NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 500,000 Max Cl/Cd: 104.21 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n8h12-il-500000.txt Download as CSV file: xf-n8h12-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4288 0.08431 0.08161 0.0085 0.6891 0.0252
-8.750 -0.5280 0.07857 0.07581 -0.0050 0.7080 0.0245
-8.500 -0.5419 0.07371 0.07090 -0.0073 0.7020 0.0245
-8.250 -0.5381 0.07158 0.06873 -0.0071 0.6954 0.0248
-8.000 -0.5363 0.06816 0.06525 -0.0082 0.6889 0.0250
-7.750 -0.5324 0.06489 0.06188 -0.0090 0.6834 0.0254
-7.500 -0.5274 0.06115 0.05807 -0.0099 0.6775 0.0260
-7.250 -0.5219 0.05688 0.05365 -0.0107 0.6718 0.0267
-7.000 -0.5264 0.04746 0.04346 -0.0106 0.6688 0.0293
-6.750 -0.5217 0.04187 0.03779 -0.0102 0.6636 0.0300
-6.500 -0.5300 0.03010 0.02500 -0.0063 0.6604 0.0247
-6.250 -0.5084 0.02875 0.02356 -0.0058 0.6539 0.0251
-6.000 -0.4935 0.02433 0.01827 -0.0031 0.6489 0.0242
-5.750 -0.4734 0.02137 0.01496 -0.0019 0.6426 0.0245
-5.500 -0.4499 0.01969 0.01306 -0.0012 0.6367 0.0250
-5.250 -0.4244 0.01870 0.01195 -0.0007 0.6305 0.0257
-5.000 -0.3985 0.01774 0.01086 -0.0003 0.6242 0.0264
-4.750 -0.3724 0.01694 0.00988 0.0002 0.6185 0.0274
-4.500 -0.3454 0.01624 0.00904 0.0006 0.6119 0.0285
-4.250 -0.3184 0.01571 0.00833 0.0011 0.6058 0.0292
-4.000 -0.2927 0.01436 0.00688 0.0016 0.5999 0.0301
-3.750 -0.2664 0.01369 0.00619 0.0020 0.5937 0.0312
-3.500 -0.2397 0.01330 0.00573 0.0023 0.5882 0.0326
-3.250 -0.2127 0.01290 0.00531 0.0027 0.5824 0.0341
-3.000 -0.1858 0.01252 0.00486 0.0030 0.5767 0.0352
-2.750 -0.1603 0.01197 0.00422 0.0037 0.5716 0.0366
-2.500 -0.1338 0.01157 0.00383 0.0040 0.5659 0.0387
-2.250 -0.1067 0.01134 0.00357 0.0043 0.5602 0.0414
-2.000 -0.0800 0.01108 0.00324 0.0047 0.5552 0.0443
-1.750 -0.0529 0.01079 0.00298 0.0050 0.5498 0.0497
-1.500 -0.0259 0.01054 0.00274 0.0053 0.5449 0.0617
-1.250 0.0000 0.01021 0.00253 0.0057 0.5403 0.1047
-1.000 0.0249 0.00968 0.00241 0.0062 0.5357 0.2091
-0.750 0.0459 0.00880 0.00227 0.0072 0.5313 0.4250
-0.500 0.0569 0.00757 0.00216 0.0106 0.5275 0.7393
-0.250 0.1341 0.00738 0.00249 0.0011 0.5218 0.9471
0.000 0.1809 0.00769 0.00272 -0.0024 0.5167 0.9727
0.250 0.2360 0.00794 0.00285 -0.0078 0.5120 0.9845
0.500 0.2965 0.00810 0.00290 -0.0145 0.5075 0.9940
0.750 0.3499 0.00803 0.00277 -0.0199 0.5031 1.0000
1.000 0.3752 0.00805 0.00274 -0.0195 0.4995 1.0000
1.250 0.4005 0.00809 0.00271 -0.0190 0.4961 1.0000
1.500 0.4259 0.00816 0.00272 -0.0186 0.4927 1.0000
1.750 0.4516 0.00817 0.00274 -0.0183 0.4892 1.0000
2.000 0.4774 0.00821 0.00276 -0.0179 0.4859 1.0000
2.250 0.5032 0.00826 0.00278 -0.0176 0.4829 1.0000
2.500 0.5290 0.00835 0.00281 -0.0172 0.4800 1.0000
2.750 0.5550 0.00844 0.00289 -0.0169 0.4771 1.0000
3.000 0.5812 0.00849 0.00296 -0.0166 0.4742 1.0000
3.250 0.6073 0.00855 0.00303 -0.0163 0.4710 1.0000
3.500 0.6335 0.00863 0.00310 -0.0161 0.4682 1.0000
3.750 0.6595 0.00874 0.00319 -0.0158 0.4657 1.0000
4.000 0.6854 0.00891 0.00332 -0.0155 0.4628 1.0000
4.250 0.7117 0.00898 0.00346 -0.0152 0.4601 1.0000
4.500 0.7379 0.00907 0.00359 -0.0150 0.4573 1.0000
4.750 0.7641 0.00917 0.00370 -0.0147 0.4542 1.0000
5.000 0.7901 0.00927 0.00379 -0.0145 0.4506 1.0000
5.250 0.8160 0.00941 0.00394 -0.0142 0.4462 1.0000
5.500 0.8423 0.00946 0.00407 -0.0140 0.4418 1.0000
5.750 0.8682 0.00950 0.00411 -0.0137 0.4358 1.0000
6.000 0.8942 0.00956 0.00421 -0.0134 0.4282 1.0000
6.250 0.9201 0.00959 0.00425 -0.0131 0.4203 1.0000
6.500 0.9461 0.00963 0.00434 -0.0129 0.4102 1.0000
6.750 0.9718 0.00973 0.00444 -0.0127 0.4001 1.0000
7.000 0.9979 0.00982 0.00460 -0.0125 0.3916 1.0000
7.250 1.0236 0.00995 0.00477 -0.0123 0.3820 1.0000
7.500 1.0491 0.01011 0.00495 -0.0121 0.3695 1.0000
7.750 1.0744 0.01031 0.00517 -0.0118 0.3526 1.0000
8.000 1.0988 0.01064 0.00545 -0.0116 0.3249 1.0000
8.250 1.1181 0.01169 0.00615 -0.0113 0.2564 1.0000
8.500 1.1315 0.01342 0.00745 -0.0106 0.1802 1.0000
8.750 1.1429 0.01505 0.00874 -0.0097 0.1216 1.0000
9.000 1.1519 0.01664 0.01007 -0.0084 0.0791 1.0000
9.250 1.1593 0.01811 0.01138 -0.0068 0.0541 1.0000
9.500 1.1657 0.01951 0.01275 -0.0054 0.0428 1.0000
9.750 1.1626 0.02114 0.01438 -0.0029 0.0379 1.0000
10.000 1.1628 0.02252 0.01583 -0.0007 0.0351 1.0000
10.250 1.1630 0.02427 0.01760 0.0009 0.0328 1.0000
10.500 1.1614 0.02640 0.01978 0.0021 0.0310 1.0000
10.750 1.1668 0.02808 0.02153 0.0029 0.0297 1.0000
11.000 1.1705 0.02997 0.02348 0.0036 0.0287 1.0000
11.250 1.1735 0.03197 0.02555 0.0042 0.0277 1.0000
11.500 1.1748 0.03419 0.02782 0.0047 0.0270 1.0000
11.750 1.1732 0.03673 0.03041 0.0052 0.0262 1.0000
12.000 1.1666 0.03976 0.03350 0.0057 0.0254 1.0000
12.250 1.1701 0.04188 0.03569 0.0060 0.0250 1.0000
12.500 1.1738 0.04399 0.03787 0.0063 0.0244 1.0000
12.750 1.1769 0.04620 0.04015 0.0065 0.0240 1.0000
13.000 1.1797 0.04850 0.04252 0.0067 0.0235 1.0000
13.250 1.1827 0.05082 0.04491 0.0068 0.0230 1.0000
13.500 1.1867 0.05307 0.04720 0.0068 0.0224 1.0000
13.750 1.1897 0.05544 0.04962 0.0069 0.0221 1.0000
14.000 1.1932 0.05774 0.05197 0.0069 0.0217 1.0000
14.250 1.1960 0.06011 0.05437 0.0071 0.0214 1.0000
14.500 1.1989 0.06233 0.05663 0.0074 0.0209 1.0000
14.750 1.2032 0.06403 0.05837 0.0086 0.0205 1.0000
15.000 1.2089 0.06630 0.06073 0.0084 0.0202 1.0000
15.250 1.2144 0.06860 0.06312 0.0082 0.0199 1.0000
15.500 1.2198 0.07075 0.06535 0.0082 0.0197 1.0000
15.750 1.2250 0.07301 0.06769 0.0082 0.0194 1.0000
16.000 1.2297 0.07534 0.07011 0.0081 0.0190 1.0000
16.250 1.2339 0.07779 0.07264 0.0079 0.0187 1.0000
16.500 1.2379 0.08018 0.07512 0.0078 0.0185 1.0000
16.750 1.2401 0.08298 0.07801 0.0073 0.0181 1.0000
17.000 1.2431 0.08560 0.08073 0.0071 0.0181 1.0000
17.250 1.2442 0.08859 0.08380 0.0064 0.0177 1.0000
17.500 1.2454 0.09162 0.08691 0.0057 0.0175 1.0000
17.750 1.2462 0.09464 0.08999 0.0050 0.0172 1.0000
18.000 1.2474 0.09751 0.09291 0.0046 0.0169 1.0000
18.250 1.2468 0.10061 0.09610 0.0042 0.0167 1.0000
18.500 1.2371 0.10526 0.10092 0.0033 0.0164 1.0000
18.750 1.2288 0.11025 0.10606 0.0010 0.0163 1.0000
19.000 1.2197 0.11531 0.11129 -0.0010 0.0163 1.0000
19.250 1.2079 0.12116 0.11731 -0.0039 0.0162 1.0000
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