NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 500,000 Max Cl/Cd: 78.21 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23112-jf-500000-n5.txt Download as CSV file: xf-naca23112-jf-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9326 0.08024 0.07756 -0.0137 1.0000 0.0137
-14.250 -1.0306 0.05587 0.05265 -0.0326 1.0000 0.0135
-14.000 -1.0635 0.04843 0.04489 -0.0360 1.0000 0.0135
-13.750 -1.0856 0.04340 0.03957 -0.0364 1.0000 0.0136
-13.500 -1.0995 0.03974 0.03562 -0.0351 1.0000 0.0137
-13.250 -1.1073 0.03694 0.03258 -0.0331 1.0000 0.0138
-13.000 -1.1097 0.03488 0.03037 -0.0306 1.0000 0.0139
-12.750 -1.1068 0.03336 0.02873 -0.0281 1.0000 0.0140
-12.500 -1.0993 0.03208 0.02735 -0.0259 1.0000 0.0142
-12.250 -1.0874 0.03093 0.02610 -0.0243 1.0000 0.0143
-12.000 -1.0737 0.02983 0.02490 -0.0227 1.0000 0.0145
-11.750 -1.0589 0.02874 0.02370 -0.0213 1.0000 0.0147
-11.500 -1.0431 0.02767 0.02250 -0.0199 1.0000 0.0149
-11.250 -1.0266 0.02656 0.02127 -0.0185 1.0000 0.0152
-11.000 -1.0093 0.02546 0.02002 -0.0172 1.0000 0.0154
-10.750 -0.9912 0.02439 0.01880 -0.0160 1.0000 0.0158
-10.500 -0.9722 0.02338 0.01763 -0.0148 1.0000 0.0161
-10.250 -0.9525 0.02242 0.01652 -0.0136 1.0000 0.0165
-10.000 -0.9324 0.02153 0.01549 -0.0125 1.0000 0.0168
-9.750 -0.9123 0.02073 0.01464 -0.0113 1.0000 0.0172
-9.500 -0.8909 0.02011 0.01398 -0.0103 1.0000 0.0175
-9.250 -0.8693 0.01953 0.01336 -0.0093 1.0000 0.0178
-9.000 -0.8477 0.01895 0.01273 -0.0082 1.0000 0.0182
-8.750 -0.8263 0.01837 0.01209 -0.0071 1.0000 0.0186
-8.500 -0.8053 0.01778 0.01143 -0.0058 1.0000 0.0190
-8.250 -0.7845 0.01721 0.01078 -0.0045 1.0000 0.0195
-8.000 -0.7639 0.01668 0.01017 -0.0031 1.0000 0.0199
-7.750 -0.7438 0.01614 0.00959 -0.0016 1.0000 0.0204
-7.500 -0.7235 0.01571 0.00916 -0.0001 1.0000 0.0209
-7.250 -0.6958 0.01532 0.00877 -0.0002 0.9981 0.0216
-7.000 -0.6620 0.01487 0.00829 -0.0016 0.9945 0.0224
-6.750 -0.6295 0.01438 0.00775 -0.0027 0.9899 0.0232
-6.500 -0.5963 0.01393 0.00724 -0.0038 0.9846 0.0239
-6.250 -0.5654 0.01342 0.00674 -0.0046 0.9774 0.0248
-6.000 -0.5321 0.01306 0.00638 -0.0057 0.9702 0.0258
-5.750 -0.5014 0.01273 0.00604 -0.0063 0.9595 0.0270
-5.500 -0.4709 0.01241 0.00567 -0.0067 0.9469 0.0282
-5.250 -0.4423 0.01203 0.00527 -0.0068 0.9313 0.0293
-5.000 -0.4150 0.01175 0.00497 -0.0065 0.9119 0.0305
-4.750 -0.3892 0.01152 0.00467 -0.0057 0.8880 0.0319
-4.500 -0.3646 0.01137 0.00438 -0.0047 0.8543 0.0334
-4.250 -0.3404 0.01119 0.00409 -0.0037 0.8166 0.0351
-4.000 -0.3152 0.01107 0.00386 -0.0029 0.7836 0.0370
-3.750 -0.2894 0.01097 0.00362 -0.0023 0.7557 0.0389
-3.500 -0.2635 0.01083 0.00339 -0.0018 0.7276 0.0413
-3.250 -0.2371 0.01074 0.00321 -0.0013 0.7021 0.0442
-3.000 -0.2106 0.01066 0.00303 -0.0009 0.6764 0.0469
-2.750 -0.1842 0.01056 0.00286 -0.0005 0.6498 0.0507
-2.500 -0.1575 0.01053 0.00271 -0.0001 0.6234 0.0548
-2.250 -0.1307 0.01043 0.00257 0.0002 0.5996 0.0605
-2.000 -0.1038 0.01039 0.00245 0.0005 0.5751 0.0667
-1.750 -0.0769 0.01034 0.00234 0.0008 0.5498 0.0759
-1.500 -0.0502 0.01029 0.00223 0.0011 0.5246 0.0891
-1.250 -0.0236 0.01017 0.00213 0.0014 0.5027 0.1171
-1.000 -0.0045 0.00901 0.00185 0.0024 0.4825 0.3913
-0.750 0.0183 0.00854 0.00176 0.0033 0.4601 0.5188
-0.500 0.0423 0.00828 0.00173 0.0041 0.4378 0.6037
-0.250 0.0665 0.00810 0.00173 0.0049 0.4168 0.6764
0.000 0.0912 0.00798 0.00175 0.0057 0.3977 0.7338
0.250 0.1165 0.00795 0.00180 0.0065 0.3782 0.7795
0.500 0.1419 0.00797 0.00187 0.0073 0.3590 0.8214
0.750 0.1678 0.00804 0.00195 0.0080 0.3413 0.8552
1.000 0.1939 0.00813 0.00206 0.0087 0.3262 0.8873
1.250 0.2212 0.00826 0.00215 0.0091 0.3125 0.9055
1.500 0.2494 0.00839 0.00223 0.0092 0.2993 0.9157
1.750 0.2773 0.00854 0.00231 0.0093 0.2874 0.9259
2.250 0.3353 0.00882 0.00249 0.0090 0.2687 0.9423
2.500 0.3660 0.00899 0.00260 0.0085 0.2600 0.9487
2.750 0.3944 0.00912 0.00270 0.0085 0.2523 0.9564
3.000 0.4269 0.00931 0.00282 0.0075 0.2452 0.9607
3.250 0.4580 0.00944 0.00294 0.0069 0.2397 0.9661
3.500 0.4883 0.00960 0.00306 0.0063 0.2333 0.9713
3.750 0.5220 0.00978 0.00319 0.0051 0.2276 0.9743
4.000 0.5551 0.00992 0.00333 0.0039 0.2226 0.9777
4.250 0.5866 0.01010 0.00347 0.0031 0.2172 0.9816
4.500 0.6198 0.01028 0.00363 0.0018 0.2122 0.9841
4.750 0.6543 0.01043 0.00378 0.0003 0.2075 0.9862
5.000 0.6877 0.01060 0.00394 -0.0010 0.2025 0.9886
5.250 0.7201 0.01080 0.00412 -0.0021 0.1977 0.9913
5.500 0.7521 0.01096 0.00429 -0.0031 0.1935 0.9939
5.750 0.7857 0.01114 0.00446 -0.0045 0.1884 0.9956
6.000 0.8185 0.01136 0.00466 -0.0057 0.1835 0.9976
6.250 0.8513 0.01152 0.00486 -0.0070 0.1793 0.9994
6.500 0.8775 0.01171 0.00504 -0.0068 0.1745 1.0000
6.750 0.8998 0.01193 0.00525 -0.0058 0.1701 1.0000
7.000 0.9227 0.01210 0.00545 -0.0049 0.1663 1.0000
7.250 0.9453 0.01230 0.00566 -0.0040 0.1616 1.0000
7.500 0.9675 0.01255 0.00590 -0.0030 0.1567 1.0000
7.750 0.9902 0.01276 0.00614 -0.0021 0.1524 1.0000
8.000 1.0127 0.01299 0.00638 -0.0012 0.1471 1.0000
8.250 1.0347 0.01329 0.00666 -0.0003 0.1417 1.0000
8.500 1.0574 0.01352 0.00693 0.0006 0.1366 1.0000
8.750 1.0793 0.01384 0.00723 0.0015 0.1305 1.0000
9.000 1.1016 0.01412 0.00754 0.0024 0.1250 1.0000
9.250 1.1234 0.01447 0.00788 0.0033 0.1186 1.0000
9.500 1.1454 0.01481 0.00824 0.0041 0.1128 1.0000
9.750 1.1670 0.01521 0.00863 0.0050 0.1060 1.0000
10.000 1.1889 0.01560 0.00904 0.0058 0.0998 1.0000
10.500 1.2312 0.01653 0.00997 0.0074 0.0864 1.0000
10.750 1.2515 0.01707 0.01050 0.0083 0.0799 1.0000
11.000 1.2713 0.01763 0.01107 0.0092 0.0731 1.0000
11.250 1.2910 0.01821 0.01166 0.0102 0.0671 1.0000
11.500 1.3093 0.01888 0.01233 0.0112 0.0612 1.0000
11.750 1.3273 0.01954 0.01301 0.0123 0.0558 1.0000
12.000 1.3445 0.02024 0.01374 0.0135 0.0512 1.0000
12.250 1.3600 0.02103 0.01455 0.0148 0.0467 1.0000
12.500 1.3753 0.02178 0.01534 0.0161 0.0431 1.0000
12.750 1.3866 0.02266 0.01625 0.0179 0.0397 1.0000
13.000 1.3973 0.02350 0.01716 0.0198 0.0372 1.0000
13.250 1.4063 0.02450 0.01821 0.0217 0.0347 1.0000
13.500 1.4139 0.02566 0.01943 0.0234 0.0327 1.0000
13.750 1.4219 0.02688 0.02073 0.0247 0.0308 1.0000
14.000 1.4272 0.02840 0.02232 0.0259 0.0291 1.0000
14.250 1.4311 0.03017 0.02417 0.0268 0.0277 1.0000
14.500 1.4353 0.03207 0.02619 0.0272 0.0265 1.0000
14.750 1.4370 0.03441 0.02863 0.0272 0.0253 1.0000
15.000 1.4357 0.03729 0.03161 0.0267 0.0244 1.0000
15.500 1.4267 0.04458 0.03915 0.0241 0.0230 1.0000
15.750 1.4188 0.04900 0.04371 0.0221 0.0225 1.0000
16.000 1.4063 0.05420 0.04906 0.0197 0.0220 1.0000
16.250 1.3893 0.06019 0.05520 0.0169 0.0217 1.0000
16.500 1.3678 0.06689 0.06206 0.0138 0.0215 1.0000
16.750 1.3432 0.07412 0.06944 0.0106 0.0214 1.0000
17.000 1.3168 0.08168 0.07714 0.0072 0.0213 1.0000
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