5.750 0.8752 0.00718 0.00273 -0.0147 0.3959 1.0000
6.000 0.9013 0.00730 0.00281 -0.0145 0.3860 1.0000
6.250 0.9276 0.00738 0.00291 -0.0143 0.3772 1.0000
6.500 0.9538 0.00750 0.00303 -0.0142 0.3687 1.0000
6.750 0.9798 0.00766 0.00318 -0.0140 0.3577 1.0000
7.000 1.0057 0.00783 0.00333 -0.0138 0.3440 1.0000
7.250 1.0311 0.00810 0.00354 -0.0137 0.3210 1.0000
7.500 1.0540 0.00885 0.00402 -0.0135 0.2647 1.0000
7.750 1.0738 0.01008 0.00487 -0.0133 0.1947 1.0000
8.000 1.0929 0.01124 0.00571 -0.0129 0.1382 1.0000
8.250 1.1117 0.01228 0.00651 -0.0124 0.0962 1.0000
8.500 1.1299 0.01325 0.00730 -0.0117 0.0657 1.0000
8.750 1.1479 0.01409 0.00803 -0.0109 0.0470 1.0000
9.000 1.1657 0.01486 0.00874 -0.0101 0.0349 1.0000
9.250 1.1827 0.01562 0.00947 -0.0092 0.0282 1.0000
9.500 1.1988 0.01638 0.01023 -0.0081 0.0247 1.0000
9.750 1.2146 0.01706 0.01096 -0.0070 0.0231 1.0000
10.000 1.2266 0.01801 0.01192 -0.0059 0.0215 1.0000
10.250 1.2293 0.01934 0.01332 -0.0039 0.0204 1.0000
10.500 1.2305 0.02045 0.01449 -0.0014 0.0201 1.0000
10.750 1.2364 0.02166 0.01576 0.0001 0.0196 1.0000
11.000 1.2432 0.02301 0.01716 0.0012 0.0191 1.0000
11.250 1.2502 0.02447 0.01867 0.0020 0.0185 1.0000
11.500 1.2566 0.02606 0.02031 0.0027 0.0181 1.0000
11.750 1.2611 0.02789 0.02219 0.0033 0.0176 1.0000
12.000 1.2631 0.03000 0.02435 0.0039 0.0172 1.0000
12.250 1.2622 0.03244 0.02687 0.0044 0.0168 1.0000
12.500 1.2601 0.03504 0.02955 0.0048 0.0164 1.0000
12.750 1.2626 0.03725 0.03183 0.0051 0.0163 1.0000
13.000 1.2668 0.03931 0.03395 0.0053 0.0162 1.0000
13.250 1.2696 0.04153 0.03624 0.0055 0.0159 1.0000
13.500 1.2746 0.04358 0.03835 0.0055 0.0156 1.0000
13.750 1.2782 0.04585 0.04069 0.0055 0.0154 1.0000
14.000 1.2784 0.04851 0.04342 0.0055 0.0153 1.0000
14.250 1.2831 0.05075 0.04571 0.0053 0.0149 1.0000
14.500 1.2843 0.05342 0.04844 0.0051 0.0147 1.0000
14.750 1.2856 0.05609 0.05117 0.0049 0.0145 1.0000
15.000 1.2871 0.05879 0.05393 0.0046 0.0143 1.0000
15.250 1.2891 0.06149 0.05668 0.0042 0.0141 1.0000
15.500 1.2895 0.06435 0.05960 0.0039 0.0140 1.0000
15.750 1.2894 0.06734 0.06264 0.0034 0.0138 1.0000
16.000 1.2870 0.07057 0.06594 0.0029 0.0135 1.0000
16.250 1.2847 0.07384 0.06927 0.0024 0.0133 1.0000
16.500 1.2807 0.07713 0.07263 0.0022 0.0131 1.0000
16.750 1.2804 0.08021 0.07579 0.0016 0.0130 1.0000
17.000 1.2822 0.08303 0.07867 0.0011 0.0129 1.0000
17.250 1.2847 0.08605 0.08178 0.0002 0.0127 1.0000
17.500 1.2859 0.08904 0.08484 -0.0005 0.0127 1.0000
17.750 1.2868 0.09225 0.08812 -0.0014 0.0125 1.0000
18.000 1.2871 0.09549 0.09144 -0.0023 0.0123 1.0000
18.250 1.2865 0.09882 0.09485 -0.0032 0.0122 1.0000
18.500 1.2858 0.10228 0.09838 -0.0043 0.0120 1.0000
18.750 1.2848 0.10583 0.10202 -0.0055 0.0119 1.0000
19.000 1.2829 0.10948 0.10574 -0.0067 0.0117 1.0000
19.250 1.2809 0.11334 0.10967 -0.0082 0.0115 1.0000
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