HT12 (ht12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 500,000 Max Cl/Cd: 45.15 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht12-il-500000.txt Download as CSV file: xf-ht12-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HT12
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.7458 0.03155 0.02770 -0.0047 1.0000 0.0157
-6.750 -0.7277 0.02601 0.02153 -0.0050 1.0000 0.0155
-6.500 -0.7051 0.02250 0.01751 -0.0048 1.0000 0.0157
-6.250 -0.6796 0.02076 0.01543 -0.0045 1.0000 0.0161
-6.000 -0.6567 0.01657 0.01073 -0.0042 1.0000 0.0170
-5.750 -0.6308 0.01516 0.00919 -0.0039 1.0000 0.0180
-5.500 -0.6040 0.01448 0.00843 -0.0038 1.0000 0.0195
-5.250 -0.5769 0.01380 0.00765 -0.0035 1.0000 0.0214
-5.000 -0.5497 0.01305 0.00679 -0.0033 1.0000 0.0226
-4.750 -0.5233 0.01166 0.00526 -0.0030 1.0000 0.0247
-4.500 -0.4960 0.01099 0.00455 -0.0028 1.0000 0.0279
-4.250 -0.4683 0.01063 0.00414 -0.0027 1.0000 0.0315
-4.000 -0.4408 0.00988 0.00335 -0.0025 1.0000 0.0370
-3.750 -0.4130 0.00954 0.00298 -0.0024 1.0000 0.0432
-3.500 -0.3853 0.00901 0.00249 -0.0023 1.0000 0.0585
-3.250 -0.3575 0.00855 0.00214 -0.0023 1.0000 0.0851
-3.000 -0.3299 0.00810 0.00189 -0.0023 1.0000 0.1279
-2.750 -0.3023 0.00768 0.00169 -0.0023 1.0000 0.1821
-2.500 -0.2747 0.00732 0.00155 -0.0023 1.0000 0.2401
-2.250 -0.2470 0.00700 0.00142 -0.0023 1.0000 0.2951
-2.000 -0.2193 0.00671 0.00132 -0.0023 1.0000 0.3489
-1.750 -0.1916 0.00642 0.00123 -0.0022 1.0000 0.4055
-1.500 -0.1641 0.00610 0.00116 -0.0022 1.0000 0.4739
-1.250 -0.1372 0.00563 0.00108 -0.0020 1.0000 0.5735
-1.000 -0.1129 0.00493 0.00106 -0.0011 1.0000 0.7461
-0.750 -0.0948 0.00437 0.00107 0.0020 1.0000 0.9263
-0.500 -0.0549 0.00429 0.00102 -0.0004 1.0000 1.0000
-0.250 -0.0274 0.00428 0.00099 -0.0002 1.0000 1.0000
0.000 0.0001 0.00428 0.00098 0.0000 1.0000 1.0000
0.250 0.0276 0.00428 0.00099 0.0002 1.0000 1.0000
0.500 0.0551 0.00429 0.00102 0.0004 1.0000 1.0000
0.750 0.0950 0.00438 0.00107 -0.0020 0.9247 1.0000
1.000 0.1130 0.00494 0.00106 0.0011 0.7442 1.0000
1.500 0.1643 0.00610 0.00116 0.0022 0.4735 1.0000
1.750 0.1918 0.00642 0.00124 0.0022 0.4050 1.0000
2.000 0.2194 0.00672 0.00132 0.0023 0.3482 1.0000
2.250 0.2472 0.00701 0.00142 0.0023 0.2947 1.0000
2.500 0.2749 0.00732 0.00155 0.0023 0.2404 1.0000
2.750 0.3025 0.00769 0.00169 0.0023 0.1818 1.0000
3.000 0.3301 0.00810 0.00189 0.0023 0.1276 1.0000
3.250 0.3577 0.00855 0.00214 0.0023 0.0850 1.0000
3.500 0.3855 0.00901 0.00249 0.0023 0.0583 1.0000
3.750 0.4132 0.00954 0.00298 0.0024 0.0432 1.0000
4.000 0.4410 0.00988 0.00335 0.0025 0.0369 1.0000
4.250 0.4685 0.01063 0.00415 0.0027 0.0314 1.0000
4.500 0.4962 0.01099 0.00455 0.0028 0.0278 1.0000
4.750 0.5235 0.01166 0.00526 0.0030 0.0247 1.0000
5.000 0.5499 0.01306 0.00680 0.0032 0.0226 1.0000
5.250 0.5771 0.01381 0.00766 0.0035 0.0213 1.0000
5.500 0.6042 0.01449 0.00843 0.0038 0.0195 1.0000
5.750 0.6310 0.01519 0.00922 0.0039 0.0180 1.0000
6.000 0.6570 0.01656 0.01072 0.0041 0.0170 1.0000
6.250 0.6798 0.02082 0.01550 0.0045 0.0161 1.0000
6.500 0.7053 0.02250 0.01751 0.0047 0.0157 1.0000
6.750 0.7280 0.02603 0.02155 0.0049 0.0155 1.0000
7.250 0.7620 0.03728 0.03398 0.0037 0.0155 1.0000
12.750 0.7966 0.16859 0.16630 -0.0716 0.0153 1.0000
13.000 0.8016 0.17292 0.17062 -0.0739 0.0146 1.0000
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Polar data table (+)
Polar graphs
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