RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 50,000 Max Cl/Cd: 33.59 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1410-il-50000-n5.txt Download as CSV file: xf-rg1410-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 10% 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5384 0.09209 0.08477 -0.0338 1.0000 0.0557
-9.750 -0.5430 0.08679 0.07952 -0.0364 1.0000 0.0554
-9.500 -0.5513 0.08101 0.07379 -0.0399 1.0000 0.0550
-9.250 -0.5655 0.07585 0.06867 -0.0424 1.0000 0.0546
-9.000 -0.5823 0.07154 0.06436 -0.0430 1.0000 0.0543
-8.750 -0.5978 0.06700 0.05975 -0.0432 1.0000 0.0541
-8.500 -0.6095 0.06272 0.05534 -0.0428 1.0000 0.0539
-8.250 -0.6182 0.05854 0.05096 -0.0418 1.0000 0.0539
-8.000 -0.6239 0.05440 0.04652 -0.0405 1.0000 0.0542
-7.750 -0.6263 0.05046 0.04216 -0.0388 1.0000 0.0549
-7.500 -0.6246 0.04681 0.03805 -0.0370 1.0000 0.0563
-7.000 -0.6021 0.04220 0.03314 -0.0340 1.0000 0.0605
-6.750 -0.5901 0.03941 0.02996 -0.0323 1.0000 0.0619
-6.500 -0.5758 0.03678 0.02691 -0.0306 1.0000 0.0637
-6.250 -0.5592 0.03438 0.02407 -0.0290 1.0000 0.0661
-6.000 -0.5415 0.03245 0.02183 -0.0276 1.0000 0.0699
-5.750 -0.5231 0.03103 0.02033 -0.0262 1.0000 0.0744
-5.500 -0.5027 0.02939 0.01840 -0.0248 1.0000 0.0789
-5.250 -0.4820 0.02786 0.01668 -0.0234 1.0000 0.0835
-5.000 -0.4622 0.02676 0.01552 -0.0220 1.0000 0.0920
-4.750 -0.4422 0.02567 0.01440 -0.0207 1.0000 0.1019
-4.500 -0.4221 0.02465 0.01335 -0.0193 1.0000 0.1154
-4.250 -0.4021 0.02373 0.01241 -0.0180 1.0000 0.1349
-4.000 -0.3823 0.02282 0.01159 -0.0168 1.0000 0.1615
-3.750 -0.3622 0.02193 0.01087 -0.0158 1.0000 0.1989
-3.500 -0.3441 0.02106 0.01026 -0.0145 1.0000 0.2476
-3.250 -0.3268 0.02021 0.00977 -0.0130 1.0000 0.3176
-3.000 -0.3107 0.01937 0.00944 -0.0112 1.0000 0.4148
-2.750 -0.2970 0.01860 0.00932 -0.0083 1.0000 0.5441
-2.500 -0.2839 0.01825 0.00968 -0.0038 1.0000 0.6989
-2.250 -0.2644 0.01837 0.00991 -0.0007 1.0000 0.8265
-2.000 -0.2207 0.01863 0.01000 -0.0024 1.0000 0.9160
-1.750 -0.1304 0.01891 0.00985 -0.0138 1.0000 0.9830
-1.500 -0.0972 0.01892 0.00963 -0.0161 1.0000 1.0000
-1.250 -0.0900 0.01893 0.00949 -0.0137 0.9987 1.0000
-1.000 -0.0463 0.01915 0.00949 -0.0178 0.9865 1.0000
-0.750 -0.0046 0.01933 0.00948 -0.0214 0.9739 1.0000
-0.500 0.0358 0.01948 0.00948 -0.0246 0.9607 1.0000
-0.250 0.0753 0.01961 0.00948 -0.0274 0.9473 1.0000
0.000 0.1144 0.01971 0.00948 -0.0301 0.9336 1.0000
0.250 0.1533 0.01979 0.00948 -0.0326 0.9199 1.0000
0.500 0.1927 0.01984 0.00948 -0.0351 0.9060 1.0000
0.750 0.2325 0.01985 0.00946 -0.0375 0.8921 1.0000
1.000 0.2707 0.01983 0.00943 -0.0395 0.8773 1.0000
1.250 0.3063 0.01980 0.00940 -0.0408 0.8616 1.0000
1.500 0.3404 0.01976 0.00938 -0.0418 0.8453 1.0000
1.750 0.3732 0.01973 0.00937 -0.0424 0.8286 1.0000
2.000 0.4054 0.01969 0.00936 -0.0428 0.8115 1.0000
2.250 0.4351 0.01968 0.00937 -0.0427 0.7932 1.0000
2.500 0.4608 0.01973 0.00945 -0.0418 0.7730 1.0000
2.750 0.4891 0.01974 0.00950 -0.0413 0.7533 1.0000
3.000 0.5161 0.01978 0.00957 -0.0406 0.7328 1.0000
3.250 0.5411 0.01986 0.00968 -0.0395 0.7102 1.0000
3.500 0.5657 0.01992 0.00975 -0.0381 0.6849 1.0000
3.750 0.5895 0.01997 0.00978 -0.0366 0.6564 1.0000
4.000 0.6120 0.02008 0.00985 -0.0348 0.6264 1.0000
4.250 0.6343 0.02026 0.01003 -0.0332 0.5972 1.0000
4.500 0.6568 0.02051 0.01027 -0.0317 0.5699 1.0000
4.750 0.6785 0.02081 0.01054 -0.0301 0.5412 1.0000
5.000 0.6993 0.02115 0.01088 -0.0285 0.5108 1.0000
5.250 0.7191 0.02155 0.01125 -0.0267 0.4775 1.0000
5.500 0.7381 0.02199 0.01166 -0.0248 0.4421 1.0000
5.750 0.7560 0.02251 0.01209 -0.0229 0.4044 1.0000
6.000 0.7733 0.02313 0.01260 -0.0210 0.3663 1.0000
6.250 0.7901 0.02385 0.01322 -0.0192 0.3281 1.0000
6.500 0.8067 0.02468 0.01395 -0.0174 0.2934 1.0000
6.750 0.8232 0.02561 0.01475 -0.0158 0.2623 1.0000
7.000 0.8402 0.02662 0.01568 -0.0143 0.2348 1.0000
7.250 0.8575 0.02768 0.01671 -0.0129 0.2108 1.0000
7.500 0.8746 0.02881 0.01777 -0.0115 0.1915 1.0000
7.750 0.8924 0.03002 0.01900 -0.0102 0.1744 1.0000
8.000 0.9102 0.03129 0.02030 -0.0090 0.1590 1.0000
8.250 0.9289 0.03267 0.02168 -0.0079 0.1464 1.0000
8.500 0.9468 0.03407 0.02312 -0.0068 0.1343 1.0000
8.750 0.9653 0.03557 0.02485 -0.0057 0.1236 1.0000
9.000 0.9832 0.03718 0.02662 -0.0046 0.1144 1.0000
9.250 0.9997 0.03864 0.02810 -0.0035 0.1065 1.0000
9.500 1.0157 0.04060 0.03044 -0.0022 0.0992 1.0000
9.750 1.0316 0.04219 0.03195 -0.0012 0.0931 1.0000
10.000 1.0413 0.04445 0.03471 0.0006 0.0869 1.0000
10.250 1.0544 0.04650 0.03689 0.0018 0.0825 1.0000
10.500 1.0629 0.04898 0.03960 0.0033 0.0784 1.0000
10.750 1.0627 0.05173 0.04276 0.0054 0.0744 1.0000
11.000 1.0637 0.05398 0.04522 0.0075 0.0709 1.0000
11.250 1.0708 0.05635 0.04762 0.0088 0.0683 1.0000
11.500 1.0588 0.05981 0.05141 0.0109 0.0668 1.0000
11.750 1.0399 0.06380 0.05577 0.0124 0.0657 1.0000
12.000 1.0191 0.06837 0.06062 0.0126 0.0651 1.0000
12.250 0.9954 0.07375 0.06625 0.0114 0.0649 1.0000
12.500 0.9686 0.08032 0.07301 0.0086 0.0652 1.0000
12.750 0.9396 0.08827 0.08107 0.0041 0.0659 1.0000
13.000 0.9086 0.09787 0.09076 -0.0019 0.0666 1.0000
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Polar data table (+)
Polar graphs
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