NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 1,000,000 Max Cl/Cd: 56.42 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001234-il-1000000.txt Download as CSV file: xf-naca001234-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-34
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8163 0.05080 0.04838 -0.0459 1.0000 0.0073
-10.750 -0.8417 0.04705 0.04446 -0.0425 1.0000 0.0071
-10.500 -0.8663 0.04384 0.04106 -0.0372 1.0000 0.0070
-10.250 -0.8898 0.04115 0.03819 -0.0303 1.0000 0.0068
-10.000 -0.9122 0.03777 0.03455 -0.0232 1.0000 0.0066
-9.750 -0.9343 0.03419 0.03066 -0.0155 1.0000 0.0064
-9.500 -0.9487 0.03100 0.02715 -0.0086 1.0000 0.0064
-9.250 -0.9435 0.02828 0.02414 -0.0054 0.9993 0.0065
-9.000 -0.9253 0.02511 0.02061 -0.0047 0.9978 0.0067
-8.750 -0.9032 0.02254 0.01773 -0.0044 0.9964 0.0069
-8.500 -0.8768 0.02096 0.01594 -0.0048 0.9953 0.0072
-8.250 -0.8476 0.02000 0.01485 -0.0057 0.9944 0.0075
-8.000 -0.8238 0.01825 0.01289 -0.0055 0.9927 0.0078
-7.750 -0.8019 0.01638 0.01088 -0.0051 0.9905 0.0083
-7.500 -0.7745 0.01552 0.00997 -0.0056 0.9885 0.0087
-7.250 -0.7452 0.01482 0.00923 -0.0065 0.9869 0.0091
-7.000 -0.7151 0.01414 0.00850 -0.0076 0.9855 0.0096
-6.750 -0.6838 0.01357 0.00788 -0.0088 0.9845 0.0104
-6.500 -0.6509 0.01316 0.00742 -0.0104 0.9836 0.0111
-6.250 -0.6233 0.01228 0.00645 -0.0108 0.9818 0.0120
-6.000 -0.5993 0.01157 0.00567 -0.0104 0.9777 0.0132
-5.750 -0.5699 0.01116 0.00523 -0.0111 0.9751 0.0144
-5.500 -0.5394 0.01078 0.00481 -0.0120 0.9728 0.0159
-5.250 -0.5095 0.01040 0.00439 -0.0127 0.9706 0.0175
-5.000 -0.4853 0.01000 0.00397 -0.0121 0.9659 0.0216
-4.750 -0.4595 0.00970 0.00364 -0.0118 0.9612 0.0263
-4.500 -0.4343 0.00926 0.00328 -0.0115 0.9572 0.0458
-4.250 -0.4164 0.00843 0.00286 -0.0098 0.9509 0.1414
-4.000 -0.3999 0.00749 0.00247 -0.0080 0.9445 0.2738
-3.750 -0.3800 0.00687 0.00221 -0.0067 0.9387 0.3685
-3.500 -0.3584 0.00643 0.00201 -0.0057 0.9322 0.4359
-3.250 -0.3361 0.00601 0.00182 -0.0047 0.9267 0.5053
-3.000 -0.3153 0.00560 0.00167 -0.0034 0.9194 0.5791
-2.750 -0.2928 0.00528 0.00155 -0.0023 0.9134 0.6426
-2.500 -0.2689 0.00510 0.00148 -0.0016 0.9058 0.6796
-2.250 -0.2438 0.00496 0.00140 -0.0010 0.8993 0.7160
-2.000 -0.2180 0.00486 0.00136 -0.0006 0.8916 0.7358
-1.750 -0.1909 0.00481 0.00130 -0.0005 0.8851 0.7503
-1.500 -0.1639 0.00476 0.00126 -0.0003 0.8774 0.7632
-1.250 -0.1367 0.00472 0.00121 -0.0002 0.8706 0.7763
-1.000 -0.1096 0.00469 0.00119 -0.0001 0.8626 0.7894
-0.750 -0.0823 0.00467 0.00117 -0.0001 0.8553 0.8013
-0.500 -0.0550 0.00465 0.00116 0.0000 0.8470 0.8117
-0.250 -0.0275 0.00464 0.00115 0.0000 0.8389 0.8210
0.000 0.0000 0.00464 0.00114 0.0000 0.8303 0.8303
0.250 0.0275 0.00464 0.00115 0.0000 0.8210 0.8389
0.500 0.0550 0.00465 0.00116 0.0000 0.8117 0.8469
0.750 0.0822 0.00467 0.00117 0.0001 0.8013 0.8553
1.000 0.1096 0.00469 0.00119 0.0001 0.7894 0.8626
1.250 0.1366 0.00472 0.00121 0.0003 0.7764 0.8706
1.500 0.1639 0.00476 0.00126 0.0003 0.7633 0.8774
1.750 0.1908 0.00481 0.00130 0.0005 0.7502 0.8851
2.000 0.2180 0.00486 0.00136 0.0006 0.7359 0.8916
2.250 0.2437 0.00496 0.00140 0.0010 0.7154 0.8994
2.500 0.2687 0.00510 0.00148 0.0016 0.6785 0.9058
2.750 0.2928 0.00528 0.00155 0.0023 0.6425 0.9134
3.000 0.3154 0.00559 0.00167 0.0034 0.5798 0.9194
3.250 0.3359 0.00602 0.00182 0.0047 0.5041 0.9268
3.500 0.3584 0.00643 0.00201 0.0057 0.4362 0.9322
3.750 0.3799 0.00687 0.00221 0.0067 0.3684 0.9387
4.000 0.3999 0.00749 0.00247 0.0080 0.2739 0.9445
4.250 0.4164 0.00843 0.00286 0.0098 0.1415 0.9509
4.500 0.4343 0.00926 0.00328 0.0115 0.0458 0.9572
4.750 0.4595 0.00969 0.00363 0.0118 0.0266 0.9612
5.000 0.4853 0.00999 0.00397 0.0121 0.0216 0.9659
5.250 0.5096 0.01040 0.00438 0.0127 0.0175 0.9706
5.500 0.5395 0.01078 0.00481 0.0120 0.0159 0.9729
5.750 0.5700 0.01115 0.00523 0.0111 0.0144 0.9751
6.000 0.5994 0.01157 0.00567 0.0104 0.0132 0.9778
6.250 0.6235 0.01227 0.00643 0.0108 0.0120 0.9818
6.500 0.6510 0.01317 0.00743 0.0103 0.0111 0.9836
6.750 0.6840 0.01356 0.00786 0.0088 0.0104 0.9845
7.000 0.7153 0.01414 0.00850 0.0075 0.0096 0.9856
7.250 0.7453 0.01482 0.00923 0.0065 0.0091 0.9869
7.500 0.7746 0.01551 0.00996 0.0056 0.0087 0.9885
7.750 0.8020 0.01638 0.01088 0.0050 0.0083 0.9905
8.000 0.8240 0.01825 0.01289 0.0055 0.0078 0.9927
8.250 0.8478 0.02003 0.01488 0.0057 0.0075 0.9944
8.500 0.8771 0.02093 0.01591 0.0047 0.0072 0.9953
8.750 0.9035 0.02254 0.01773 0.0043 0.0069 0.9964
9.000 0.9256 0.02512 0.02062 0.0046 0.0067 0.9978
9.250 0.9442 0.02822 0.02407 0.0053 0.0065 0.9993
9.500 0.9478 0.03112 0.02729 0.0088 0.0064 1.0000
9.750 0.9345 0.03416 0.03063 0.0155 0.0064 1.0000
10.000 0.9116 0.03785 0.03464 0.0234 0.0066 1.0000
10.250 0.8894 0.04120 0.03824 0.0304 0.0068 1.0000
10.500 0.8661 0.04389 0.04111 0.0372 0.0070 1.0000
10.750 0.8422 0.04706 0.04447 0.0424 0.0071 1.0000
11.000 0.8141 0.05101 0.04860 0.0459 0.0073 1.0000
11.250 0.7097 0.04360 0.04134 0.0525 0.0076 1.0000
11.500 0.6878 0.04814 0.04602 0.0526 0.0075 1.0000
11.750 0.6654 0.05353 0.05152 0.0515 0.0075 1.0000
12.000 0.6424 0.05978 0.05789 0.0492 0.0075 1.0000
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Polar data table (+)
Polar graphs
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