RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 100,000 Max Cl/Cd: 48.5 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1495-il-100000.txt Download as CSV file: xf-rg1495-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4909 0.09736 0.09226 -0.0202 1.0000 0.1231
-9.000 -0.5100 0.09380 0.08882 -0.0249 1.0000 0.1278
-8.750 -0.5502 0.08986 0.08505 -0.0320 1.0000 0.1288
-8.500 -0.4984 0.08683 0.08191 -0.0234 1.0000 0.1384
-8.250 -0.5235 0.08296 0.07818 -0.0275 1.0000 0.1417
-8.000 -0.5645 0.07881 0.07403 -0.0333 1.0000 0.1431
-7.750 -0.5243 0.07597 0.07128 -0.0264 1.0000 0.1507
-7.500 -0.5664 0.07211 0.06728 -0.0323 1.0000 0.1576
-7.250 -0.5417 0.06828 0.06363 -0.0283 1.0000 0.1622
-7.000 -0.5611 0.06472 0.05991 -0.0302 1.0000 0.1734
-6.750 -0.5447 0.06144 0.05674 -0.0275 1.0000 0.1770
-6.500 -0.5682 0.04288 0.03672 -0.0321 1.0000 0.0820
-6.250 -0.5628 0.03716 0.02996 -0.0293 1.0000 0.0724
-6.000 -0.5493 0.03377 0.02622 -0.0275 1.0000 0.0716
-5.750 -0.5335 0.03151 0.02338 -0.0255 1.0000 0.0730
-5.500 -0.5168 0.02859 0.02011 -0.0239 1.0000 0.0748
-5.250 -0.4971 0.02635 0.01763 -0.0225 1.0000 0.0761
-5.000 -0.4764 0.02461 0.01570 -0.0211 1.0000 0.0784
-4.750 -0.4552 0.02329 0.01419 -0.0198 1.0000 0.0830
-4.500 -0.4333 0.02189 0.01256 -0.0184 1.0000 0.0883
-4.250 -0.4117 0.02059 0.01129 -0.0172 1.0000 0.0944
-4.000 -0.3900 0.01941 0.01006 -0.0159 1.0000 0.1037
-3.750 -0.3694 0.01845 0.00921 -0.0147 1.0000 0.1198
-3.500 -0.3491 0.01736 0.00830 -0.0133 1.0000 0.1475
-3.250 -0.3296 0.01636 0.00761 -0.0121 1.0000 0.2022
-3.000 -0.3116 0.01517 0.00715 -0.0108 1.0000 0.3068
-2.750 -0.2976 0.01383 0.00698 -0.0084 1.0000 0.5156
-2.500 -0.2897 0.01325 0.00746 -0.0028 1.0000 0.7561
-2.250 -0.2767 0.01344 0.00779 0.0019 1.0000 0.8801
-2.000 -0.1719 0.01411 0.00808 -0.0104 1.0000 0.9788
-1.750 -0.1019 0.01421 0.00784 -0.0190 1.0000 1.0000
-1.500 -0.1068 0.01415 0.00772 -0.0146 1.0000 1.0000
-1.250 -0.1082 0.01416 0.00763 -0.0107 1.0000 1.0000
-1.000 -0.1050 0.01424 0.00761 -0.0077 1.0000 1.0000
-0.750 -0.0763 0.01455 0.00779 -0.0091 0.9955 1.0000
-0.500 -0.0227 0.01499 0.00807 -0.0150 0.9849 1.0000
-0.250 0.0290 0.01531 0.00828 -0.0203 0.9734 1.0000
0.000 0.0791 0.01553 0.00841 -0.0252 0.9612 1.0000
0.250 0.1286 0.01567 0.00849 -0.0298 0.9488 1.0000
0.500 0.1789 0.01573 0.00852 -0.0343 0.9366 1.0000
0.750 0.2332 0.01569 0.00847 -0.0395 0.9256 1.0000
1.000 0.2900 0.01552 0.00832 -0.0449 0.9148 1.0000
1.250 0.3405 0.01528 0.00812 -0.0489 0.9015 1.0000
1.500 0.3879 0.01497 0.00786 -0.0522 0.8872 1.0000
1.750 0.4318 0.01464 0.00759 -0.0546 0.8716 1.0000
2.000 0.4691 0.01434 0.00731 -0.0555 0.8527 1.0000
2.250 0.4992 0.01409 0.00707 -0.0549 0.8295 1.0000
2.500 0.5261 0.01388 0.00687 -0.0537 0.8044 1.0000
2.750 0.5517 0.01374 0.00669 -0.0522 0.7789 1.0000
3.000 0.5746 0.01372 0.00663 -0.0504 0.7529 1.0000
3.250 0.5960 0.01379 0.00667 -0.0485 0.7264 1.0000
3.500 0.6176 0.01389 0.00675 -0.0467 0.6995 1.0000
3.750 0.6389 0.01403 0.00683 -0.0448 0.6714 1.0000
4.000 0.6595 0.01419 0.00693 -0.0428 0.6412 1.0000
4.250 0.6796 0.01438 0.00703 -0.0407 0.6088 1.0000
4.500 0.6997 0.01461 0.00717 -0.0387 0.5753 1.0000
4.750 0.7187 0.01488 0.00738 -0.0366 0.5382 1.0000
5.000 0.7377 0.01521 0.00758 -0.0345 0.4995 1.0000
5.250 0.7557 0.01561 0.00784 -0.0323 0.4555 1.0000
5.500 0.7728 0.01612 0.00820 -0.0301 0.4056 1.0000
5.750 0.7888 0.01681 0.00862 -0.0279 0.3518 1.0000
6.000 0.8049 0.01767 0.00920 -0.0257 0.3004 1.0000
6.250 0.8217 0.01863 0.00990 -0.0239 0.2580 1.0000
6.500 0.8393 0.01968 0.01070 -0.0222 0.2250 1.0000
6.750 0.8579 0.02075 0.01163 -0.0208 0.1972 1.0000
7.000 0.8777 0.02192 0.01272 -0.0195 0.1748 1.0000
7.250 0.8979 0.02316 0.01385 -0.0184 0.1562 1.0000
7.500 0.9194 0.02457 0.01517 -0.0175 0.1407 1.0000
7.750 0.9406 0.02592 0.01654 -0.0165 0.1267 1.0000
8.000 0.9621 0.02740 0.01819 -0.0155 0.1154 1.0000
8.250 0.9829 0.02894 0.01983 -0.0145 0.1050 1.0000
8.500 1.0051 0.03082 0.02167 -0.0138 0.0966 1.0000
8.750 1.0231 0.03220 0.02334 -0.0123 0.0883 1.0000
9.000 1.0417 0.03453 0.02585 -0.0112 0.0818 1.0000
9.250 1.0580 0.03608 0.02763 -0.0097 0.0750 1.0000
9.500 1.0722 0.03910 0.03089 -0.0083 0.0704 1.0000
9.750 1.0811 0.04148 0.03376 -0.0059 0.0659 1.0000
10.000 1.0965 0.04341 0.03567 -0.0049 0.0612 1.0000
10.250 1.0999 0.04776 0.04038 -0.0029 0.0594 1.0000
10.500 1.0947 0.05118 0.04436 0.0003 0.0584 1.0000
10.750 1.0839 0.05482 0.04846 0.0035 0.0575 1.0000
11.000 1.0686 0.05847 0.05247 0.0066 0.0570 1.0000
11.250 1.0483 0.06205 0.05631 0.0096 0.0570 1.0000
11.500 1.0252 0.06608 0.06057 0.0113 0.0571 1.0000
11.750 1.0021 0.07075 0.06543 0.0114 0.0576 1.0000
12.000 0.9761 0.07622 0.07107 0.0098 0.0580 1.0000
12.250 0.9528 0.08262 0.07758 0.0069 0.0587 1.0000
12.500 0.9306 0.08984 0.08488 0.0030 0.0594 1.0000
12.750 0.8398 0.11674 0.11183 -0.0168 0.0711 1.0000
13.000 0.8387 0.12272 0.11781 -0.0182 0.0719 1.0000
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Polar data table (+)
Polar graphs
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