NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 95.35 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23112-jf-1000000-n5.txt Download as CSV file: xf-naca23112-jf-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23112
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
------ -------- --------- --------- -------- -------- --------
-17.250 -1.2596 0.06261 0.05979 -0.0298 1.0000 0.0101
-17.000 -1.2872 0.05474 0.05171 -0.0347 1.0000 0.0101
-16.750 -1.3044 0.04914 0.04593 -0.0375 1.0000 0.0101
-16.500 -1.3149 0.04494 0.04158 -0.0388 1.0000 0.0102
-16.250 -1.3217 0.04152 0.03801 -0.0393 1.0000 0.0103
-16.000 -1.3254 0.03870 0.03505 -0.0390 1.0000 0.0103
-15.750 -1.3263 0.03636 0.03259 -0.0382 1.0000 0.0104
-15.500 -1.3249 0.03437 0.03047 -0.0370 1.0000 0.0105
-15.250 -1.3216 0.03265 0.02863 -0.0356 1.0000 0.0106
-15.000 -1.3166 0.03115 0.02701 -0.0339 1.0000 0.0107
-14.750 -1.3100 0.02982 0.02557 -0.0320 1.0000 0.0108
-14.500 -1.3018 0.02864 0.02428 -0.0300 1.0000 0.0109
-14.250 -1.2926 0.02756 0.02309 -0.0279 1.0000 0.0110
-14.000 -1.2823 0.02657 0.02200 -0.0258 1.0000 0.0110
-13.750 -1.2708 0.02558 0.02092 -0.0237 1.0000 0.0111
-13.500 -1.2585 0.02444 0.01968 -0.0219 1.0000 0.0113
-13.250 -1.2429 0.02351 0.01867 -0.0204 1.0000 0.0115
-13.000 -1.2255 0.02270 0.01780 -0.0190 1.0000 0.0116
-12.750 -1.2067 0.02198 0.01701 -0.0179 1.0000 0.0118
-12.500 -1.1871 0.02130 0.01627 -0.0167 1.0000 0.0120
-12.250 -1.1668 0.02066 0.01558 -0.0157 1.0000 0.0121
-12.000 -1.1460 0.02004 0.01491 -0.0147 1.0000 0.0123
-11.750 -1.1249 0.01944 0.01425 -0.0137 1.0000 0.0125
-11.500 -1.1034 0.01887 0.01361 -0.0127 1.0000 0.0127
-11.250 -1.0816 0.01830 0.01298 -0.0118 1.0000 0.0129
-11.000 -1.0595 0.01776 0.01238 -0.0109 1.0000 0.0131
-10.750 -1.0372 0.01724 0.01180 -0.0099 1.0000 0.0134
-10.500 -1.0146 0.01675 0.01125 -0.0090 1.0000 0.0135
-10.250 -0.9919 0.01628 0.01074 -0.0081 1.0000 0.0137
-10.000 -0.9700 0.01573 0.01014 -0.0071 1.0000 0.0140
-9.750 -0.9477 0.01525 0.00965 -0.0061 1.0000 0.0143
-9.500 -0.9251 0.01487 0.00924 -0.0051 1.0000 0.0147
-9.250 -0.9026 0.01451 0.00887 -0.0040 1.0000 0.0150
-9.000 -0.8804 0.01417 0.00851 -0.0029 1.0000 0.0154
-8.750 -0.8587 0.01383 0.00814 -0.0016 1.0000 0.0157
-8.500 -0.8315 0.01345 0.00773 -0.0015 0.9985 0.0161
-8.250 -0.7995 0.01307 0.00731 -0.0025 0.9957 0.0164
-8.000 -0.7672 0.01271 0.00693 -0.0035 0.9929 0.0167
-7.750 -0.7373 0.01228 0.00648 -0.0040 0.9875 0.0173
-7.500 -0.7052 0.01193 0.00613 -0.0049 0.9825 0.0179
-7.250 -0.6753 0.01163 0.00583 -0.0053 0.9745 0.0184
-7.000 -0.6450 0.01135 0.00553 -0.0058 0.9654 0.0191
-6.750 -0.6160 0.01109 0.00524 -0.0059 0.9534 0.0197
-6.500 -0.5890 0.01086 0.00497 -0.0056 0.9377 0.0202
-6.250 -0.5638 0.01059 0.00466 -0.0049 0.9185 0.0210
-6.000 -0.5386 0.01040 0.00441 -0.0041 0.8965 0.0218
-5.750 -0.5133 0.01024 0.00417 -0.0033 0.8726 0.0226
-5.500 -0.4876 0.01011 0.00394 -0.0027 0.8454 0.0233
-5.250 -0.4622 0.01004 0.00372 -0.0019 0.8077 0.0240
-5.000 -0.4370 0.00995 0.00349 -0.0012 0.7633 0.0253
-4.750 -0.4108 0.00989 0.00330 -0.0008 0.7262 0.0265
-4.500 -0.3839 0.00980 0.00312 -0.0004 0.6996 0.0277
-4.000 -0.3299 0.00962 0.00278 0.0002 0.6507 0.0303
-3.750 -0.3027 0.00955 0.00264 0.0004 0.6263 0.0321
-3.500 -0.2753 0.00951 0.00251 0.0006 0.6011 0.0336
-3.250 -0.2481 0.00943 0.00237 0.0008 0.5771 0.0361
-2.750 -0.1930 0.00934 0.00215 0.0012 0.5332 0.0410
-2.500 -0.1656 0.00931 0.00205 0.0013 0.5084 0.0445
-2.250 -0.1379 0.00928 0.00196 0.0015 0.4869 0.0477
-2.000 -0.1103 0.00924 0.00188 0.0016 0.4672 0.0524
-1.750 -0.0826 0.00923 0.00181 0.0017 0.4461 0.0579
-1.500 -0.0550 0.00922 0.00175 0.0019 0.4240 0.0643
-1.250 -0.0275 0.00920 0.00170 0.0020 0.4028 0.0739
-1.000 0.0002 0.00917 0.00165 0.0021 0.3845 0.0876
-0.750 0.0275 0.00911 0.00161 0.0022 0.3670 0.1117
-0.250 0.0739 0.00786 0.00135 0.0035 0.3325 0.4610
0.000 0.0995 0.00761 0.00133 0.0039 0.3175 0.5437
0.250 0.1254 0.00743 0.00133 0.0043 0.3049 0.6123
0.500 0.1516 0.00733 0.00135 0.0047 0.2924 0.6664
0.750 0.1777 0.00722 0.00138 0.0051 0.2804 0.7202
1.000 0.2041 0.00717 0.00142 0.0056 0.2702 0.7632
1.250 0.2302 0.00713 0.00148 0.0061 0.2613 0.8052
1.500 0.2562 0.00709 0.00156 0.0067 0.2547 0.8472
1.750 0.2834 0.00715 0.00163 0.0070 0.2466 0.8668
2.000 0.3111 0.00721 0.00170 0.0072 0.2402 0.8802
2.250 0.3388 0.00729 0.00177 0.0073 0.2342 0.8928
2.500 0.3663 0.00738 0.00185 0.0075 0.2289 0.9047
2.750 0.3941 0.00745 0.00193 0.0077 0.2244 0.9150
3.000 0.4218 0.00755 0.00202 0.0079 0.2187 0.9252
3.250 0.4495 0.00767 0.00212 0.0080 0.2137 0.9341
3.500 0.4775 0.00776 0.00221 0.0081 0.2105 0.9423
3.750 0.5060 0.00787 0.00231 0.0080 0.2059 0.9496
4.000 0.5338 0.00801 0.00242 0.0081 0.2006 0.9567
4.250 0.5638 0.00812 0.00254 0.0077 0.1971 0.9619
4.500 0.5926 0.00824 0.00265 0.0075 0.1935 0.9679
4.750 0.6225 0.00838 0.00277 0.0071 0.1884 0.9722
5.000 0.6536 0.00855 0.00290 0.0063 0.1838 0.9756
5.250 0.6839 0.00867 0.00303 0.0058 0.1806 0.9796
5.500 0.7134 0.00882 0.00317 0.0054 0.1759 0.9834
5.750 0.7459 0.00900 0.00332 0.0043 0.1710 0.9852
6.000 0.7786 0.00915 0.00347 0.0032 0.1671 0.9869
6.250 0.8108 0.00931 0.00363 0.0021 0.1626 0.9887
6.500 0.8422 0.00952 0.00380 0.0012 0.1571 0.9908
6.750 0.8730 0.00969 0.00398 0.0004 0.1531 0.9929
7.000 0.9044 0.00988 0.00416 -0.0005 0.1477 0.9944
7.250 0.9363 0.01012 0.00437 -0.0016 0.1418 0.9956
7.500 0.9680 0.01031 0.00457 -0.0026 0.1368 0.9969
7.750 0.9989 0.01058 0.00480 -0.0035 0.1298 0.9983
8.000 1.0298 0.01080 0.00502 -0.0044 0.1243 0.9995
8.250 1.0556 0.01109 0.00528 -0.0043 0.1173 1.0000
8.500 1.0779 0.01132 0.00551 -0.0033 0.1122 1.0000
8.750 1.0993 0.01163 0.00578 -0.0023 0.1052 1.0000
9.000 1.1214 0.01190 0.00605 -0.0013 0.0997 1.0000
9.250 1.1427 0.01225 0.00637 -0.0003 0.0927 1.0000
9.500 1.1646 0.01256 0.00667 0.0007 0.0868 1.0000
9.750 1.1858 0.01294 0.00703 0.0017 0.0804 1.0000
10.000 1.2069 0.01335 0.00741 0.0027 0.0735 1.0000
10.250 1.2284 0.01375 0.00780 0.0036 0.0675 1.0000
10.500 1.2493 0.01423 0.00825 0.0045 0.0611 1.0000
10.750 1.2704 0.01470 0.00871 0.0054 0.0555 1.0000
11.000 1.2917 0.01516 0.00917 0.0062 0.0506 1.0000
11.250 1.3120 0.01572 0.00971 0.0071 0.0455 1.0000
11.500 1.3326 0.01624 0.01023 0.0079 0.0412 1.0000
11.750 1.3527 0.01678 0.01079 0.0088 0.0377 1.0000
12.000 1.3722 0.01736 0.01137 0.0097 0.0343 1.0000
12.250 1.3915 0.01794 0.01197 0.0107 0.0315 1.0000
12.500 1.4096 0.01858 0.01262 0.0117 0.0288 1.0000
12.750 1.4278 0.01919 0.01327 0.0127 0.0269 1.0000
13.000 1.4447 0.01984 0.01395 0.0139 0.0250 1.0000
13.250 1.4598 0.02056 0.01470 0.0153 0.0234 1.0000
13.500 1.4729 0.02123 0.01542 0.0170 0.0221 1.0000
13.750 1.4837 0.02204 0.01627 0.0189 0.0208 1.0000
14.000 1.4932 0.02298 0.01726 0.0207 0.0196 1.0000
14.250 1.5038 0.02390 0.01825 0.0222 0.0188 1.0000
14.500 1.5127 0.02500 0.01941 0.0236 0.0179 1.0000
14.750 1.5199 0.02632 0.02079 0.0248 0.0171 1.0000
15.000 1.5251 0.02790 0.02244 0.0257 0.0164 1.0000
15.250 1.5312 0.02956 0.02418 0.0263 0.0159 1.0000
15.500 1.5357 0.03150 0.02621 0.0265 0.0154 1.0000
15.750 1.5381 0.03382 0.02862 0.0264 0.0149 1.0000
16.000 1.5378 0.03662 0.03152 0.0258 0.0145 1.0000
16.250 1.5347 0.03998 0.03498 0.0248 0.0140 1.0000
16.500 1.5278 0.04401 0.03912 0.0232 0.0137 1.0000
16.750 1.5167 0.04881 0.04405 0.0211 0.0134 1.0000
17.000 1.5027 0.05415 0.04953 0.0187 0.0132 1.0000
17.250 1.4839 0.06031 0.05583 0.0159 0.0131 1.0000
17.500 1.4585 0.06745 0.06313 0.0127 0.0131 1.0000
17.750 1.4277 0.07554 0.07138 0.0092 0.0131 1.0000
18.000 1.3940 0.08416 0.08016 0.0054 0.0132 1.0000
18.250 1.3599 0.09305 0.08920 0.0014 0.0132 1.0000
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