NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| 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: 92.89 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc12n1-il-1000000.txt Download as CSV file: xf-rc12n1-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4898 0.10281 0.10098 -0.0014 0.8335 0.0156
-10.750 -0.4992 0.09666 0.09481 -0.0037 0.8272 0.0164
-8.750 -0.8373 0.02785 0.02357 -0.0063 0.8011 0.0130
-8.500 -0.8197 0.02602 0.02143 -0.0051 0.7952 0.0133
-8.250 -0.8000 0.02465 0.01980 -0.0040 0.7899 0.0134
-8.000 -0.7891 0.02020 0.01483 -0.0019 0.7848 0.0138
-7.750 -0.7669 0.01898 0.01347 -0.0012 0.7798 0.0142
-7.500 -0.7428 0.01827 0.01268 -0.0008 0.7753 0.0145
-7.250 -0.7182 0.01758 0.01191 -0.0004 0.7706 0.0148
-7.000 -0.6932 0.01697 0.01119 0.0000 0.7661 0.0152
-6.750 -0.6679 0.01644 0.01057 0.0003 0.7617 0.0158
-6.500 -0.6425 0.01577 0.00983 0.0006 0.7575 0.0162
-6.250 -0.6172 0.01504 0.00900 0.0011 0.7533 0.0166
-6.000 -0.5919 0.01441 0.00827 0.0015 0.7493 0.0168
-5.750 -0.5662 0.01387 0.00766 0.0018 0.7454 0.0171
-5.500 -0.5402 0.01339 0.00713 0.0021 0.7412 0.0173
-5.250 -0.5178 0.01231 0.00595 0.0031 0.7371 0.0178
-5.000 -0.4936 0.01169 0.00526 0.0037 0.7333 0.0185
-4.750 -0.4672 0.01134 0.00491 0.0039 0.7295 0.0193
-4.500 -0.4405 0.01105 0.00460 0.0040 0.7254 0.0202
-4.250 -0.4140 0.01074 0.00425 0.0043 0.7214 0.0211
-4.000 -0.3873 0.01051 0.00395 0.0045 0.7175 0.0219
-3.750 -0.3615 0.01003 0.00344 0.0048 0.7138 0.0234
-3.500 -0.3345 0.00976 0.00316 0.0050 0.7097 0.0253
-3.250 -0.3071 0.00958 0.00295 0.0050 0.7057 0.0274
-3.000 -0.2800 0.00936 0.00269 0.0052 0.7018 0.0298
-2.750 -0.2526 0.00913 0.00248 0.0052 0.6979 0.0340
-2.500 -0.2248 0.00895 0.00229 0.0052 0.6938 0.0387
-2.250 -0.1973 0.00878 0.00213 0.0052 0.6898 0.0466
-2.000 -0.1701 0.00855 0.00197 0.0053 0.6858 0.0661
-1.750 -0.1445 0.00805 0.00178 0.0056 0.6816 0.1506
-1.500 -0.1272 0.00655 0.00140 0.0069 0.6774 0.4698
-1.250 -0.1034 0.00611 0.00135 0.0076 0.6731 0.5909
-1.000 -0.0764 0.00595 0.00133 0.0078 0.6688 0.6378
-0.750 -0.0488 0.00585 0.00130 0.0078 0.6640 0.6635
-0.500 -0.0210 0.00580 0.00126 0.0079 0.6593 0.6853
-0.250 0.0069 0.00573 0.00123 0.0079 0.6544 0.7041
0.000 0.0346 0.00563 0.00119 0.0079 0.6491 0.7222
0.250 0.0617 0.00553 0.00115 0.0081 0.6439 0.7463
0.500 0.0883 0.00538 0.00113 0.0084 0.6389 0.7771
0.750 0.1142 0.00521 0.00114 0.0089 0.6337 0.8221
1.000 0.1402 0.00513 0.00118 0.0094 0.6284 0.8721
1.250 0.1679 0.00510 0.00123 0.0096 0.6232 0.9011
1.500 0.1964 0.00510 0.00126 0.0096 0.6174 0.9204
1.750 0.2256 0.00515 0.00130 0.0093 0.6118 0.9350
2.000 0.2555 0.00517 0.00135 0.0089 0.6058 0.9466
2.250 0.2878 0.00524 0.00140 0.0080 0.5997 0.9549
2.500 0.3197 0.00530 0.00147 0.0071 0.5935 0.9621
2.750 0.3532 0.00538 0.00153 0.0059 0.5851 0.9672
3.000 0.3831 0.00546 0.00159 0.0054 0.5730 0.9732
3.250 0.4184 0.00556 0.00166 0.0037 0.5592 0.9756
3.500 0.4537 0.00567 0.00173 0.0020 0.5438 0.9781
3.750 0.4872 0.00579 0.00181 0.0006 0.5283 0.9813
4.000 0.5181 0.00591 0.00190 -0.0001 0.5126 0.9848
4.250 0.5536 0.00607 0.00200 -0.0020 0.4907 0.9862
4.500 0.5880 0.00633 0.00213 -0.0037 0.4518 0.9879
4.750 0.6211 0.00669 0.00230 -0.0052 0.4046 0.9899
5.000 0.6531 0.00712 0.00253 -0.0066 0.3542 0.9921
5.250 0.6839 0.00759 0.00280 -0.0077 0.3058 0.9943
5.500 0.7172 0.00815 0.00310 -0.0096 0.2476 0.9955
5.750 0.7493 0.00882 0.00346 -0.0113 0.1840 0.9969
6.000 0.7805 0.00951 0.00387 -0.0128 0.1280 0.9983
6.250 0.8125 0.01001 0.00422 -0.0142 0.0974 0.9995
6.500 0.8392 0.01042 0.00453 -0.0145 0.0781 1.0000
6.750 0.8610 0.01078 0.00482 -0.0137 0.0651 1.0000
7.000 0.8827 0.01112 0.00513 -0.0128 0.0558 1.0000
7.250 0.9042 0.01144 0.00543 -0.0119 0.0484 1.0000
7.500 0.9248 0.01183 0.00579 -0.0108 0.0416 1.0000
7.750 0.9462 0.01213 0.00609 -0.0099 0.0379 1.0000
8.000 0.9658 0.01260 0.00654 -0.0086 0.0327 1.0000
8.250 0.9872 0.01288 0.00685 -0.0077 0.0308 1.0000
8.500 1.0073 0.01329 0.00725 -0.0066 0.0280 1.0000
8.750 1.0259 0.01382 0.00780 -0.0052 0.0250 1.0000
9.000 1.0466 0.01416 0.00817 -0.0042 0.0237 1.0000
9.250 1.0663 0.01458 0.00861 -0.0030 0.0222 1.0000
9.500 1.0835 0.01519 0.00924 -0.0015 0.0204 1.0000
9.750 1.1002 0.01582 0.00992 0.0000 0.0193 1.0000
10.000 1.1197 0.01621 0.01035 0.0011 0.0186 1.0000
10.250 1.1380 0.01667 0.01085 0.0024 0.0177 1.0000
10.500 1.1556 0.01719 0.01141 0.0037 0.0170 1.0000
10.750 1.1713 0.01785 0.01209 0.0051 0.0162 1.0000
11.000 1.1804 0.01895 0.01326 0.0074 0.0153 1.0000
11.250 1.1933 0.01965 0.01403 0.0092 0.0149 1.0000
11.500 1.2068 0.02026 0.01469 0.0108 0.0146 1.0000
11.750 1.2199 0.02100 0.01549 0.0122 0.0141 1.0000
12.000 1.2332 0.02184 0.01640 0.0132 0.0136 1.0000
12.250 1.2461 0.02280 0.01740 0.0141 0.0132 1.0000
12.500 1.2584 0.02387 0.01852 0.0149 0.0128 1.0000
12.750 1.2679 0.02522 0.01992 0.0158 0.0123 1.0000
13.000 1.2705 0.02721 0.02200 0.0168 0.0119 1.0000
13.250 1.2729 0.02928 0.02419 0.0178 0.0115 1.0000
13.500 1.2841 0.03060 0.02558 0.0183 0.0114 1.0000
13.750 1.2938 0.03207 0.02714 0.0187 0.0111 1.0000
14.000 1.3025 0.03365 0.02881 0.0191 0.0108 1.0000
14.250 1.3100 0.03536 0.03060 0.0195 0.0106 1.0000
14.500 1.3175 0.03712 0.03243 0.0197 0.0103 1.0000
14.750 1.3237 0.03900 0.03439 0.0199 0.0100 1.0000
15.000 1.3287 0.04106 0.03651 0.0200 0.0097 1.0000
15.250 1.3319 0.04335 0.03888 0.0200 0.0095 1.0000
15.500 1.3313 0.04607 0.04168 0.0200 0.0093 1.0000
15.750 1.3265 0.04933 0.04503 0.0198 0.0091 1.0000
16.000 1.3161 0.05339 0.04921 0.0193 0.0089 1.0000
16.250 1.2985 0.05855 0.05455 0.0185 0.0087 1.0000
16.500 1.2958 0.06214 0.05824 0.0175 0.0086 1.0000
16.750 1.2933 0.06578 0.06200 0.0163 0.0086 1.0000
17.000 1.2891 0.06982 0.06615 0.0149 0.0085 1.0000
17.250 1.2828 0.07426 0.07070 0.0133 0.0084 1.0000
17.500 1.2749 0.07905 0.07563 0.0114 0.0083 1.0000
17.750 1.2651 0.08429 0.08098 0.0092 0.0082 1.0000
18.000 1.2535 0.08997 0.08679 0.0067 0.0082 1.0000
18.250 1.2402 0.09607 0.09302 0.0039 0.0081 1.0000
18.500 1.2249 0.10262 0.09969 0.0009 0.0081 1.0000
18.750 1.2088 0.10953 0.10673 -0.0025 0.0080 1.0000
19.000 1.1908 0.11694 0.11427 -0.0062 0.0080 1.0000
19.250 1.1716 0.12472 0.12217 -0.0101 0.0080 1.0000
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Polar data table (+)
Polar graphs
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