NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: NASA/LANGLEY RC-12(N)1 AIRFOIL (rc12n1-il) Reynolds number: 500,000 Max Cl/Cd: 70.42 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12n1-il-500000-n5.txt Download as CSV file: xf-rc12n1-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8692 0.04935 0.04654 -0.0223 0.9094 0.0102
-10.500 -0.9144 0.04138 0.03791 -0.0172 0.8641 0.0104
-10.250 -0.9129 0.03876 0.03498 -0.0151 0.8455 0.0105
-10.000 -0.9060 0.03646 0.03240 -0.0134 0.8325 0.0107
-9.750 -0.8960 0.03431 0.02999 -0.0118 0.8222 0.0109
-9.500 -0.8842 0.03211 0.02751 -0.0104 0.8135 0.0111
-9.250 -0.8711 0.02989 0.02497 -0.0089 0.8063 0.0113
-9.000 -0.8560 0.02770 0.02246 -0.0075 0.7993 0.0116
-8.500 -0.8198 0.02400 0.01813 -0.0053 0.7875 0.0123
-8.250 -0.7986 0.02265 0.01653 -0.0044 0.7821 0.0128
-8.000 -0.7763 0.02154 0.01517 -0.0037 0.7772 0.0132
-7.750 -0.7530 0.02057 0.01400 -0.0031 0.7721 0.0134
-7.500 -0.7312 0.01921 0.01248 -0.0024 0.7672 0.0137
-7.250 -0.7076 0.01841 0.01157 -0.0018 0.7629 0.0140
-7.000 -0.6831 0.01775 0.01083 -0.0014 0.7583 0.0144
-6.750 -0.6585 0.01713 0.01013 -0.0010 0.7536 0.0147
-6.500 -0.6338 0.01653 0.00944 -0.0006 0.7495 0.0151
-6.250 -0.6090 0.01593 0.00876 -0.0002 0.7455 0.0155
-6.000 -0.5839 0.01538 0.00812 0.0002 0.7412 0.0160
-5.750 -0.5587 0.01490 0.00756 0.0006 0.7369 0.0166
-5.250 -0.5088 0.01384 0.00636 0.0015 0.7291 0.0177
-5.000 -0.4838 0.01334 0.00582 0.0020 0.7250 0.0184
-4.750 -0.4580 0.01298 0.00542 0.0022 0.7210 0.0191
-4.500 -0.4320 0.01265 0.00504 0.0025 0.7173 0.0201
-4.250 -0.4057 0.01232 0.00467 0.0028 0.7131 0.0211
-4.000 -0.3791 0.01203 0.00433 0.0030 0.7091 0.0221
-3.750 -0.3531 0.01168 0.00395 0.0032 0.7053 0.0238
-3.500 -0.3263 0.01145 0.00370 0.0034 0.7016 0.0259
-3.250 -0.2991 0.01125 0.00347 0.0034 0.6974 0.0281
-3.000 -0.2723 0.01097 0.00320 0.0036 0.6933 0.0315
-2.750 -0.2451 0.01079 0.00299 0.0037 0.6895 0.0352
-2.500 -0.2179 0.01058 0.00279 0.0037 0.6857 0.0414
-2.250 -0.1904 0.01039 0.00261 0.0038 0.6814 0.0496
-2.000 -0.1632 0.01019 0.00245 0.0038 0.6772 0.0641
-1.750 -0.1366 0.00991 0.00227 0.0039 0.6734 0.0988
-1.500 -0.1214 0.00813 0.00184 0.0054 0.6694 0.4597
-1.250 -0.0981 0.00766 0.00180 0.0062 0.6650 0.5811
-1.000 -0.0718 0.00751 0.00176 0.0066 0.6607 0.6271
-0.750 -0.0447 0.00742 0.00171 0.0068 0.6567 0.6561
-0.500 -0.0174 0.00732 0.00168 0.0069 0.6519 0.6792
-0.250 0.0096 0.00721 0.00163 0.0071 0.6469 0.7047
0.000 0.0365 0.00711 0.00158 0.0073 0.6424 0.7272
0.250 0.0644 0.00702 0.00155 0.0074 0.6369 0.7423
0.500 0.0922 0.00696 0.00152 0.0074 0.6312 0.7561
0.750 0.1195 0.00688 0.00151 0.0075 0.6257 0.7753
1.000 0.1466 0.00678 0.00153 0.0078 0.6194 0.8038
1.250 0.1737 0.00672 0.00158 0.0081 0.6136 0.8432
1.500 0.2023 0.00671 0.00165 0.0080 0.6075 0.8769
1.750 0.2314 0.00674 0.00169 0.0079 0.6010 0.8992
2.000 0.2613 0.00678 0.00174 0.0075 0.5948 0.9150
2.250 0.2928 0.00683 0.00181 0.0067 0.5874 0.9273
2.500 0.3253 0.00690 0.00187 0.0057 0.5802 0.9370
2.750 0.3566 0.00696 0.00194 0.0049 0.5722 0.9460
3.000 0.3909 0.00705 0.00203 0.0035 0.5641 0.9516
3.250 0.4224 0.00714 0.00210 0.0026 0.5531 0.9582
3.500 0.4557 0.00726 0.00217 0.0013 0.5319 0.9628
3.750 0.4881 0.00742 0.00226 0.0002 0.5054 0.9673
4.000 0.5173 0.00763 0.00237 -0.0003 0.4744 0.9727
4.250 0.5500 0.00791 0.00252 -0.0016 0.4370 0.9755
4.500 0.5817 0.00826 0.00271 -0.0028 0.3966 0.9791
4.750 0.6107 0.00871 0.00298 -0.0035 0.3503 0.9839
5.000 0.6418 0.00928 0.00330 -0.0049 0.2942 0.9867
5.250 0.6727 0.00985 0.00364 -0.0062 0.2431 0.9896
5.500 0.7024 0.01047 0.00404 -0.0073 0.1898 0.9927
5.750 0.7326 0.01108 0.00443 -0.0086 0.1459 0.9952
6.000 0.7637 0.01164 0.00483 -0.0099 0.1124 0.9973
6.500 0.8198 0.01258 0.00560 -0.0112 0.0733 1.0000
6.750 0.8409 0.01298 0.00595 -0.0103 0.0621 1.0000
7.000 0.8618 0.01337 0.00631 -0.0093 0.0537 1.0000
7.250 0.8829 0.01373 0.00668 -0.0084 0.0479 1.0000
7.500 0.9033 0.01415 0.00708 -0.0073 0.0422 1.0000
7.750 0.9241 0.01451 0.00747 -0.0063 0.0385 1.0000
8.000 0.9440 0.01496 0.00790 -0.0052 0.0343 1.0000
8.250 0.9639 0.01538 0.00836 -0.0042 0.0313 1.0000
8.500 0.9836 0.01582 0.00882 -0.0030 0.0287 1.0000
8.750 1.0021 0.01634 0.00934 -0.0018 0.0263 1.0000
9.000 1.0206 0.01685 0.00989 -0.0005 0.0246 1.0000
9.250 1.0390 0.01734 0.01044 0.0007 0.0232 1.0000
9.500 1.0567 0.01788 0.01102 0.0020 0.0217 1.0000
9.750 1.0729 0.01852 0.01167 0.0035 0.0202 1.0000
10.000 1.0890 0.01917 0.01237 0.0049 0.0191 1.0000
10.250 1.1054 0.01978 0.01305 0.0062 0.0183 1.0000
10.500 1.1207 0.02045 0.01380 0.0076 0.0175 1.0000
10.750 1.1335 0.02117 0.01457 0.0093 0.0168 1.0000
11.000 1.1442 0.02198 0.01543 0.0112 0.0161 1.0000
11.250 1.1532 0.02306 0.01655 0.0128 0.0154 1.0000
11.500 1.1644 0.02411 0.01768 0.0140 0.0148 1.0000
11.750 1.1767 0.02516 0.01882 0.0149 0.0143 1.0000
12.000 1.1882 0.02632 0.02006 0.0157 0.0138 1.0000
12.250 1.1991 0.02758 0.02141 0.0165 0.0134 1.0000
12.500 1.2095 0.02891 0.02282 0.0171 0.0130 1.0000
12.750 1.2192 0.03033 0.02431 0.0177 0.0126 1.0000
13.000 1.2275 0.03190 0.02595 0.0183 0.0122 1.0000
13.250 1.2329 0.03377 0.02789 0.0189 0.0118 1.0000
13.500 1.2370 0.03579 0.03000 0.0195 0.0115 1.0000
13.750 1.2443 0.03756 0.03189 0.0198 0.0113 1.0000
14.000 1.2503 0.03947 0.03391 0.0201 0.0110 1.0000
14.250 1.2550 0.04155 0.03609 0.0204 0.0107 1.0000
14.500 1.2586 0.04379 0.03846 0.0205 0.0104 1.0000
14.750 1.2610 0.04619 0.04097 0.0205 0.0102 1.0000
15.000 1.2622 0.04879 0.04368 0.0204 0.0099 1.0000
15.250 1.2626 0.05156 0.04655 0.0201 0.0097 1.0000
15.500 1.2617 0.05453 0.04963 0.0197 0.0096 1.0000
15.750 1.2600 0.05778 0.05299 0.0190 0.0094 1.0000
16.000 1.2569 0.06135 0.05667 0.0180 0.0092 1.0000
16.250 1.2517 0.06531 0.06074 0.0168 0.0091 1.0000
16.500 1.2446 0.06970 0.06524 0.0154 0.0090 1.0000
16.750 1.2354 0.07456 0.07022 0.0136 0.0088 1.0000
17.000 1.2238 0.07990 0.07569 0.0115 0.0087 1.0000
17.250 1.2127 0.08537 0.08129 0.0092 0.0087 1.0000
17.500 1.2023 0.09096 0.08702 0.0067 0.0086 1.0000
17.750 1.1901 0.09696 0.09317 0.0039 0.0085 1.0000
18.000 1.1764 0.10337 0.09972 0.0009 0.0085 1.0000
18.250 1.1614 0.11021 0.10671 -0.0024 0.0084 1.0000
18.500 1.1451 0.11744 0.11408 -0.0061 0.0084 1.0000
18.750 1.1277 0.12508 0.12185 -0.0100 0.0084 1.0000
19.000 1.1092 0.13318 0.13008 -0.0142 0.0084 1.0000
19.250 1.0898 0.14177 0.13881 -0.0189 0.0084 1.0000
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