RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 50,000 Max Cl/Cd: 34.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14-il-50000-n5.txt Download as CSV file: xf-rg14-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5093 0.10219 0.09508 -0.0225 1.0000 0.0450
-9.250 -0.5074 0.09813 0.09108 -0.0237 1.0000 0.0447
-9.000 -0.5066 0.09402 0.08703 -0.0250 1.0000 0.0443
-8.750 -0.5078 0.08972 0.08280 -0.0268 1.0000 0.0439
-8.500 -0.5100 0.08546 0.07861 -0.0288 1.0000 0.0433
-8.250 -0.5146 0.08113 0.07436 -0.0310 1.0000 0.0427
-8.000 -0.5204 0.07669 0.06996 -0.0330 1.0000 0.0422
-7.750 -0.5248 0.07215 0.06542 -0.0346 1.0000 0.0416
-7.500 -0.5284 0.06767 0.06090 -0.0358 1.0000 0.0410
-7.250 -0.5311 0.06317 0.05629 -0.0365 1.0000 0.0405
-7.000 -0.5316 0.05875 0.05171 -0.0367 1.0000 0.0400
-6.750 -0.5296 0.05439 0.04711 -0.0365 1.0000 0.0396
-6.500 -0.5245 0.05023 0.04264 -0.0359 1.0000 0.0394
-6.250 -0.5163 0.04622 0.03825 -0.0350 1.0000 0.0394
-6.000 -0.5051 0.04250 0.03403 -0.0339 1.0000 0.0396
-5.750 -0.4912 0.03899 0.03004 -0.0327 1.0000 0.0402
-5.500 -0.4745 0.03585 0.02639 -0.0313 1.0000 0.0410
-5.250 -0.4554 0.03301 0.02303 -0.0299 1.0000 0.0425
-5.000 -0.4346 0.03068 0.02017 -0.0286 1.0000 0.0459
-4.750 -0.4151 0.02903 0.01845 -0.0275 1.0000 0.0517
-4.500 -0.3924 0.02717 0.01619 -0.0261 1.0000 0.0569
-4.250 -0.3710 0.02554 0.01452 -0.0248 1.0000 0.0640
-4.000 -0.3495 0.02425 0.01313 -0.0235 1.0000 0.0788
-3.750 -0.3273 0.02292 0.01164 -0.0222 1.0000 0.0989
-3.500 -0.3051 0.02167 0.01046 -0.0213 1.0000 0.1284
-3.250 -0.2847 0.02050 0.00950 -0.0202 1.0000 0.1785
-3.000 -0.2657 0.01923 0.00876 -0.0191 1.0000 0.2682
-2.750 -0.2501 0.01787 0.00828 -0.0172 1.0000 0.4344
-2.500 -0.2402 0.01682 0.00842 -0.0121 1.0000 0.6764
-2.250 -0.2090 0.01680 0.00854 -0.0100 1.0000 0.8890
-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 0.0082 0.01743 0.00710 -0.0147 0.9878 1.0000
0.000 0.0513 0.01772 0.00725 -0.0184 0.9746 1.0000
0.250 0.0934 0.01797 0.00737 -0.0218 0.9609 1.0000
0.500 0.1348 0.01818 0.00749 -0.0249 0.9467 1.0000
0.750 0.1763 0.01835 0.00761 -0.0280 0.9322 1.0000
1.000 0.2179 0.01846 0.00771 -0.0309 0.9175 1.0000
1.250 0.2602 0.01853 0.00778 -0.0338 0.9027 1.0000
1.500 0.3020 0.01855 0.00784 -0.0364 0.8873 1.0000
1.750 0.3369 0.01858 0.00793 -0.0376 0.8685 1.0000
2.000 0.3736 0.01857 0.00797 -0.0389 0.8502 1.0000
2.250 0.4097 0.01854 0.00800 -0.0400 0.8313 1.0000
2.500 0.4409 0.01855 0.00808 -0.0401 0.8093 1.0000
2.750 0.4722 0.01856 0.00820 -0.0402 0.7868 1.0000
3.000 0.5034 0.01856 0.00826 -0.0400 0.7637 1.0000
3.250 0.5306 0.01863 0.00839 -0.0392 0.7375 1.0000
3.500 0.5573 0.01873 0.00854 -0.0383 0.7103 1.0000
3.750 0.5832 0.01886 0.00877 -0.0372 0.6817 1.0000
4.000 0.6079 0.01905 0.00900 -0.0359 0.6510 1.0000
4.250 0.6318 0.01929 0.00927 -0.0346 0.6185 1.0000
4.500 0.6555 0.01957 0.00954 -0.0332 0.5852 1.0000
4.750 0.6778 0.01991 0.00991 -0.0316 0.5493 1.0000
5.000 0.6996 0.02031 0.01036 -0.0301 0.5123 1.0000
5.250 0.7207 0.02077 0.01079 -0.0284 0.4738 1.0000
5.500 0.7409 0.02130 0.01130 -0.0268 0.4333 1.0000
5.750 0.7603 0.02192 0.01188 -0.0251 0.3917 1.0000
6.000 0.7790 0.02264 0.01254 -0.0235 0.3488 1.0000
6.250 0.7970 0.02346 0.01330 -0.0219 0.3058 1.0000
6.500 0.8145 0.02442 0.01419 -0.0203 0.2632 1.0000
6.750 0.8313 0.02552 0.01528 -0.0188 0.2228 1.0000
7.000 0.8474 0.02679 0.01643 -0.0173 0.1861 1.0000
7.250 0.8639 0.02821 0.01782 -0.0159 0.1544 1.0000
7.500 0.8793 0.02974 0.01930 -0.0144 0.1262 1.0000
7.750 0.8940 0.03147 0.02093 -0.0129 0.1056 1.0000
8.000 0.9101 0.03327 0.02289 -0.0114 0.0867 1.0000
8.250 0.9248 0.03514 0.02486 -0.0100 0.0725 1.0000
8.500 0.9410 0.03738 0.02724 -0.0085 0.0628 1.0000
8.750 0.9565 0.03968 0.02961 -0.0072 0.0558 1.0000
9.000 0.9701 0.04209 0.03251 -0.0057 0.0483 1.0000
9.250 0.9815 0.04450 0.03494 -0.0045 0.0438 1.0000
9.500 0.9932 0.04801 0.03894 -0.0029 0.0415 1.0000
9.750 0.9982 0.05176 0.04321 -0.0011 0.0397 1.0000
10.000 0.9977 0.05536 0.04722 0.0007 0.0382 1.0000
10.250 0.9926 0.05863 0.05078 0.0026 0.0367 1.0000
10.500 0.9834 0.06186 0.05426 0.0044 0.0357 1.0000
10.750 0.9722 0.06532 0.05792 0.0054 0.0349 1.0000
11.000 0.9606 0.06896 0.06169 0.0055 0.0340 1.0000
11.250 0.9383 0.07457 0.06758 0.0038 0.0346 1.0000
11.500 0.9028 0.08354 0.07685 -0.0015 0.0371 1.0000
11.750 0.8769 0.09247 0.08589 -0.0077 0.0388 1.0000
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Polar data table (+)
Polar graphs
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