NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 200,000 Max Cl/Cd: 55.44 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23012-il-200000-n5.txt Download as CSV file: xf-naca23012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23012 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6267 0.09234 0.08851 -0.0139 1.0000 0.0237
-11.000 -0.6796 0.07247 0.06857 -0.0301 1.0000 0.0232
-10.750 -0.7271 0.06202 0.05787 -0.0369 1.0000 0.0229
-10.500 -0.7587 0.05635 0.05197 -0.0365 1.0000 0.0229
-10.250 -0.7814 0.05145 0.04679 -0.0343 1.0000 0.0231
-10.000 -0.7951 0.04662 0.04160 -0.0319 1.0000 0.0235
-9.750 -0.8082 0.04109 0.03553 -0.0289 1.0000 0.0243
-9.500 -0.8191 0.03520 0.02876 -0.0251 1.0000 0.0251
-9.250 -0.8046 0.03374 0.02721 -0.0237 1.0000 0.0254
-9.000 -0.7893 0.03240 0.02576 -0.0222 1.0000 0.0258
-8.750 -0.7738 0.03101 0.02420 -0.0206 1.0000 0.0262
-8.500 -0.7580 0.02957 0.02259 -0.0189 1.0000 0.0267
-8.250 -0.7418 0.02813 0.02095 -0.0171 1.0000 0.0274
-8.000 -0.7252 0.02662 0.01917 -0.0153 1.0000 0.0284
-7.750 -0.7080 0.02503 0.01721 -0.0134 1.0000 0.0294
-7.500 -0.6890 0.02407 0.01625 -0.0121 1.0000 0.0300
-7.250 -0.6699 0.02325 0.01538 -0.0106 1.0000 0.0306
-7.000 -0.6506 0.02243 0.01449 -0.0091 1.0000 0.0313
-6.750 -0.6312 0.02159 0.01356 -0.0076 1.0000 0.0321
-6.500 -0.6117 0.02079 0.01265 -0.0060 1.0000 0.0332
-6.250 -0.5921 0.02006 0.01177 -0.0044 1.0000 0.0344
-6.000 -0.5732 0.01941 0.01118 -0.0030 1.0000 0.0354
-5.750 -0.5399 0.01874 0.01050 -0.0043 0.9963 0.0367
-5.500 -0.5049 0.01801 0.00972 -0.0059 0.9919 0.0383
-5.250 -0.4700 0.01733 0.00895 -0.0075 0.9867 0.0401
-5.000 -0.4348 0.01671 0.00841 -0.0093 0.9816 0.0423
-4.750 -0.4003 0.01617 0.00786 -0.0107 0.9750 0.0450
-4.500 -0.3648 0.01556 0.00723 -0.0124 0.9691 0.0476
-4.250 -0.3321 0.01507 0.00678 -0.0134 0.9604 0.0508
-4.000 -0.2992 0.01465 0.00632 -0.0145 0.9513 0.0550
-3.750 -0.2658 0.01416 0.00587 -0.0156 0.9420 0.0597
-3.500 -0.2353 0.01378 0.00548 -0.0160 0.9293 0.0654
-3.250 -0.2047 0.01340 0.00511 -0.0165 0.9158 0.0726
-3.000 -0.1746 0.01303 0.00475 -0.0167 0.9005 0.0822
-2.750 -0.1455 0.01267 0.00440 -0.0167 0.8814 0.0959
-2.500 -0.1178 0.01224 0.00402 -0.0164 0.8581 0.1245
-2.250 -0.1007 0.01075 0.00360 -0.0148 0.8324 0.3854
-2.000 -0.0795 0.01013 0.00342 -0.0132 0.8071 0.5152
-1.750 -0.0567 0.00979 0.00333 -0.0118 0.7822 0.5985
-1.500 -0.0334 0.00957 0.00327 -0.0103 0.7571 0.6656
-1.250 -0.0093 0.00946 0.00324 -0.0089 0.7316 0.7191
-1.000 0.0152 0.00942 0.00324 -0.0075 0.7054 0.7666
-0.750 0.0404 0.00945 0.00327 -0.0063 0.6790 0.8078
-0.500 0.0664 0.00956 0.00335 -0.0051 0.6517 0.8495
-0.250 0.0943 0.00972 0.00342 -0.0044 0.6236 0.8789
0.000 0.1232 0.00988 0.00344 -0.0042 0.5960 0.8956
0.250 0.1519 0.01006 0.00345 -0.0040 0.5675 0.9095
0.500 0.1824 0.01024 0.00348 -0.0043 0.5383 0.9216
0.750 0.2144 0.01044 0.00352 -0.0050 0.5102 0.9318
1.000 0.2449 0.01065 0.00356 -0.0054 0.4825 0.9427
1.250 0.2783 0.01087 0.00362 -0.0065 0.4535 0.9513
1.500 0.3111 0.01109 0.00368 -0.0075 0.4264 0.9596
1.750 0.3452 0.01132 0.00376 -0.0088 0.4008 0.9670
2.000 0.3801 0.01155 0.00385 -0.0104 0.3762 0.9733
2.250 0.4160 0.01179 0.00395 -0.0122 0.3530 0.9790
2.500 0.4509 0.01202 0.00406 -0.0138 0.3336 0.9849
2.750 0.4872 0.01224 0.00418 -0.0158 0.3159 0.9898
3.000 0.5227 0.01247 0.00431 -0.0176 0.3003 0.9949
3.250 0.5592 0.01268 0.00445 -0.0196 0.2869 0.9992
3.500 0.5842 0.01289 0.00459 -0.0193 0.2770 1.0000
3.750 0.6064 0.01309 0.00474 -0.0183 0.2677 1.0000
4.000 0.6288 0.01329 0.00492 -0.0174 0.2596 1.0000
4.250 0.6510 0.01352 0.00511 -0.0164 0.2521 1.0000
4.500 0.6733 0.01376 0.00531 -0.0154 0.2454 1.0000
4.750 0.6958 0.01398 0.00553 -0.0145 0.2385 1.0000
5.000 0.7176 0.01428 0.00577 -0.0134 0.2326 1.0000
5.250 0.7405 0.01450 0.00602 -0.0125 0.2268 1.0000
5.500 0.7629 0.01477 0.00628 -0.0116 0.2208 1.0000
5.750 0.7850 0.01509 0.00657 -0.0106 0.2156 1.0000
6.000 0.8079 0.01533 0.00687 -0.0097 0.2101 1.0000
6.250 0.8303 0.01563 0.00716 -0.0088 0.2046 1.0000
6.500 0.8524 0.01597 0.00750 -0.0078 0.1997 1.0000
6.750 0.8755 0.01624 0.00783 -0.0070 0.1942 1.0000
7.000 0.8979 0.01657 0.00817 -0.0061 0.1889 1.0000
7.250 0.9203 0.01693 0.00854 -0.0052 0.1841 1.0000
7.500 0.9436 0.01722 0.00892 -0.0045 0.1786 1.0000
7.750 0.9659 0.01758 0.00928 -0.0037 0.1733 1.0000
8.000 0.9886 0.01794 0.00970 -0.0029 0.1680 1.0000
8.250 1.0115 0.01828 0.01010 -0.0022 0.1621 1.0000
8.500 1.0330 0.01871 0.01051 -0.0013 0.1568 1.0000
8.750 1.0561 0.01905 0.01098 -0.0007 0.1508 1.0000
9.000 1.0777 0.01947 0.01142 0.0002 0.1450 1.0000
9.250 1.0997 0.01989 0.01192 0.0009 0.1390 1.0000
9.500 1.1209 0.02033 0.01241 0.0017 0.1325 1.0000
9.750 1.1419 0.02081 0.01295 0.0026 0.1263 1.0000
10.000 1.1622 0.02132 0.01350 0.0035 0.1196 1.0000
10.250 1.1821 0.02186 0.01411 0.0044 0.1134 1.0000
10.500 1.2009 0.02246 0.01475 0.0054 0.1068 1.0000
10.750 1.2195 0.02308 0.01545 0.0065 0.1004 1.0000
11.000 1.2357 0.02382 0.01620 0.0078 0.0940 1.0000
11.250 1.2528 0.02451 0.01700 0.0089 0.0874 1.0000
11.500 1.2668 0.02536 0.01789 0.0104 0.0814 1.0000
11.750 1.2792 0.02622 0.01881 0.0121 0.0755 1.0000
12.000 1.2891 0.02718 0.01983 0.0140 0.0705 1.0000
12.250 1.2974 0.02828 0.02099 0.0159 0.0656 1.0000
12.500 1.3051 0.02949 0.02229 0.0176 0.0614 1.0000
12.750 1.3110 0.03089 0.02376 0.0192 0.0574 1.0000
13.000 1.3153 0.03249 0.02546 0.0206 0.0541 1.0000
13.250 1.3191 0.03426 0.02734 0.0216 0.0509 1.0000
13.500 1.3186 0.03654 0.02969 0.0223 0.0484 1.0000
13.750 1.3198 0.03886 0.03215 0.0226 0.0460 1.0000
14.000 1.3181 0.04167 0.03510 0.0224 0.0439 1.0000
14.250 1.3126 0.04515 0.03869 0.0216 0.0423 1.0000
14.500 1.3052 0.04914 0.04281 0.0203 0.0410 1.0000
14.750 1.2980 0.05335 0.04718 0.0186 0.0396 1.0000
15.000 1.2872 0.05825 0.05225 0.0164 0.0385 1.0000
15.250 1.2732 0.06381 0.05795 0.0138 0.0377 1.0000
15.500 1.2561 0.06998 0.06427 0.0108 0.0370 1.0000
15.750 1.2368 0.07657 0.07099 0.0077 0.0365 1.0000
16.000 1.2163 0.08350 0.07804 0.0043 0.0361 1.0000
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Polar data table (+)
Polar graphs
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