RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 50,000 Max Cl/Cd: 33.25 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14-il-50000.txt Download as CSV file: xf-rg14-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4845 0.09641 0.08978 -0.0067 1.0000 0.2776
-7.750 -0.4864 0.09353 0.08699 -0.0062 1.0000 0.2911
-7.500 -0.4871 0.09060 0.08414 -0.0054 1.0000 0.3048
-7.000 -0.4662 0.08309 0.07670 -0.0024 1.0000 0.3368
-6.750 -0.4710 0.08070 0.07442 -0.0004 1.0000 0.3574
-6.500 -0.4626 0.07756 0.07133 0.0022 1.0000 0.3839
-5.750 -0.4969 0.05056 0.04308 -0.0328 1.0000 0.1227
-5.500 -0.4838 0.04551 0.03730 -0.0325 1.0000 0.1105
-5.250 -0.4675 0.04161 0.03321 -0.0315 1.0000 0.1075
-5.000 -0.4500 0.03806 0.02918 -0.0304 1.0000 0.1063
-4.750 -0.4308 0.03508 0.02553 -0.0291 1.0000 0.1097
-4.500 -0.4106 0.03232 0.02258 -0.0280 1.0000 0.1155
-4.250 -0.3875 0.02972 0.01954 -0.0266 1.0000 0.1203
-4.000 -0.3645 0.02747 0.01703 -0.0253 1.0000 0.1337
-3.750 -0.3408 0.02534 0.01465 -0.0240 1.0000 0.1552
-3.500 -0.3176 0.02354 0.01286 -0.0225 1.0000 0.1927
-3.250 -0.2933 0.02159 0.01124 -0.0212 1.0000 0.2512
-3.000 -0.1271 0.01786 0.00980 -0.0354 1.0000 1.0000
-2.750 -0.1232 0.01744 0.00914 -0.0327 1.0000 1.0000
-2.500 -0.1175 0.01716 0.00857 -0.0299 1.0000 1.0000
-2.250 -0.1110 0.01696 0.00815 -0.0269 1.0000 1.0000
-2.000 -0.1040 0.01683 0.00781 -0.0240 1.0000 1.0000
-1.750 -0.0960 0.01675 0.00753 -0.0211 1.0000 1.0000
-1.500 -0.0871 0.01672 0.00731 -0.0184 1.0000 1.0000
-1.250 -0.0765 0.01674 0.00714 -0.0161 1.0000 1.0000
-1.000 -0.0641 0.01682 0.00703 -0.0140 1.0000 1.0000
-0.750 -0.0502 0.01694 0.00698 -0.0123 1.0000 1.0000
-0.500 -0.0352 0.01710 0.00696 -0.0108 1.0000 1.0000
-0.250 -0.0196 0.01732 0.00703 -0.0095 1.0000 1.0000
0.000 -0.0036 0.01758 0.00717 -0.0083 1.0000 1.0000
0.250 0.0127 0.01790 0.00738 -0.0073 1.0000 1.0000
0.500 0.0291 0.01826 0.00765 -0.0064 1.0000 1.0000
0.750 0.0454 0.01868 0.00798 -0.0057 1.0000 1.0000
1.000 0.0616 0.01916 0.00839 -0.0050 1.0000 1.0000
1.250 0.0776 0.01970 0.00889 -0.0045 1.0000 1.0000
1.500 0.0934 0.02032 0.00947 -0.0041 1.0000 1.0000
1.750 0.1088 0.02100 0.01013 -0.0038 1.0000 1.0000
2.000 0.1471 0.02209 0.01123 -0.0080 0.9892 1.0000
2.250 0.2102 0.02339 0.01261 -0.0164 0.9657 1.0000
2.500 0.2729 0.02442 0.01377 -0.0241 0.9420 1.0000
2.750 0.3303 0.02510 0.01460 -0.0303 0.9164 1.0000
3.000 0.3855 0.02554 0.01523 -0.0356 0.8901 1.0000
3.250 0.4425 0.02571 0.01567 -0.0405 0.8632 1.0000
3.500 0.5034 0.02550 0.01575 -0.0453 0.8359 1.0000
3.750 0.5591 0.02501 0.01555 -0.0483 0.8075 1.0000
4.000 0.6100 0.02432 0.01519 -0.0497 0.7777 1.0000
4.250 0.6437 0.02402 0.01508 -0.0485 0.7436 1.0000
4.500 0.6813 0.02342 0.01463 -0.0471 0.7089 1.0000
4.750 0.7081 0.02326 0.01456 -0.0446 0.6697 1.0000
5.000 0.7338 0.02317 0.01457 -0.0418 0.6280 1.0000
5.250 0.7578 0.02322 0.01459 -0.0389 0.5834 1.0000
5.500 0.7780 0.02355 0.01486 -0.0359 0.5344 1.0000
5.750 0.7980 0.02400 0.01518 -0.0329 0.4829 1.0000
6.000 0.8165 0.02468 0.01565 -0.0300 0.4288 1.0000
6.250 0.8339 0.02561 0.01635 -0.0272 0.3739 1.0000
6.500 0.8508 0.02680 0.01725 -0.0246 0.3206 1.0000
6.750 0.8668 0.02823 0.01858 -0.0222 0.2708 1.0000
7.000 0.8849 0.03005 0.02017 -0.0201 0.2281 1.0000
7.250 0.9024 0.03217 0.02228 -0.0182 0.1921 1.0000
7.500 0.9200 0.03431 0.02432 -0.0164 0.1616 1.0000
7.750 0.9380 0.03710 0.02729 -0.0147 0.1402 1.0000
8.000 0.9551 0.03994 0.03031 -0.0130 0.1232 1.0000
8.250 0.9702 0.04385 0.03465 -0.0111 0.1147 1.0000
8.500 0.9835 0.04701 0.03797 -0.0095 0.1039 1.0000
8.750 0.9879 0.05060 0.04216 -0.0072 0.0978 1.0000
9.000 0.9976 0.05470 0.04652 -0.0056 0.0945 1.0000
9.250 1.0056 0.05985 0.05185 -0.0044 0.0928 1.0000
9.500 0.9838 0.06433 0.05714 -0.0016 0.0953 1.0000
9.750 0.9603 0.06967 0.06289 -0.0001 0.0975 1.0000
10.000 0.9346 0.07462 0.06806 0.0008 0.0998 1.0000
10.250 0.9104 0.07968 0.07323 0.0006 0.1016 1.0000
10.500 0.8914 0.08535 0.07894 -0.0012 0.1034 1.0000
10.750 0.8794 0.09146 0.08506 -0.0035 0.1048 1.0000
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Polar data table (+)
Polar graphs
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