NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 1,000,000 Max Cl/Cd: 98.58 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23112-jf-1000000.txt Download as CSV file: xf-naca23112-jf-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6324 0.17185 0.17008 0.0331 1.0000 0.0148
-14.750 -0.6264 0.16824 0.16648 0.0314 1.0000 0.0152
-14.500 -1.0624 0.05365 0.05104 -0.0335 1.0000 0.0137
-14.000 -1.1187 0.04150 0.03836 -0.0368 1.0000 0.0138
-13.750 -1.1473 0.03672 0.03326 -0.0348 1.0000 0.0139
-13.500 -1.1608 0.03368 0.03000 -0.0318 1.0000 0.0140
-13.250 -1.1612 0.03196 0.02815 -0.0291 1.0000 0.0142
-13.000 -1.1548 0.03081 0.02693 -0.0266 1.0000 0.0144
-12.750 -1.1416 0.02999 0.02607 -0.0250 1.0000 0.0145
-12.500 -1.1273 0.02908 0.02509 -0.0235 1.0000 0.0147
-12.250 -1.1121 0.02815 0.02409 -0.0220 1.0000 0.0149
-12.000 -1.0972 0.02705 0.02287 -0.0205 1.0000 0.0151
-11.750 -1.0816 0.02590 0.02159 -0.0191 1.0000 0.0153
-11.500 -1.0648 0.02481 0.02037 -0.0177 1.0000 0.0156
-11.250 -1.0472 0.02374 0.01918 -0.0164 1.0000 0.0158
-11.000 -1.0286 0.02273 0.01805 -0.0151 1.0000 0.0161
-10.750 -1.0090 0.02183 0.01702 -0.0140 1.0000 0.0163
-10.500 -0.9882 0.02107 0.01615 -0.0129 1.0000 0.0166
-10.250 -0.9665 0.02046 0.01544 -0.0119 1.0000 0.0167
-10.000 -0.9510 0.01867 0.01349 -0.0102 1.0000 0.0172
-9.750 -0.9299 0.01799 0.01278 -0.0091 1.0000 0.0176
-9.500 -0.9077 0.01751 0.01227 -0.0081 1.0000 0.0179
-9.250 -0.8856 0.01704 0.01177 -0.0070 1.0000 0.0182
-9.000 -0.8639 0.01657 0.01126 -0.0058 1.0000 0.0186
-8.750 -0.8425 0.01613 0.01077 -0.0046 1.0000 0.0191
-8.500 -0.8213 0.01572 0.01031 -0.0032 1.0000 0.0195
-8.250 -0.8001 0.01535 0.00990 -0.0019 1.0000 0.0199
-8.000 -0.7791 0.01504 0.00953 -0.0004 1.0000 0.0201
-7.750 -0.7636 0.01400 0.00845 0.0018 1.0000 0.0208
-7.500 -0.7444 0.01362 0.00806 0.0036 1.0000 0.0213
-7.250 -0.7148 0.01327 0.00771 0.0031 0.9989 0.0219
-7.000 -0.6798 0.01288 0.00730 0.0016 0.9968 0.0226
-6.750 -0.6442 0.01249 0.00688 -0.0001 0.9948 0.0234
-6.500 -0.6089 0.01218 0.00655 -0.0016 0.9923 0.0240
-6.250 -0.5764 0.01148 0.00584 -0.0027 0.9885 0.0252
-6.000 -0.5405 0.01118 0.00556 -0.0044 0.9852 0.0262
-5.750 -0.5072 0.01087 0.00524 -0.0055 0.9797 0.0273
-5.500 -0.4747 0.01060 0.00495 -0.0064 0.9715 0.0282
-5.250 -0.4468 0.01013 0.00445 -0.0062 0.9567 0.0295
-5.000 -0.4210 0.00989 0.00420 -0.0055 0.9365 0.0308
-4.750 -0.3956 0.00973 0.00400 -0.0047 0.9151 0.0322
-4.500 -0.3700 0.00961 0.00380 -0.0039 0.8937 0.0333
-4.250 -0.3453 0.00931 0.00342 -0.0030 0.8709 0.0352
-4.000 -0.3192 0.00918 0.00323 -0.0024 0.8477 0.0370
-3.750 -0.2930 0.00910 0.00306 -0.0019 0.8225 0.0388
-3.500 -0.2669 0.00894 0.00281 -0.0013 0.7953 0.0413
-3.250 -0.2402 0.00886 0.00266 -0.0009 0.7692 0.0441
-3.000 -0.2132 0.00882 0.00252 -0.0005 0.7433 0.0464
-2.750 -0.1866 0.00869 0.00233 -0.0001 0.7164 0.0509
-2.500 -0.1595 0.00867 0.00222 0.0002 0.6884 0.0545
-2.250 -0.1325 0.00858 0.00207 0.0005 0.6621 0.0608
-2.000 -0.1052 0.00854 0.00196 0.0008 0.6374 0.0670
-1.750 -0.0779 0.00849 0.00186 0.0010 0.6113 0.0768
-1.500 -0.0510 0.00840 0.00176 0.0013 0.5853 0.0973
-1.250 -0.0298 0.00747 0.00150 0.0022 0.5607 0.3171
-1.000 -0.0080 0.00676 0.00136 0.0031 0.5382 0.5013
-0.750 0.0163 0.00642 0.00131 0.0038 0.5154 0.6044
-0.500 0.0408 0.00621 0.00129 0.0045 0.4911 0.6854
-0.250 0.0664 0.00612 0.00130 0.0052 0.4667 0.7411
0.000 0.0920 0.00608 0.00132 0.0058 0.4428 0.7869
0.250 0.1181 0.00609 0.00136 0.0064 0.4211 0.8247
0.500 0.1444 0.00614 0.00141 0.0069 0.3992 0.8534
0.750 0.1708 0.00623 0.00147 0.0075 0.3766 0.8784
1.000 0.1971 0.00634 0.00155 0.0080 0.3557 0.8988
1.250 0.2235 0.00646 0.00163 0.0086 0.3375 0.9168
1.500 0.2492 0.00660 0.00173 0.0093 0.3209 0.9348
1.750 0.2761 0.00675 0.00182 0.0098 0.3054 0.9453
2.000 0.3029 0.00691 0.00190 0.0101 0.2914 0.9538
2.250 0.3317 0.00705 0.00199 0.0101 0.2798 0.9598
2.500 0.3606 0.00719 0.00208 0.0100 0.2705 0.9660
2.750 0.3896 0.00736 0.00218 0.0098 0.2608 0.9716
3.000 0.4229 0.00749 0.00228 0.0087 0.2532 0.9747
3.250 0.4558 0.00768 0.00241 0.0077 0.2451 0.9781
3.500 0.4869 0.00779 0.00251 0.0070 0.2401 0.9822
3.750 0.5222 0.00796 0.00262 0.0054 0.2332 0.9838
4.000 0.5586 0.00811 0.00275 0.0035 0.2275 0.9850
4.250 0.5945 0.00824 0.00286 0.0017 0.2225 0.9864
4.500 0.6295 0.00841 0.00299 0.0001 0.2163 0.9881
4.750 0.6640 0.00855 0.00311 -0.0014 0.2118 0.9901
5.000 0.6975 0.00867 0.00323 -0.0027 0.2074 0.9924
5.250 0.7309 0.00885 0.00337 -0.0039 0.2018 0.9942
5.500 0.7661 0.00900 0.00351 -0.0056 0.1972 0.9953
5.750 0.8012 0.00911 0.00362 -0.0073 0.1928 0.9966
6.000 0.8355 0.00927 0.00376 -0.0088 0.1876 0.9980
6.250 0.8694 0.00944 0.00393 -0.0103 0.1826 0.9993
6.500 0.8998 0.00956 0.00405 -0.0109 0.1786 1.0000
6.750 0.9228 0.00971 0.00419 -0.0101 0.1739 1.0000
7.000 0.9454 0.00991 0.00437 -0.0092 0.1690 1.0000
7.250 0.9687 0.01002 0.00451 -0.0083 0.1654 1.0000
7.500 0.9914 0.01019 0.00467 -0.0074 0.1604 1.0000
7.750 1.0136 0.01042 0.00488 -0.0064 0.1551 1.0000
8.000 1.0367 0.01056 0.00504 -0.0056 0.1511 1.0000
8.250 1.0590 0.01078 0.00524 -0.0046 0.1456 1.0000
8.500 1.0814 0.01100 0.00546 -0.0036 0.1406 1.0000
8.750 1.1041 0.01120 0.00567 -0.0028 0.1355 1.0000
9.000 1.1258 0.01151 0.00594 -0.0018 0.1290 1.0000
9.250 1.1489 0.01170 0.00617 -0.0009 0.1246 1.0000
9.500 1.1708 0.01202 0.00645 0.0000 0.1182 1.0000
9.750 1.1934 0.01228 0.00673 0.0008 0.1128 1.0000
10.000 1.2149 0.01264 0.00706 0.0018 0.1058 1.0000
10.250 1.2373 0.01296 0.00738 0.0026 0.1000 1.0000
10.500 1.2586 0.01339 0.00778 0.0035 0.0925 1.0000
10.750 1.2808 0.01376 0.00815 0.0042 0.0863 1.0000
11.000 1.3023 0.01422 0.00859 0.0050 0.0795 1.0000
11.500 1.3438 0.01525 0.00958 0.0067 0.0658 1.0000
11.750 1.3641 0.01581 0.01013 0.0076 0.0597 1.0000
12.000 1.3831 0.01646 0.01075 0.0086 0.0534 1.0000
12.250 1.4023 0.01706 0.01136 0.0095 0.0484 1.0000
12.500 1.4208 0.01771 0.01201 0.0106 0.0439 1.0000
12.750 1.4372 0.01847 0.01277 0.0118 0.0396 1.0000
13.000 1.4549 0.01910 0.01344 0.0129 0.0366 1.0000
13.250 1.4687 0.01997 0.01431 0.0144 0.0333 1.0000
13.500 1.4837 0.02062 0.01501 0.0159 0.0312 1.0000
13.750 1.4928 0.02152 0.01593 0.0181 0.0291 1.0000
14.000 1.5025 0.02241 0.01689 0.0200 0.0274 1.0000
14.250 1.5123 0.02336 0.01790 0.0216 0.0260 1.0000
14.500 1.5186 0.02462 0.01920 0.0233 0.0246 1.0000
14.750 1.5231 0.02611 0.02077 0.0247 0.0234 1.0000
15.000 1.5309 0.02747 0.02221 0.0257 0.0225 1.0000
15.250 1.5357 0.02921 0.02403 0.0263 0.0216 1.0000
15.500 1.5369 0.03144 0.02634 0.0267 0.0208 1.0000
15.750 1.5334 0.03441 0.02940 0.0264 0.0200 1.0000
16.000 1.5301 0.03764 0.03274 0.0256 0.0195 1.0000
16.250 1.5287 0.04086 0.03609 0.0245 0.0190 1.0000
16.500 1.5228 0.04482 0.04017 0.0229 0.0186 1.0000
16.750 1.5122 0.04961 0.04508 0.0208 0.0183 1.0000
17.000 1.4958 0.05532 0.05093 0.0183 0.0180 1.0000
17.250 1.4735 0.06202 0.05778 0.0152 0.0179 1.0000
17.500 1.4454 0.06960 0.06552 0.0119 0.0179 1.0000
17.750 1.4133 0.07788 0.07396 0.0082 0.0179 1.0000
18.000 1.3796 0.08658 0.08281 0.0044 0.0180 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 23112 (naca23112-jf)