RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.53 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14a147-il-1000000-n5.txt Download as CSV file: xf-rg14a147-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14A-1.4/7.0 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5383 0.08361 0.08202 -0.0137 1.0000 0.0027
-8.500 -0.5420 0.07916 0.07760 -0.0161 1.0000 0.0026
-8.250 -0.5488 0.07476 0.07323 -0.0187 1.0000 0.0026
-8.000 -0.5590 0.06961 0.06810 -0.0232 1.0000 0.0024
-7.750 -0.5604 0.06404 0.06250 -0.0274 1.0000 0.0026
-7.500 -0.5605 0.05828 0.05667 -0.0303 1.0000 0.0026
-7.250 -0.5590 0.05256 0.05084 -0.0320 1.0000 0.0026
-7.000 -0.5558 0.04681 0.04494 -0.0325 1.0000 0.0027
-6.750 -0.5510 0.04114 0.03907 -0.0320 1.0000 0.0027
-6.500 -0.5418 0.03450 0.03212 -0.0316 0.9995 0.0027
-6.250 -0.5171 0.02807 0.02530 -0.0332 0.9970 0.0029
-6.000 -0.4902 0.02300 0.01978 -0.0344 0.9946 0.0031
-5.750 -0.4644 0.01900 0.01530 -0.0347 0.9917 0.0031
-5.500 -0.4371 0.01591 0.01176 -0.0350 0.9885 0.0031
-5.250 -0.4076 0.01374 0.00924 -0.0355 0.9857 0.0030
-5.000 -0.3767 0.01209 0.00731 -0.0362 0.9835 0.0030
-4.750 -0.3455 0.01077 0.00578 -0.0370 0.9813 0.0031
-4.500 -0.3189 0.00989 0.00477 -0.0367 0.9756 0.0031
-4.250 -0.2884 0.00913 0.00389 -0.0373 0.9711 0.0033
-4.000 -0.2583 0.00859 0.00325 -0.0378 0.9653 0.0035
-3.750 -0.2275 0.00801 0.00255 -0.0384 0.9579 0.0044
-3.500 -0.1960 0.00767 0.00218 -0.0391 0.9487 0.0062
-3.250 -0.1643 0.00744 0.00191 -0.0400 0.9366 0.0081
-3.000 -0.1345 0.00722 0.00163 -0.0403 0.9200 0.0126
-2.750 -0.1067 0.00706 0.00142 -0.0402 0.9000 0.0203
-2.500 -0.0805 0.00686 0.00124 -0.0398 0.8777 0.0457
-2.250 -0.0545 0.00672 0.00110 -0.0394 0.8544 0.0700
-2.000 -0.0286 0.00659 0.00098 -0.0390 0.8304 0.1022
-1.750 -0.0033 0.00639 0.00087 -0.0385 0.8029 0.1611
-1.500 0.0214 0.00610 0.00076 -0.0380 0.7739 0.2543
-1.250 0.0473 0.00600 0.00069 -0.0377 0.7526 0.3032
-1.000 0.0735 0.00586 0.00064 -0.0374 0.7358 0.3592
-0.750 0.0994 0.00561 0.00061 -0.0372 0.7189 0.4458
-0.500 0.1252 0.00538 0.00056 -0.0369 0.6966 0.5324
-0.250 0.1485 0.00495 0.00054 -0.0361 0.6652 0.6925
0.000 0.1725 0.00483 0.00059 -0.0352 0.6352 0.7830
0.250 0.1982 0.00489 0.00062 -0.0347 0.6065 0.8132
0.500 0.2241 0.00497 0.00065 -0.0342 0.5780 0.8374
0.750 0.2500 0.00506 0.00069 -0.0338 0.5497 0.8561
1.000 0.2760 0.00516 0.00073 -0.0333 0.5205 0.8723
1.250 0.3015 0.00528 0.00079 -0.0328 0.4890 0.8886
1.500 0.3269 0.00542 0.00085 -0.0322 0.4571 0.9030
1.750 0.3518 0.00557 0.00093 -0.0316 0.4237 0.9185
2.000 0.3764 0.00571 0.00100 -0.0308 0.3928 0.9362
2.250 0.4020 0.00587 0.00109 -0.0303 0.3610 0.9558
2.500 0.4321 0.00609 0.00119 -0.0308 0.3241 0.9721
2.750 0.4635 0.00639 0.00131 -0.0318 0.2756 0.9831
3.000 0.4950 0.00674 0.00147 -0.0329 0.2256 0.9898
3.250 0.5250 0.00718 0.00166 -0.0337 0.1652 0.9960
3.500 0.5531 0.00759 0.00186 -0.0341 0.1175 1.0000
3.750 0.5774 0.00788 0.00204 -0.0335 0.0929 1.0000
4.000 0.6020 0.00819 0.00224 -0.0330 0.0685 1.0000
4.250 0.6268 0.00850 0.00249 -0.0325 0.0486 1.0000
4.500 0.6518 0.00881 0.00274 -0.0320 0.0320 1.0000
4.750 0.6769 0.00914 0.00301 -0.0316 0.0194 1.0000
5.000 0.7024 0.00944 0.00329 -0.0312 0.0138 1.0000
5.250 0.7283 0.00968 0.00357 -0.0309 0.0127 1.0000
5.500 0.7539 0.00997 0.00389 -0.0305 0.0114 1.0000
5.750 0.7793 0.01029 0.00421 -0.0301 0.0095 1.0000
6.000 0.8043 0.01068 0.00465 -0.0297 0.0083 1.0000
6.250 0.8290 0.01114 0.00524 -0.0291 0.0074 1.0000
6.500 0.8550 0.01133 0.00545 -0.0289 0.0072 1.0000
6.750 0.8809 0.01154 0.00567 -0.0287 0.0063 1.0000
7.000 0.9061 0.01184 0.00595 -0.0285 0.0041 1.0000
7.250 0.9305 0.01229 0.00641 -0.0280 0.0028 1.0000
7.500 0.9549 0.01276 0.00693 -0.0275 0.0024 1.0000
7.750 0.9789 0.01326 0.00750 -0.0270 0.0021 1.0000
8.000 1.0026 0.01382 0.00814 -0.0264 0.0018 1.0000
8.250 1.0256 0.01447 0.00889 -0.0257 0.0015 1.0000
8.500 1.0473 0.01533 0.00988 -0.0249 0.0013 1.0000
8.750 1.0671 0.01648 0.01122 -0.0237 0.0011 1.0000
9.000 1.0894 0.01715 0.01199 -0.0230 0.0011 1.0000
9.250 1.1111 0.01789 0.01284 -0.0222 0.0010 1.0000
9.500 1.1314 0.01883 0.01392 -0.0213 0.0010 1.0000
9.750 1.1507 0.01990 0.01515 -0.0202 0.0009 1.0000
10.000 1.1682 0.02119 0.01663 -0.0190 0.0009 1.0000
10.250 1.1839 0.02268 0.01833 -0.0175 0.0008 1.0000
10.500 1.1971 0.02446 0.02039 -0.0158 0.0008 1.0000
10.750 1.2080 0.02639 0.02257 -0.0139 0.0007 1.0000
11.000 1.2142 0.02876 0.02523 -0.0116 0.0007 1.0000
11.250 1.2168 0.03125 0.02800 -0.0091 0.0007 1.0000
11.500 1.2080 0.03435 0.03142 -0.0055 0.0007 1.0000
11.750 1.1954 0.03692 0.03421 -0.0014 0.0007 1.0000
12.000 1.1780 0.04008 0.03759 0.0016 0.0007 1.0000
12.250 1.1587 0.04396 0.04168 0.0027 0.0007 1.0000
12.500 1.1382 0.04892 0.04682 0.0017 0.0007 1.0000
12.750 1.1178 0.05518 0.05326 -0.0019 0.0007 1.0000
13.000 1.0974 0.06326 0.06149 -0.0078 0.0007 1.0000
13.250 1.0716 0.07460 0.07299 -0.0162 0.0007 1.0000
13.500 1.0453 0.08705 0.08554 -0.0240 0.0007 1.0000
13.750 1.0062 0.10215 0.10069 -0.0317 0.0007 1.0000
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Polar data table (+)
Polar graphs
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