NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.48 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12n1-il-1000000-n5.txt Download as CSV file: xf-rc12n1-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(N)1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0776 0.06083 0.05889 -0.0184 1.0000 0.0073
-14.250 -1.1228 0.05060 0.04836 -0.0242 1.0000 0.0073
-14.000 -1.1491 0.04458 0.04209 -0.0258 1.0000 0.0073
-13.750 -1.1657 0.04047 0.03775 -0.0252 1.0000 0.0074
-13.500 -1.1754 0.03744 0.03451 -0.0235 1.0000 0.0074
-13.250 -1.1801 0.03504 0.03191 -0.0212 1.0000 0.0075
-13.000 -1.1800 0.03312 0.02982 -0.0187 1.0000 0.0075
-12.750 -1.1765 0.03146 0.02800 -0.0162 1.0000 0.0076
-12.500 -1.1675 0.02990 0.02628 -0.0145 1.0000 0.0076
-12.250 -1.1664 0.02791 0.02387 -0.0113 0.8806 0.0078
-12.000 -1.1546 0.02665 0.02237 -0.0095 0.8503 0.0079
-11.750 -1.1386 0.02566 0.02121 -0.0082 0.8327 0.0081
-11.500 -1.1206 0.02480 0.02021 -0.0072 0.8197 0.0082
-11.000 -1.0810 0.02329 0.01844 -0.0054 0.8005 0.0085
-10.750 -1.0599 0.02265 0.01769 -0.0047 0.7929 0.0086
-10.500 -1.0382 0.02200 0.01695 -0.0041 0.7865 0.0088
-10.250 -1.0164 0.02132 0.01616 -0.0034 0.7805 0.0090
-10.000 -0.9946 0.02058 0.01530 -0.0027 0.7752 0.0092
-9.750 -0.9726 0.01979 0.01438 -0.0020 0.7696 0.0094
-9.500 -0.9503 0.01904 0.01349 -0.0014 0.7646 0.0096
-9.250 -0.9274 0.01833 0.01267 -0.0008 0.7604 0.0098
-9.000 -0.9039 0.01769 0.01191 -0.0002 0.7558 0.0099
-8.750 -0.8801 0.01711 0.01122 0.0003 0.7511 0.0101
-8.500 -0.8559 0.01657 0.01059 0.0008 0.7470 0.0102
-8.250 -0.8329 0.01580 0.00972 0.0014 0.7430 0.0104
-8.000 -0.8092 0.01517 0.00901 0.0019 0.7387 0.0108
-7.750 -0.7842 0.01474 0.00853 0.0023 0.7345 0.0110
-7.500 -0.7589 0.01434 0.00808 0.0026 0.7308 0.0113
-7.250 -0.7335 0.01391 0.00760 0.0029 0.7270 0.0115
-7.000 -0.7081 0.01351 0.00714 0.0032 0.7230 0.0117
-6.750 -0.6827 0.01312 0.00668 0.0036 0.7190 0.0120
-6.500 -0.6570 0.01274 0.00625 0.0039 0.7154 0.0123
-6.250 -0.6311 0.01237 0.00584 0.0042 0.7117 0.0125
-6.000 -0.6051 0.01203 0.00544 0.0044 0.7080 0.0128
-5.750 -0.5789 0.01172 0.00507 0.0047 0.7042 0.0131
-5.500 -0.5524 0.01144 0.00474 0.0048 0.7006 0.0133
-5.250 -0.5265 0.01106 0.00434 0.0051 0.6968 0.0140
-5.000 -0.4998 0.01079 0.00405 0.0053 0.6929 0.0147
-4.750 -0.4730 0.01056 0.00378 0.0054 0.6892 0.0153
-4.500 -0.4459 0.01034 0.00354 0.0055 0.6856 0.0160
-4.250 -0.4187 0.01013 0.00330 0.0056 0.6816 0.0168
-4.000 -0.3913 0.00994 0.00309 0.0056 0.6776 0.0173
-3.750 -0.3643 0.00971 0.00284 0.0057 0.6738 0.0189
-3.500 -0.3367 0.00954 0.00266 0.0057 0.6702 0.0203
-3.250 -0.3090 0.00938 0.00249 0.0057 0.6660 0.0218
-3.000 -0.2814 0.00922 0.00231 0.0057 0.6619 0.0238
-2.750 -0.2537 0.00907 0.00217 0.0057 0.6580 0.0266
-2.500 -0.2258 0.00894 0.00203 0.0056 0.6542 0.0297
-2.250 -0.1979 0.00879 0.00191 0.0056 0.6499 0.0349
-2.000 -0.1701 0.00866 0.00179 0.0055 0.6456 0.0420
-1.750 -0.1423 0.00853 0.00168 0.0055 0.6415 0.0528
-1.500 -0.1144 0.00837 0.00158 0.0054 0.6371 0.0686
-1.250 -0.0873 0.00812 0.00147 0.0055 0.6323 0.1138
-0.750 -0.0450 0.00619 0.00106 0.0072 0.6229 0.5599
-0.500 -0.0180 0.00605 0.00104 0.0073 0.6173 0.6049
-0.250 0.0097 0.00598 0.00102 0.0073 0.6117 0.6319
0.000 0.0378 0.00592 0.00101 0.0073 0.6056 0.6525
0.250 0.0658 0.00588 0.00099 0.0072 0.5993 0.6730
0.500 0.0939 0.00584 0.00098 0.0071 0.5935 0.6887
0.750 0.1223 0.00582 0.00097 0.0070 0.5872 0.6971
1.000 0.1509 0.00583 0.00096 0.0068 0.5812 0.7041
1.250 0.1794 0.00581 0.00097 0.0066 0.5746 0.7123
1.500 0.2076 0.00581 0.00097 0.0065 0.5678 0.7216
1.750 0.2360 0.00579 0.00098 0.0064 0.5607 0.7331
2.250 0.2911 0.00571 0.00103 0.0064 0.5460 0.7708
2.500 0.3168 0.00560 0.00108 0.0069 0.5381 0.8182
2.750 0.3428 0.00553 0.00116 0.0073 0.5271 0.8697
3.000 0.3700 0.00561 0.00123 0.0075 0.5064 0.8941
3.250 0.3974 0.00575 0.00132 0.0075 0.4778 0.9107
3.500 0.4250 0.00597 0.00143 0.0074 0.4398 0.9237
3.750 0.4527 0.00627 0.00159 0.0071 0.3971 0.9343
4.000 0.4809 0.00658 0.00177 0.0068 0.3585 0.9444
4.250 0.5118 0.00686 0.00195 0.0059 0.3285 0.9520
4.500 0.5410 0.00726 0.00218 0.0052 0.2849 0.9595
4.750 0.5726 0.00774 0.00245 0.0039 0.2359 0.9645
5.000 0.6025 0.00821 0.00273 0.0030 0.1911 0.9697
5.250 0.6311 0.00866 0.00301 0.0023 0.1534 0.9739
5.500 0.6617 0.00907 0.00329 0.0012 0.1237 0.9769
5.750 0.6911 0.00949 0.00359 0.0005 0.0987 0.9809
6.500 0.7802 0.01056 0.00445 -0.0021 0.0545 0.9891
6.750 0.8103 0.01086 0.00473 -0.0029 0.0480 0.9916
7.000 0.8393 0.01119 0.00503 -0.0036 0.0414 0.9940
7.250 0.8697 0.01152 0.00534 -0.0046 0.0362 0.9953
7.500 0.9002 0.01186 0.00566 -0.0057 0.0315 0.9967
7.750 0.9303 0.01220 0.00600 -0.0067 0.0283 0.9981
8.000 0.9607 0.01258 0.00638 -0.0077 0.0251 0.9995
8.250 0.9866 0.01290 0.00672 -0.0078 0.0234 1.0000
8.500 1.0072 0.01325 0.00707 -0.0067 0.0215 1.0000
8.750 1.0274 0.01365 0.00746 -0.0056 0.0195 1.0000
9.000 1.0482 0.01398 0.00782 -0.0047 0.0184 1.0000
9.250 1.0684 0.01436 0.00822 -0.0036 0.0172 1.0000
9.500 1.0879 0.01479 0.00866 -0.0025 0.0160 1.0000
9.750 1.1070 0.01524 0.00913 -0.0013 0.0150 1.0000
10.000 1.1265 0.01564 0.00957 -0.0002 0.0144 1.0000
10.250 1.1454 0.01608 0.01005 0.0010 0.0137 1.0000
10.500 1.1636 0.01656 0.01055 0.0022 0.0130 1.0000
10.750 1.1812 0.01709 0.01110 0.0035 0.0124 1.0000
11.000 1.1975 0.01771 0.01176 0.0049 0.0117 1.0000
11.250 1.2146 0.01827 0.01237 0.0061 0.0114 1.0000
11.500 1.2312 0.01884 0.01299 0.0073 0.0111 1.0000
11.750 1.2446 0.01944 0.01366 0.0090 0.0107 1.0000
12.000 1.2573 0.02013 0.01440 0.0106 0.0103 1.0000
12.250 1.2702 0.02094 0.01525 0.0118 0.0099 1.0000
12.500 1.2829 0.02185 0.01621 0.0129 0.0096 1.0000
12.750 1.2951 0.02289 0.01730 0.0137 0.0093 1.0000
13.000 1.3057 0.02411 0.01858 0.0146 0.0089 1.0000
13.250 1.3160 0.02541 0.01995 0.0153 0.0086 1.0000
13.500 1.3280 0.02659 0.02121 0.0159 0.0085 1.0000
13.750 1.3392 0.02786 0.02256 0.0164 0.0083 1.0000
14.000 1.3494 0.02922 0.02400 0.0170 0.0081 1.0000
14.250 1.3589 0.03068 0.02553 0.0174 0.0079 1.0000
14.500 1.3678 0.03221 0.02713 0.0179 0.0077 1.0000
14.750 1.3758 0.03383 0.02883 0.0182 0.0075 1.0000
15.000 1.3828 0.03557 0.03064 0.0186 0.0072 1.0000
15.250 1.3888 0.03745 0.03259 0.0188 0.0070 1.0000
15.500 1.3932 0.03950 0.03471 0.0191 0.0068 1.0000
15.750 1.3961 0.04176 0.03705 0.0192 0.0066 1.0000
16.000 1.3964 0.04433 0.03972 0.0192 0.0065 1.0000
16.250 1.3936 0.04731 0.04280 0.0191 0.0063 1.0000
16.500 1.3923 0.05024 0.04582 0.0188 0.0062 1.0000
16.750 1.3919 0.05318 0.04887 0.0183 0.0061 1.0000
17.000 1.3905 0.05637 0.05216 0.0177 0.0061 1.0000
17.250 1.3878 0.05984 0.05574 0.0168 0.0060 1.0000
17.500 1.3834 0.06362 0.05963 0.0157 0.0059 1.0000
17.750 1.3776 0.06771 0.06383 0.0144 0.0059 1.0000
18.000 1.3701 0.07219 0.06842 0.0128 0.0058 1.0000
18.250 1.3609 0.07705 0.07340 0.0110 0.0057 1.0000
18.500 1.3491 0.08241 0.07888 0.0088 0.0057 1.0000
18.750 1.3358 0.08818 0.08478 0.0064 0.0056 1.0000
19.000 1.3202 0.09452 0.09124 0.0036 0.0056 1.0000
19.250 1.3018 0.10141 0.09827 0.0004 0.0055 1.0000
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Polar data table (+)
Polar graphs
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