RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 500,000 Max Cl/Cd: 70.82 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg149-il-500000-n5.txt Download as CSV file: xf-rg149-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.8160 0.04410 0.04153 -0.0539 1.0000 0.0063
-11.000 -0.8535 0.03901 0.03616 -0.0509 1.0000 0.0062
-10.750 -0.8722 0.03451 0.03127 -0.0482 1.0000 0.0063
-10.500 -0.8788 0.03095 0.02734 -0.0455 1.0000 0.0064
-10.250 -0.8763 0.02828 0.02434 -0.0431 1.0000 0.0066
-10.000 -0.8688 0.02609 0.02184 -0.0409 1.0000 0.0069
-9.750 -0.8577 0.02431 0.01978 -0.0389 1.0000 0.0071
-9.500 -0.8442 0.02281 0.01803 -0.0371 1.0000 0.0072
-9.250 -0.8302 0.02141 0.01647 -0.0353 1.0000 0.0076
-9.000 -0.8119 0.02067 0.01562 -0.0340 1.0000 0.0079
-8.750 -0.7931 0.01998 0.01483 -0.0327 1.0000 0.0082
-8.500 -0.7730 0.01955 0.01434 -0.0315 1.0000 0.0087
-8.250 -0.7543 0.01877 0.01343 -0.0301 1.0000 0.0092
-8.000 -0.7346 0.01814 0.01268 -0.0288 1.0000 0.0099
-7.750 -0.7054 0.01733 0.01170 -0.0295 0.9985 0.0105
-7.500 -0.6753 0.01630 0.01051 -0.0305 0.9964 0.0112
-7.250 -0.6436 0.01567 0.00983 -0.0317 0.9944 0.0119
-7.000 -0.6132 0.01516 0.00925 -0.0326 0.9921 0.0127
-6.750 -0.5823 0.01466 0.00867 -0.0334 0.9893 0.0138
-6.500 -0.5502 0.01424 0.00816 -0.0345 0.9867 0.0148
-6.250 -0.5175 0.01373 0.00754 -0.0358 0.9844 0.0156
-6.000 -0.4879 0.01288 0.00663 -0.0365 0.9813 0.0168
-5.750 -0.4586 0.01243 0.00616 -0.0369 0.9769 0.0179
-5.500 -0.4267 0.01202 0.00570 -0.0379 0.9735 0.0192
-5.250 -0.3934 0.01160 0.00523 -0.0392 0.9708 0.0203
-5.000 -0.3649 0.01121 0.00477 -0.0394 0.9654 0.0210
-4.750 -0.3342 0.01075 0.00426 -0.0401 0.9606 0.0225
-4.500 -0.3009 0.01034 0.00382 -0.0413 0.9571 0.0246
-4.250 -0.2720 0.01003 0.00349 -0.0415 0.9498 0.0262
-4.000 -0.2388 0.00974 0.00315 -0.0426 0.9443 0.0285
-3.750 -0.2077 0.00944 0.00286 -0.0433 0.9367 0.0340
-3.500 -0.1745 0.00912 0.00259 -0.0444 0.9292 0.0488
-3.250 -0.1441 0.00881 0.00236 -0.0450 0.9189 0.0711
-3.000 -0.1136 0.00853 0.00215 -0.0456 0.9078 0.0959
-2.750 -0.0842 0.00829 0.00197 -0.0459 0.8952 0.1243
-2.500 -0.0561 0.00805 0.00181 -0.0460 0.8808 0.1601
-2.250 -0.0293 0.00777 0.00167 -0.0458 0.8650 0.2112
-2.000 -0.0032 0.00747 0.00153 -0.0455 0.8481 0.2769
-1.750 0.0222 0.00717 0.00143 -0.0450 0.8306 0.3516
-1.500 0.0472 0.00688 0.00134 -0.0445 0.8130 0.4295
-1.250 0.0718 0.00659 0.00126 -0.0439 0.7950 0.5132
-1.000 0.0949 0.00621 0.00121 -0.0429 0.7766 0.6263
-0.750 0.1173 0.00594 0.00124 -0.0415 0.7578 0.7289
-0.500 0.1419 0.00592 0.00128 -0.0405 0.7384 0.7810
-0.250 0.1672 0.00597 0.00130 -0.0397 0.7170 0.8091
0.000 0.1921 0.00605 0.00131 -0.0389 0.6906 0.8300
0.250 0.2168 0.00615 0.00133 -0.0380 0.6625 0.8485
0.500 0.2419 0.00625 0.00136 -0.0372 0.6392 0.8629
0.750 0.2675 0.00634 0.00139 -0.0365 0.6186 0.8751
1.000 0.2925 0.00644 0.00143 -0.0358 0.5965 0.8877
1.250 0.3172 0.00656 0.00148 -0.0349 0.5715 0.9008
1.500 0.3419 0.00668 0.00153 -0.0341 0.5469 0.9125
1.750 0.3669 0.00681 0.00159 -0.0333 0.5239 0.9235
2.000 0.3922 0.00695 0.00166 -0.0326 0.4996 0.9356
2.250 0.4190 0.00710 0.00174 -0.0323 0.4750 0.9477
2.500 0.4473 0.00728 0.00183 -0.0323 0.4471 0.9585
2.750 0.4772 0.00754 0.00194 -0.0329 0.4100 0.9672
3.000 0.5082 0.00780 0.00206 -0.0337 0.3735 0.9736
3.250 0.5389 0.00808 0.00219 -0.0345 0.3376 0.9793
3.500 0.5695 0.00835 0.00234 -0.0353 0.3054 0.9846
3.750 0.6014 0.00863 0.00251 -0.0364 0.2745 0.9891
4.000 0.6318 0.00899 0.00271 -0.0372 0.2360 0.9944
4.250 0.6627 0.00939 0.00293 -0.0382 0.1965 0.9997
4.500 0.6835 0.00974 0.00317 -0.0370 0.1680 1.0000
4.750 0.7051 0.01005 0.00340 -0.0359 0.1492 1.0000
5.000 0.7279 0.01034 0.00364 -0.0350 0.1348 1.0000
5.250 0.7512 0.01064 0.00388 -0.0342 0.1189 1.0000
5.500 0.7747 0.01097 0.00414 -0.0335 0.1029 1.0000
5.750 0.7983 0.01130 0.00443 -0.0328 0.0890 1.0000
6.000 0.8223 0.01162 0.00472 -0.0322 0.0790 1.0000
6.250 0.8463 0.01195 0.00504 -0.0316 0.0705 1.0000
6.500 0.8700 0.01232 0.00539 -0.0309 0.0626 1.0000
6.750 0.8942 0.01264 0.00573 -0.0304 0.0566 1.0000
7.000 0.9176 0.01305 0.00613 -0.0297 0.0490 1.0000
7.250 0.9412 0.01343 0.00651 -0.0291 0.0424 1.0000
7.500 0.9646 0.01384 0.00692 -0.0284 0.0372 1.0000
7.750 0.9878 0.01426 0.00734 -0.0278 0.0324 1.0000
8.000 1.0106 0.01471 0.00781 -0.0270 0.0287 1.0000
8.250 1.0338 0.01512 0.00829 -0.0264 0.0259 1.0000
8.500 1.0558 0.01563 0.00880 -0.0256 0.0226 1.0000
8.750 1.0783 0.01609 0.00931 -0.0248 0.0199 1.0000
9.000 1.0998 0.01664 0.00987 -0.0240 0.0169 1.0000
9.250 1.1213 0.01718 0.01047 -0.0231 0.0144 1.0000
9.500 1.1417 0.01781 0.01113 -0.0221 0.0120 1.0000
9.750 1.1617 0.01847 0.01187 -0.0211 0.0103 1.0000
10.000 1.1811 0.01915 0.01262 -0.0199 0.0091 1.0000
10.250 1.1993 0.01992 0.01344 -0.0187 0.0081 1.0000
10.500 1.2163 0.02077 0.01438 -0.0173 0.0073 1.0000
10.750 1.2338 0.02153 0.01524 -0.0159 0.0069 1.0000
11.000 1.2499 0.02234 0.01616 -0.0145 0.0064 1.0000
11.250 1.2644 0.02325 0.01718 -0.0128 0.0060 1.0000
11.500 1.2768 0.02417 0.01819 -0.0108 0.0057 1.0000
11.750 1.2858 0.02517 0.01933 -0.0084 0.0055 1.0000
12.000 1.2921 0.02634 0.02061 -0.0057 0.0053 1.0000
12.250 1.2934 0.02786 0.02226 -0.0027 0.0050 1.0000
12.500 1.2957 0.02935 0.02389 -0.0001 0.0048 1.0000
12.750 1.2984 0.03087 0.02555 0.0021 0.0048 1.0000
13.000 1.3007 0.03250 0.02733 0.0039 0.0047 1.0000
13.250 1.3010 0.03442 0.02939 0.0055 0.0047 1.0000
13.500 1.2994 0.03667 0.03179 0.0067 0.0045 1.0000
13.750 1.2962 0.03925 0.03452 0.0075 0.0045 1.0000
14.000 1.2915 0.04223 0.03766 0.0077 0.0044 1.0000
14.250 1.2847 0.04575 0.04134 0.0073 0.0044 1.0000
14.500 1.2763 0.04978 0.04553 0.0062 0.0043 1.0000
14.750 1.2651 0.05459 0.05051 0.0044 0.0043 1.0000
15.000 1.2537 0.05984 0.05592 0.0019 0.0042 1.0000
15.250 1.2383 0.06610 0.06236 -0.0015 0.0042 1.0000
15.500 1.2209 0.07314 0.06956 -0.0054 0.0042 1.0000
15.750 1.2008 0.08104 0.07763 -0.0100 0.0043 1.0000
16.000 1.1805 0.08941 0.08615 -0.0148 0.0043 1.0000
16.250 1.1566 0.09881 0.09570 -0.0202 0.0043 1.0000
16.500 1.1313 0.10890 0.10593 -0.0260 0.0044 1.0000
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