RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 50,000 Max Cl/Cd: 33.86 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1495-il-50000-n5.txt Download as CSV file: xf-rg1495-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9.5% 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5285 0.09357 0.08630 -0.0296 1.0000 0.0525
-9.500 -0.5343 0.08821 0.08100 -0.0326 1.0000 0.0525
-9.250 -0.5410 0.08269 0.07555 -0.0361 1.0000 0.0522
-9.000 -0.5537 0.07726 0.07017 -0.0392 1.0000 0.0520
-8.750 -0.5684 0.07275 0.06566 -0.0403 1.0000 0.0518
-8.500 -0.5808 0.06820 0.06106 -0.0410 1.0000 0.0517
-8.250 -0.5922 0.06367 0.05638 -0.0411 1.0000 0.0518
-8.000 -0.6008 0.05925 0.05171 -0.0406 1.0000 0.0523
-7.750 -0.6054 0.05500 0.04712 -0.0396 1.0000 0.0528
-7.500 -0.6058 0.05096 0.04264 -0.0382 1.0000 0.0533
-7.250 -0.6001 0.04734 0.03875 -0.0368 1.0000 0.0539
-7.000 -0.5907 0.04419 0.03533 -0.0353 1.0000 0.0547
-6.750 -0.5789 0.04136 0.03222 -0.0338 1.0000 0.0558
-6.500 -0.5649 0.03897 0.02957 -0.0324 1.0000 0.0578
-6.250 -0.5496 0.03677 0.02703 -0.0309 1.0000 0.0613
-6.000 -0.5327 0.03437 0.02406 -0.0294 1.0000 0.0645
-5.750 -0.5135 0.03208 0.02138 -0.0280 1.0000 0.0666
-5.500 -0.4940 0.03031 0.01951 -0.0267 1.0000 0.0693
-5.250 -0.4734 0.02875 0.01777 -0.0254 1.0000 0.0734
-5.000 -0.4522 0.02739 0.01614 -0.0240 1.0000 0.0801
-4.750 -0.4320 0.02621 0.01497 -0.0228 1.0000 0.0877
-4.500 -0.4106 0.02497 0.01359 -0.0213 1.0000 0.0957
-4.250 -0.3901 0.02397 0.01256 -0.0200 1.0000 0.1100
-4.000 -0.3697 0.02301 0.01163 -0.0188 1.0000 0.1304
-3.750 -0.3489 0.02206 0.01078 -0.0178 1.0000 0.1628
-3.500 -0.3297 0.02109 0.01008 -0.0167 1.0000 0.2097
-3.250 -0.3116 0.02011 0.00950 -0.0154 1.0000 0.2796
-3.000 -0.2951 0.01913 0.00904 -0.0138 1.0000 0.3835
-2.750 -0.2812 0.01820 0.00887 -0.0110 1.0000 0.5271
-2.500 -0.2685 0.01773 0.00921 -0.0062 1.0000 0.7067
-2.250 -0.2461 0.01783 0.00940 -0.0034 1.0000 0.8481
-2.000 -0.1808 0.01808 0.00934 -0.0091 1.0000 0.9476
-1.750 -0.0973 0.01815 0.00895 -0.0199 1.0000 1.0000
-1.500 -0.0942 0.01810 0.00875 -0.0166 1.0000 1.0000
-1.250 -0.0893 0.01812 0.00862 -0.0135 1.0000 1.0000
-1.000 -0.0751 0.01822 0.00856 -0.0122 0.9978 1.0000
-0.750 -0.0312 0.01849 0.00863 -0.0162 0.9857 1.0000
-0.500 0.0109 0.01872 0.00867 -0.0198 0.9731 1.0000
-0.250 0.0518 0.01891 0.00873 -0.0230 0.9599 1.0000
0.000 0.0919 0.01907 0.00878 -0.0259 0.9464 1.0000
0.250 0.1316 0.01921 0.00883 -0.0286 0.9326 1.0000
0.500 0.1713 0.01931 0.00887 -0.0313 0.9185 1.0000
0.750 0.2112 0.01938 0.00891 -0.0338 0.9043 1.0000
1.000 0.2514 0.01940 0.00892 -0.0362 0.8899 1.0000
1.250 0.2897 0.01940 0.00894 -0.0381 0.8747 1.0000
1.500 0.3263 0.01938 0.00894 -0.0396 0.8588 1.0000
1.750 0.3619 0.01936 0.00894 -0.0407 0.8425 1.0000
2.000 0.3951 0.01933 0.00896 -0.0413 0.8251 1.0000
2.250 0.4234 0.01937 0.00904 -0.0410 0.8052 1.0000
2.500 0.4539 0.01937 0.00908 -0.0410 0.7859 1.0000
2.750 0.4835 0.01937 0.00914 -0.0407 0.7659 1.0000
3.000 0.5096 0.01945 0.00926 -0.0398 0.7437 1.0000
3.250 0.5371 0.01949 0.00933 -0.0390 0.7208 1.0000
3.500 0.5634 0.01951 0.00937 -0.0378 0.6941 1.0000
3.750 0.5870 0.01958 0.00943 -0.0362 0.6634 1.0000
4.000 0.6097 0.01971 0.00954 -0.0345 0.6314 1.0000
4.250 0.6325 0.01991 0.00973 -0.0330 0.6007 1.0000
4.500 0.6552 0.02018 0.01003 -0.0315 0.5712 1.0000
4.750 0.6770 0.02049 0.01033 -0.0299 0.5395 1.0000
5.000 0.6982 0.02084 0.01064 -0.0283 0.5059 1.0000
5.250 0.7178 0.02126 0.01101 -0.0264 0.4678 1.0000
5.500 0.7365 0.02175 0.01141 -0.0245 0.4274 1.0000
5.750 0.7544 0.02234 0.01192 -0.0226 0.3850 1.0000
6.000 0.7716 0.02304 0.01249 -0.0208 0.3424 1.0000
6.250 0.7884 0.02388 0.01318 -0.0190 0.3017 1.0000
6.500 0.8055 0.02481 0.01400 -0.0174 0.2649 1.0000
6.750 0.8227 0.02584 0.01492 -0.0159 0.2340 1.0000
7.000 0.8403 0.02695 0.01600 -0.0146 0.2079 1.0000
7.250 0.8575 0.02813 0.01707 -0.0132 0.1863 1.0000
7.500 0.8762 0.02938 0.01836 -0.0120 0.1678 1.0000
7.750 0.8943 0.03069 0.01968 -0.0109 0.1512 1.0000
8.000 0.9137 0.03213 0.02118 -0.0098 0.1378 1.0000
8.250 0.9324 0.03358 0.02272 -0.0087 0.1255 1.0000
8.500 0.9509 0.03508 0.02429 -0.0077 0.1154 1.0000
8.750 0.9695 0.03666 0.02611 -0.0066 0.1059 1.0000
9.000 0.9864 0.03838 0.02804 -0.0054 0.0973 1.0000
9.250 1.0043 0.04012 0.02982 -0.0044 0.0911 1.0000
9.500 1.0188 0.04239 0.03249 -0.0031 0.0845 1.0000
9.750 1.0320 0.04408 0.03423 -0.0018 0.0786 1.0000
10.000 1.0432 0.04694 0.03751 -0.0004 0.0744 1.0000
10.250 1.0489 0.04977 0.04075 0.0015 0.0703 1.0000
10.500 1.0570 0.05169 0.04273 0.0029 0.0661 1.0000
10.750 1.0554 0.05473 0.04607 0.0048 0.0632 1.0000
11.000 1.0440 0.05823 0.04999 0.0074 0.0615 1.0000
11.250 1.0300 0.06191 0.05399 0.0093 0.0602 1.0000
11.500 1.0129 0.06599 0.05834 0.0102 0.0595 1.0000
11.750 0.9919 0.07077 0.06336 0.0099 0.0591 1.0000
12.000 0.9655 0.07687 0.06967 0.0077 0.0594 1.0000
12.250 0.9345 0.08469 0.07765 0.0033 0.0604 1.0000
12.500 0.9031 0.09412 0.08717 -0.0028 0.0616 1.0000
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Polar data table (+)
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