NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 100,000 Max Cl/Cd: 39.87 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23112-jf-100000-n5.txt Download as CSV file: xf-naca23112-jf-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5979 0.08714 0.08191 -0.0162 1.0000 0.0372
-10.000 -0.6182 0.07875 0.07347 -0.0232 1.0000 0.0367
-9.750 -0.6412 0.07263 0.06724 -0.0263 1.0000 0.0363
-9.500 -0.6618 0.06810 0.06258 -0.0261 1.0000 0.0362
-9.250 -0.6749 0.06392 0.05823 -0.0253 1.0000 0.0364
-9.000 -0.6825 0.05993 0.05401 -0.0241 1.0000 0.0368
-8.750 -0.6863 0.05601 0.04984 -0.0225 1.0000 0.0371
-8.500 -0.6867 0.05218 0.04570 -0.0207 1.0000 0.0374
-8.250 -0.6839 0.04848 0.04167 -0.0187 1.0000 0.0375
-8.000 -0.6784 0.04498 0.03780 -0.0165 1.0000 0.0378
-7.750 -0.6705 0.04167 0.03407 -0.0142 1.0000 0.0382
-7.500 -0.6608 0.03852 0.03042 -0.0118 1.0000 0.0390
-7.250 -0.6468 0.03637 0.02798 -0.0099 1.0000 0.0402
-7.000 -0.6288 0.03512 0.02671 -0.0087 1.0000 0.0413
-6.750 -0.6118 0.03346 0.02485 -0.0071 1.0000 0.0424
-6.500 -0.5944 0.03159 0.02272 -0.0053 1.0000 0.0433
-6.250 -0.5759 0.02981 0.02064 -0.0035 1.0000 0.0444
-6.000 -0.5564 0.02822 0.01870 -0.0018 1.0000 0.0462
-5.750 -0.5366 0.02701 0.01743 -0.0005 1.0000 0.0478
-5.500 -0.5164 0.02604 0.01643 0.0008 1.0000 0.0495
-5.250 -0.4956 0.02495 0.01525 0.0022 1.0000 0.0511
-5.000 -0.4746 0.02393 0.01412 0.0036 1.0000 0.0530
-4.750 -0.4540 0.02305 0.01313 0.0050 1.0000 0.0555
-4.500 -0.4346 0.02228 0.01244 0.0063 1.0000 0.0578
-4.250 -0.4134 0.02155 0.01172 0.0074 0.9994 0.0602
-4.000 -0.3729 0.02072 0.01081 0.0048 0.9910 0.0645
-3.750 -0.3338 0.01979 0.01001 0.0023 0.9817 0.0692
-3.500 -0.2945 0.01905 0.00928 -0.0001 0.9710 0.0747
-3.250 -0.2573 0.01831 0.00858 -0.0021 0.9584 0.0815
-3.000 -0.2209 0.01773 0.00794 -0.0037 0.9435 0.0897
-2.750 -0.1861 0.01708 0.00732 -0.0050 0.9263 0.1011
-2.500 -0.1522 0.01646 0.00673 -0.0059 0.9064 0.1186
-2.250 -0.1244 0.01542 0.00612 -0.0059 0.8829 0.1900
-2.000 -0.1096 0.01336 0.00598 -0.0031 0.8603 0.6196
-1.500 -0.0494 0.01315 0.00623 -0.0004 0.8097 0.8178
-1.250 -0.0171 0.01333 0.00633 0.0002 0.7819 0.8617
-1.000 0.0191 0.01362 0.00647 0.0002 0.7528 0.8974
-0.750 0.0573 0.01396 0.00660 -0.0005 0.7224 0.9261
-0.500 0.0952 0.01415 0.00656 -0.0018 0.6901 0.9412
-0.250 0.1350 0.01424 0.00642 -0.0039 0.6569 0.9484
0.000 0.1696 0.01435 0.00630 -0.0050 0.6246 0.9578
0.250 0.2074 0.01445 0.00617 -0.0069 0.5914 0.9656
0.500 0.2436 0.01457 0.00607 -0.0086 0.5590 0.9736
0.750 0.2799 0.01470 0.00598 -0.0104 0.5272 0.9817
1.000 0.3180 0.01482 0.00589 -0.0126 0.4961 0.9882
1.250 0.3552 0.01496 0.00584 -0.0147 0.4671 0.9951
1.500 0.3899 0.01511 0.00579 -0.0164 0.4406 1.0000
1.750 0.4128 0.01525 0.00579 -0.0157 0.4195 1.0000
2.000 0.4354 0.01542 0.00584 -0.0150 0.4005 1.0000
2.250 0.4579 0.01561 0.00590 -0.0142 0.3834 1.0000
2.500 0.4803 0.01582 0.00600 -0.0133 0.3681 1.0000
2.750 0.5027 0.01605 0.00613 -0.0125 0.3548 1.0000
3.000 0.5250 0.01630 0.00628 -0.0116 0.3429 1.0000
3.250 0.5474 0.01654 0.00647 -0.0107 0.3316 1.0000
3.500 0.5696 0.01682 0.00666 -0.0098 0.3219 1.0000
3.750 0.5919 0.01710 0.00690 -0.0089 0.3125 1.0000
4.000 0.6142 0.01740 0.00716 -0.0080 0.3044 1.0000
4.250 0.6364 0.01771 0.00743 -0.0070 0.2963 1.0000
4.500 0.6587 0.01805 0.00775 -0.0061 0.2891 1.0000
4.750 0.6810 0.01839 0.00807 -0.0052 0.2818 1.0000
5.000 0.7030 0.01878 0.00840 -0.0042 0.2759 1.0000
5.250 0.7255 0.01913 0.00882 -0.0033 0.2689 1.0000
5.500 0.7476 0.01952 0.00917 -0.0024 0.2630 1.0000
5.750 0.7699 0.01994 0.00962 -0.0015 0.2571 1.0000
6.000 0.7921 0.02035 0.01007 -0.0006 0.2511 1.0000
6.250 0.8141 0.02080 0.01048 0.0004 0.2459 1.0000
6.500 0.8363 0.02125 0.01103 0.0013 0.2401 1.0000
6.750 0.8582 0.02170 0.01154 0.0022 0.2345 1.0000
7.000 0.8802 0.02220 0.01200 0.0030 0.2298 1.0000
7.250 0.9019 0.02270 0.01265 0.0040 0.2240 1.0000
7.500 0.9237 0.02319 0.01321 0.0049 0.2185 1.0000
7.750 0.9456 0.02372 0.01371 0.0057 0.2141 1.0000
8.000 0.9667 0.02428 0.01447 0.0066 0.2082 1.0000
8.250 0.9880 0.02480 0.01506 0.0075 0.2028 1.0000
8.500 1.0094 0.02535 0.01560 0.0083 0.1982 1.0000
8.750 1.0295 0.02597 0.01647 0.0093 0.1921 1.0000
9.000 1.0501 0.02650 0.01706 0.0102 0.1868 1.0000
9.250 1.0701 0.02710 0.01775 0.0112 0.1817 1.0000
9.500 1.0891 0.02774 0.01859 0.0122 0.1756 1.0000
9.750 1.1085 0.02825 0.01912 0.0132 0.1706 1.0000
10.000 1.1261 0.02900 0.02008 0.0143 0.1644 1.0000
10.250 1.1436 0.02959 0.02078 0.0155 0.1586 1.0000
10.500 1.1602 0.03028 0.02159 0.0167 0.1531 1.0000
10.750 1.1753 0.03105 0.02254 0.0180 0.1467 1.0000
11.000 1.1900 0.03170 0.02319 0.0193 0.1416 1.0000
11.250 1.2022 0.03269 0.02444 0.0208 0.1350 1.0000
11.500 1.2135 0.03345 0.02525 0.0224 0.1297 1.0000
11.750 1.2220 0.03462 0.02664 0.0241 0.1237 1.0000
12.000 1.2269 0.03566 0.02777 0.0262 0.1186 1.0000
12.250 1.2301 0.03701 0.02923 0.0282 0.1138 1.0000
12.500 1.2317 0.03863 0.03102 0.0297 0.1086 1.0000
12.750 1.2317 0.04037 0.03279 0.0308 0.1046 1.0000
13.000 1.2294 0.04280 0.03545 0.0314 0.1000 1.0000
13.250 1.2253 0.04550 0.03829 0.0315 0.0959 1.0000
13.500 1.2199 0.04850 0.04131 0.0309 0.0928 1.0000
13.750 1.2102 0.05258 0.04563 0.0296 0.0893 1.0000
14.000 1.1985 0.05715 0.05037 0.0277 0.0863 1.0000
14.250 1.1853 0.06214 0.05546 0.0253 0.0839 1.0000
14.500 1.1730 0.06709 0.06043 0.0229 0.0817 1.0000
14.750 1.1507 0.07407 0.06765 0.0193 0.0798 1.0000
15.000 1.1255 0.08171 0.07547 0.0154 0.0781 1.0000
15.250 1.0986 0.08987 0.08378 0.0112 0.0764 1.0000
15.500 1.0755 0.09756 0.09157 0.0074 0.0746 1.0000
15.750 1.0757 0.10081 0.09476 0.0060 0.0719 1.0000
16.000 1.0403 0.11137 0.10549 0.0006 0.0705 1.0000
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