NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 100,000 Max Cl/Cd: 25.48 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20414-il-100000.txt Download as CSV file: xf-sc20414-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0414 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6707 0.09884 0.09279 -0.0410 1.0000 0.1208
-11.500 -0.8727 0.06997 0.06319 -0.0543 1.0000 0.0954
-11.250 -0.8894 0.06579 0.05886 -0.0537 1.0000 0.0952
-11.000 -0.9043 0.06177 0.05463 -0.0528 1.0000 0.0951
-10.750 -0.9158 0.05803 0.05061 -0.0515 1.0000 0.0952
-10.500 -0.9230 0.05454 0.04678 -0.0500 1.0000 0.0954
-10.250 -0.9225 0.05082 0.04278 -0.0488 1.0000 0.0959
-10.000 -0.9141 0.04748 0.03930 -0.0478 1.0000 0.0968
-9.750 -0.9000 0.04512 0.03689 -0.0469 1.0000 0.0981
-9.500 -0.8854 0.04328 0.03499 -0.0458 1.0000 0.1001
-9.250 -0.8729 0.04126 0.03277 -0.0447 1.0000 0.1025
-9.000 -0.8600 0.03908 0.03026 -0.0437 1.0000 0.1048
-8.750 -0.8453 0.03702 0.02780 -0.0427 1.0000 0.1069
-8.500 -0.8280 0.03481 0.02541 -0.0418 1.0000 0.1092
-8.250 -0.8090 0.03343 0.02408 -0.0408 1.0000 0.1125
-8.000 -0.7896 0.03220 0.02276 -0.0399 1.0000 0.1164
-7.750 -0.7698 0.03093 0.02120 -0.0390 1.0000 0.1201
-7.500 -0.7500 0.02941 0.01974 -0.0379 1.0000 0.1240
-7.250 -0.7299 0.02844 0.01880 -0.0369 1.0000 0.1290
-7.000 -0.7088 0.02753 0.01769 -0.0360 1.0000 0.1344
-6.750 -0.6889 0.02634 0.01664 -0.0347 1.0000 0.1399
-6.500 -0.6681 0.02553 0.01586 -0.0337 1.0000 0.1469
-6.250 -0.6476 0.02459 0.01496 -0.0326 1.0000 0.1541
-6.000 -0.6266 0.02385 0.01430 -0.0316 1.0000 0.1632
-5.750 -0.6060 0.02303 0.01363 -0.0306 1.0000 0.1736
-5.500 -0.5846 0.02228 0.01300 -0.0298 1.0000 0.1871
-5.250 -0.5623 0.02150 0.01245 -0.0293 1.0000 0.2056
-5.000 -0.5385 0.02063 0.01188 -0.0292 1.0000 0.2355
-4.750 -0.5078 0.01886 0.01102 -0.0318 1.0000 0.3271
-4.500 -0.4965 0.01911 0.01282 -0.0270 1.0000 0.5404
-4.250 -0.4787 0.02041 0.01409 -0.0237 1.0000 0.6009
-4.000 -0.4611 0.02162 0.01522 -0.0207 1.0000 0.6295
-3.750 -0.4474 0.02285 0.01641 -0.0166 1.0000 0.6474
-3.500 -0.4320 0.02390 0.01739 -0.0132 1.0000 0.6639
-3.250 -0.4252 0.02513 0.01864 -0.0071 1.0000 0.6731
-3.000 -0.4118 0.02599 0.01947 -0.0032 1.0000 0.6867
-2.750 -0.3956 0.02670 0.02012 -0.0005 1.0000 0.7020
-2.500 -0.3880 0.02751 0.02095 0.0050 1.0000 0.7120
-2.250 -0.3744 0.02802 0.02142 0.0083 1.0000 0.7248
-2.000 -0.3567 0.02840 0.02176 0.0102 1.0000 0.7394
-1.750 -0.3484 0.02882 0.02219 0.0151 1.0000 0.7500
-1.500 -0.3362 0.02908 0.02244 0.0185 1.0000 0.7627
-1.250 -0.3230 0.02931 0.02265 0.0215 1.0000 0.7771
-1.000 -0.3127 0.02953 0.02288 0.0253 1.0000 0.7932
-0.750 -0.3026 0.02964 0.02300 0.0291 1.0000 0.8094
-0.500 -0.2739 0.02987 0.02320 0.0292 0.9946 0.8251
-0.250 -0.2433 0.02981 0.02312 0.0287 0.9878 0.8340
0.000 -0.1994 0.02999 0.02326 0.0241 0.9816 0.8411
0.250 -0.1683 0.02976 0.02302 0.0232 0.9729 0.8467
0.500 -0.1257 0.02981 0.02306 0.0195 0.9628 0.8535
0.750 -0.0779 0.02982 0.02306 0.0150 0.9537 0.8587
1.000 -0.0426 0.02957 0.02283 0.0129 0.9420 0.8617
1.250 -0.0038 0.02944 0.02272 0.0102 0.9308 0.8652
1.500 0.0457 0.02925 0.02256 0.0058 0.9184 0.8684
1.750 0.1025 0.02879 0.02214 0.0006 0.9022 0.8710
2.000 0.1618 0.02795 0.02136 -0.0042 0.8863 0.8736
2.250 0.2180 0.02683 0.02032 -0.0077 0.8704 0.8763
2.500 0.2703 0.02569 0.01928 -0.0106 0.8539 0.8790
2.750 0.3173 0.02456 0.01823 -0.0126 0.8368 0.8811
3.000 0.3598 0.02352 0.01728 -0.0140 0.8191 0.8828
3.250 0.4034 0.02233 0.01617 -0.0152 0.7973 0.8846
3.500 0.4336 0.02152 0.01543 -0.0146 0.7658 0.8871
3.750 0.4653 0.02055 0.01444 -0.0136 0.7212 0.8894
4.000 0.4886 0.01990 0.01361 -0.0113 0.6322 0.8914
4.250 0.5011 0.02059 0.01303 -0.0074 0.4162 0.8932
4.500 0.5111 0.02191 0.01346 -0.0049 0.2989 0.8953
4.750 0.5304 0.02285 0.01395 -0.0041 0.2484 0.8974
5.000 0.5539 0.02369 0.01447 -0.0040 0.2198 0.9000
5.250 0.5812 0.02449 0.01513 -0.0045 0.1990 0.9026
5.500 0.6056 0.02510 0.01561 -0.0042 0.1843 0.9050
5.750 0.6329 0.02593 0.01625 -0.0045 0.1720 0.9072
6.000 0.6601 0.02653 0.01692 -0.0047 0.1611 0.9100
6.250 0.6897 0.02754 0.01789 -0.0054 0.1524 0.9130
6.500 0.7194 0.02841 0.01874 -0.0063 0.1440 0.9156
6.750 0.7491 0.02961 0.01998 -0.0071 0.1375 0.9177
7.000 0.7751 0.03042 0.02090 -0.0070 0.1312 0.9202
7.250 0.8045 0.03197 0.02229 -0.0079 0.1257 0.9226
7.500 0.8293 0.03302 0.02372 -0.0077 0.1213 0.9256
7.750 0.8561 0.03421 0.02503 -0.0080 0.1165 0.9289
8.000 0.8834 0.03586 0.02662 -0.0087 0.1126 0.9320
8.250 0.9030 0.03763 0.02880 -0.0078 0.1100 0.9353
8.500 0.9224 0.03946 0.03106 -0.0070 0.1070 0.9384
8.750 0.9439 0.04119 0.03300 -0.0068 0.1038 0.9415
9.000 0.9695 0.04291 0.03471 -0.0074 0.1011 0.9445
9.250 0.9882 0.04603 0.03796 -0.0073 0.0995 0.9479
9.500 0.9955 0.04882 0.04127 -0.0053 0.0987 0.9520
9.750 0.9988 0.05210 0.04510 -0.0034 0.0978 0.9563
10.000 0.9970 0.05567 0.04914 -0.0013 0.0971 0.9610
10.250 0.9902 0.05972 0.05362 0.0007 0.0968 0.9660
10.500 0.9795 0.06420 0.05847 0.0023 0.0972 0.9710
10.750 0.9685 0.06873 0.06327 0.0035 0.0980 0.9770
11.000 0.9643 0.07343 0.06811 0.0037 0.0988 0.9862
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Polar data table (+)
Polar graphs
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