RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 50,000 Max Cl/Cd: 32.17 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1410-il-50000.txt Download as CSV file: xf-rg1410-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4550 0.10359 0.09635 -0.0069 1.0000 0.3016
-8.750 -0.4545 0.10059 0.09340 -0.0066 1.0000 0.3147
-8.000 -0.4632 0.09276 0.08580 -0.0049 1.0000 0.3554
-7.750 -0.4435 0.08830 0.08133 -0.0040 1.0000 0.3674
-7.500 -0.4496 0.08597 0.07909 -0.0026 1.0000 0.3847
-7.250 -0.4619 0.08401 0.07726 -0.0007 1.0000 0.4011
-7.000 -0.5603 0.06316 0.05633 -0.0300 1.0000 0.1699
-6.750 -0.5749 0.05563 0.04827 -0.0318 1.0000 0.1492
-6.500 -0.5691 0.05122 0.04354 -0.0309 1.0000 0.1435
-6.250 -0.5616 0.04695 0.03892 -0.0298 1.0000 0.1394
-6.000 -0.5534 0.04263 0.03400 -0.0284 1.0000 0.1358
-5.750 -0.5396 0.03945 0.03042 -0.0269 1.0000 0.1366
-5.500 -0.5237 0.03690 0.02751 -0.0253 1.0000 0.1413
-5.250 -0.5064 0.03425 0.02426 -0.0238 1.0000 0.1456
-5.000 -0.4865 0.03171 0.02148 -0.0224 1.0000 0.1502
-4.750 -0.4658 0.02984 0.01928 -0.0210 1.0000 0.1602
-4.500 -0.4447 0.02804 0.01737 -0.0196 1.0000 0.1744
-4.250 -0.4228 0.02630 0.01555 -0.0183 1.0000 0.1930
-4.000 -0.4013 0.02480 0.01410 -0.0169 1.0000 0.2221
-3.750 -0.3800 0.02337 0.01286 -0.0154 1.0000 0.2654
-3.500 -0.3588 0.02185 0.01181 -0.0139 1.0000 0.3303
-3.250 -0.3420 0.02015 0.01089 -0.0114 1.0000 0.4406
-3.000 -0.3360 0.01847 0.01078 -0.0049 1.0000 0.6535
-2.750 -0.0872 0.02000 0.01124 -0.0343 1.0000 1.0000
-2.500 -0.0907 0.01955 0.01069 -0.0310 1.0000 1.0000
-2.250 -0.0929 0.01926 0.01029 -0.0274 1.0000 1.0000
-2.000 -0.0944 0.01907 0.00998 -0.0237 1.0000 1.0000
-1.750 -0.0953 0.01895 0.00974 -0.0199 1.0000 1.0000
-1.500 -0.0951 0.01889 0.00956 -0.0163 1.0000 1.0000
-1.250 -0.0932 0.01888 0.00944 -0.0129 1.0000 1.0000
-1.000 -0.0892 0.01894 0.00936 -0.0099 1.0000 1.0000
-0.750 -0.0829 0.01906 0.00935 -0.0073 1.0000 1.0000
-0.500 -0.0740 0.01924 0.00941 -0.0052 1.0000 1.0000
-0.250 -0.0632 0.01950 0.00953 -0.0034 1.0000 1.0000
0.000 -0.0509 0.01982 0.00974 -0.0020 1.0000 1.0000
0.250 -0.0378 0.02020 0.01001 -0.0009 1.0000 1.0000
0.500 -0.0240 0.02064 0.01037 0.0001 1.0000 1.0000
0.750 -0.0099 0.02114 0.01079 0.0009 1.0000 1.0000
1.000 0.0044 0.02171 0.01129 0.0015 1.0000 1.0000
1.250 0.0195 0.02236 0.01188 0.0019 0.9997 1.0000
1.500 0.0804 0.02379 0.01329 -0.0062 0.9796 1.0000
1.750 0.1373 0.02497 0.01447 -0.0132 0.9592 1.0000
2.000 0.1886 0.02591 0.01544 -0.0188 0.9381 1.0000
2.250 0.2402 0.02672 0.01631 -0.0241 0.9169 1.0000
2.500 0.2907 0.02738 0.01705 -0.0288 0.8955 1.0000
2.750 0.3365 0.02789 0.01768 -0.0324 0.8732 1.0000
3.000 0.3914 0.02819 0.01813 -0.0370 0.8520 1.0000
3.250 0.4348 0.02843 0.01851 -0.0395 0.8287 1.0000
3.500 0.4949 0.02812 0.01844 -0.0437 0.8061 1.0000
3.750 0.5565 0.02708 0.01765 -0.0466 0.7795 1.0000
4.000 0.6011 0.02622 0.01696 -0.0467 0.7505 1.0000
4.250 0.6375 0.02568 0.01656 -0.0458 0.7219 1.0000
4.500 0.6708 0.02527 0.01628 -0.0444 0.6926 1.0000
4.750 0.7033 0.02479 0.01587 -0.0427 0.6607 1.0000
5.000 0.7285 0.02464 0.01574 -0.0402 0.6247 1.0000
5.250 0.7562 0.02432 0.01534 -0.0376 0.5846 1.0000
5.500 0.7778 0.02438 0.01529 -0.0345 0.5393 1.0000
5.750 0.7958 0.02474 0.01551 -0.0314 0.4901 1.0000
6.000 0.8143 0.02532 0.01586 -0.0285 0.4408 1.0000
6.250 0.8326 0.02615 0.01644 -0.0259 0.3951 1.0000
6.500 0.8508 0.02720 0.01733 -0.0237 0.3546 1.0000
6.750 0.8704 0.02841 0.01836 -0.0218 0.3198 1.0000
7.000 0.8900 0.02974 0.01954 -0.0201 0.2891 1.0000
7.250 0.9092 0.03136 0.02119 -0.0185 0.2635 1.0000
7.500 0.9299 0.03300 0.02276 -0.0172 0.2410 1.0000
7.750 0.9484 0.03497 0.02491 -0.0157 0.2226 1.0000
8.000 0.9667 0.03691 0.02696 -0.0142 0.2057 1.0000
8.250 0.9839 0.03930 0.02955 -0.0127 0.1925 1.0000
8.500 0.9991 0.04174 0.03218 -0.0111 0.1801 1.0000
8.750 1.0166 0.04444 0.03497 -0.0098 0.1698 1.0000
9.000 1.0223 0.04757 0.03864 -0.0074 0.1622 1.0000
9.250 1.0318 0.05073 0.04200 -0.0057 0.1544 1.0000
9.500 1.0272 0.05475 0.04654 -0.0030 0.1509 1.0000
9.750 1.0238 0.05874 0.05088 -0.0009 0.1476 1.0000
10.000 1.0335 0.06230 0.05447 0.0003 0.1416 1.0000
10.250 1.0137 0.06694 0.05949 0.0026 0.1411 1.0000
10.500 0.9914 0.07177 0.06457 0.0044 0.1413 1.0000
10.750 0.9690 0.07655 0.06948 0.0058 0.1420 1.0000
11.000 0.9467 0.08191 0.07491 0.0059 0.1426 1.0000
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Polar data table (+)
Polar graphs
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