RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.06 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a213-il-1000000-n5.txt Download as CSV file: xf-rg15a213-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 15A 2.5/13.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.9039 0.08749 0.08473 -0.0536 1.0000 0.0064
-16.750 -0.9633 0.07389 0.07094 -0.0612 1.0000 0.0063
-16.500 -1.0104 0.06228 0.05913 -0.0680 1.0000 0.0062
-16.250 -1.0420 0.05330 0.04997 -0.0737 1.0000 0.0062
-16.000 -1.0636 0.04659 0.04309 -0.0779 1.0000 0.0061
-15.750 -1.0779 0.04171 0.03807 -0.0805 1.0000 0.0061
-15.500 -1.0894 0.03783 0.03406 -0.0818 1.0000 0.0062
-15.250 -1.0964 0.03486 0.03101 -0.0822 1.0000 0.0063
-15.000 -1.1020 0.03237 0.02841 -0.0818 1.0000 0.0063
-14.750 -1.1068 0.03024 0.02619 -0.0808 1.0000 0.0064
-14.500 -1.1089 0.02861 0.02449 -0.0793 1.0000 0.0065
-14.250 -1.1132 0.02718 0.02298 -0.0769 1.0000 0.0066
-14.000 -1.1213 0.02604 0.02176 -0.0733 1.0000 0.0066
-13.750 -1.1263 0.02519 0.02085 -0.0694 0.9997 0.0067
-13.500 -1.1027 0.02417 0.01976 -0.0704 0.9982 0.0069
-13.250 -1.0779 0.02317 0.01869 -0.0715 0.9964 0.0071
-13.000 -1.0520 0.02225 0.01769 -0.0726 0.9949 0.0073
-12.750 -1.0253 0.02143 0.01680 -0.0737 0.9936 0.0075
-12.500 -1.0033 0.02062 0.01590 -0.0737 0.9913 0.0077
-12.250 -0.9781 0.01992 0.01514 -0.0742 0.9892 0.0079
-12.000 -0.9512 0.01924 0.01438 -0.0749 0.9873 0.0081
-11.750 -0.9234 0.01852 0.01360 -0.0758 0.9856 0.0083
-11.500 -0.8946 0.01779 0.01283 -0.0769 0.9843 0.0086
-11.250 -0.8640 0.01724 0.01224 -0.0781 0.9833 0.0090
-11.000 -0.8426 0.01671 0.01166 -0.0774 0.9792 0.0092
-10.750 -0.8156 0.01623 0.01115 -0.0777 0.9763 0.0096
-10.500 -0.7868 0.01571 0.01059 -0.0784 0.9741 0.0099
-10.250 -0.7566 0.01522 0.01005 -0.0793 0.9724 0.0102
-10.000 -0.7255 0.01475 0.00952 -0.0804 0.9711 0.0105
-9.750 -0.7047 0.01435 0.00908 -0.0792 0.9650 0.0107
-9.500 -0.6773 0.01380 0.00849 -0.0796 0.9615 0.0111
-9.250 -0.6469 0.01330 0.00796 -0.0805 0.9591 0.0115
-9.000 -0.6170 0.01291 0.00754 -0.0812 0.9556 0.0120
-8.750 -0.5889 0.01255 0.00715 -0.0815 0.9503 0.0125
-8.500 -0.5561 0.01217 0.00674 -0.0827 0.9465 0.0130
-8.250 -0.5226 0.01179 0.00632 -0.0841 0.9427 0.0134
-8.000 -0.4918 0.01147 0.00595 -0.0849 0.9357 0.0137
-7.750 -0.4585 0.01103 0.00546 -0.0863 0.9295 0.0144
-7.500 -0.4290 0.01067 0.00506 -0.0868 0.9201 0.0151
-7.250 -0.3989 0.01038 0.00473 -0.0874 0.9107 0.0158
-7.000 -0.3704 0.01013 0.00441 -0.0876 0.8995 0.0164
-6.750 -0.3432 0.00991 0.00414 -0.0875 0.8878 0.0170
-6.500 -0.3162 0.00973 0.00389 -0.0873 0.8760 0.0174
-6.250 -0.2901 0.00949 0.00359 -0.0870 0.8637 0.0188
-6.000 -0.2640 0.00931 0.00335 -0.0866 0.8510 0.0201
-5.750 -0.2379 0.00915 0.00314 -0.0862 0.8380 0.0214
-5.500 -0.2122 0.00895 0.00292 -0.0858 0.8251 0.0258
-5.250 -0.1869 0.00871 0.00270 -0.0853 0.8122 0.0398
-5.000 -0.1612 0.00853 0.00253 -0.0849 0.7992 0.0503
-4.750 -0.1353 0.00839 0.00237 -0.0845 0.7860 0.0595
-4.500 -0.1094 0.00826 0.00223 -0.0841 0.7727 0.0704
-4.250 -0.0831 0.00815 0.00211 -0.0838 0.7592 0.0805
-4.000 -0.0568 0.00804 0.00199 -0.0834 0.7462 0.0906
-3.750 -0.0304 0.00795 0.00188 -0.0831 0.7330 0.1003
-3.500 -0.0041 0.00785 0.00177 -0.0828 0.7199 0.1143
-3.250 0.0220 0.00772 0.00168 -0.0825 0.7065 0.1367
-3.000 0.0481 0.00760 0.00159 -0.0821 0.6930 0.1605
-2.500 0.1011 0.00742 0.00145 -0.0816 0.6661 0.2034
-2.250 0.1275 0.00730 0.00138 -0.0813 0.6526 0.2359
-2.000 0.1538 0.00716 0.00133 -0.0811 0.6396 0.2748
-1.750 0.1802 0.00705 0.00128 -0.0808 0.6261 0.3111
-1.500 0.2065 0.00693 0.00124 -0.0806 0.6126 0.3558
-1.250 0.2331 0.00686 0.00122 -0.0803 0.5988 0.3886
-1.000 0.2596 0.00676 0.00119 -0.0801 0.5850 0.4315
-0.750 0.2862 0.00666 0.00118 -0.0799 0.5710 0.4762
-0.500 0.3127 0.00657 0.00118 -0.0797 0.5569 0.5231
-0.250 0.3390 0.00650 0.00122 -0.0794 0.5424 0.5798
0.000 0.3658 0.00652 0.00126 -0.0791 0.5281 0.6123
0.250 0.3928 0.00658 0.00131 -0.0789 0.5137 0.6297
0.500 0.4198 0.00667 0.00135 -0.0787 0.4991 0.6412
0.750 0.4467 0.00676 0.00140 -0.0784 0.4845 0.6529
1.000 0.4736 0.00685 0.00147 -0.0782 0.4702 0.6655
1.250 0.5004 0.00696 0.00153 -0.0779 0.4551 0.6762
1.500 0.5272 0.00706 0.00160 -0.0777 0.4408 0.6851
1.750 0.5539 0.00719 0.00167 -0.0774 0.4258 0.6927
2.000 0.5804 0.00731 0.00176 -0.0771 0.4113 0.7014
2.500 0.6334 0.00757 0.00194 -0.0766 0.3819 0.7169
2.750 0.6599 0.00771 0.00204 -0.0763 0.3675 0.7243
3.000 0.6862 0.00784 0.00215 -0.0760 0.3541 0.7324
3.250 0.7124 0.00799 0.00226 -0.0756 0.3400 0.7403
3.500 0.7384 0.00814 0.00239 -0.0753 0.3269 0.7484
4.000 0.7901 0.00847 0.00265 -0.0745 0.2996 0.7602
4.250 0.8151 0.00870 0.00281 -0.0740 0.2809 0.7660
4.500 0.8398 0.00895 0.00298 -0.0735 0.2611 0.7716
4.750 0.8650 0.00914 0.00314 -0.0730 0.2480 0.7773
5.000 0.8904 0.00933 0.00331 -0.0726 0.2369 0.7836
5.250 0.9153 0.00953 0.00348 -0.0721 0.2256 0.7901
5.750 0.9635 0.01003 0.00390 -0.0708 0.1960 0.8051
6.000 0.9871 0.01029 0.00413 -0.0701 0.1815 0.8134
6.250 1.0105 0.01056 0.00436 -0.0693 0.1681 0.8219
6.500 1.0337 0.01083 0.00460 -0.0686 0.1560 0.8320
6.750 1.0568 0.01106 0.00485 -0.0677 0.1460 0.8435
7.000 1.0789 0.01134 0.00512 -0.0668 0.1343 0.8568
7.250 1.1003 0.01162 0.00540 -0.0656 0.1235 0.8723
7.500 1.1204 0.01192 0.00569 -0.0642 0.1125 0.8921
7.750 1.1382 0.01216 0.00598 -0.0623 0.1026 0.9243
8.000 1.1639 0.01245 0.00629 -0.0622 0.0926 1.0000
8.250 1.1854 0.01280 0.00661 -0.0612 0.0854 1.0000
8.500 1.2062 0.01317 0.00695 -0.0601 0.0782 1.0000
8.750 1.2267 0.01351 0.00728 -0.0589 0.0726 1.0000
9.000 1.2452 0.01389 0.00763 -0.0574 0.0669 1.0000
9.250 1.2639 0.01425 0.00798 -0.0559 0.0624 1.0000
9.500 1.2817 0.01464 0.00837 -0.0543 0.0578 1.0000
9.750 1.2988 0.01507 0.00879 -0.0526 0.0529 1.0000
10.000 1.3150 0.01554 0.00924 -0.0508 0.0470 1.0000
10.250 1.3309 0.01603 0.00972 -0.0490 0.0417 1.0000
10.500 1.3447 0.01663 0.01028 -0.0469 0.0353 1.0000
11.000 1.3728 0.01780 0.01145 -0.0430 0.0280 1.0000
11.250 1.3866 0.01841 0.01206 -0.0411 0.0260 1.0000
11.500 1.4004 0.01903 0.01271 -0.0393 0.0245 1.0000
11.750 1.4148 0.01961 0.01333 -0.0376 0.0238 1.0000
12.000 1.4284 0.02025 0.01402 -0.0359 0.0230 1.0000
12.250 1.4410 0.02097 0.01477 -0.0341 0.0221 1.0000
12.500 1.4519 0.02179 0.01563 -0.0322 0.0210 1.0000
12.750 1.4625 0.02267 0.01654 -0.0304 0.0202 1.0000
13.000 1.4737 0.02354 0.01746 -0.0288 0.0193 1.0000
13.250 1.4850 0.02442 0.01840 -0.0273 0.0189 1.0000
13.500 1.4955 0.02539 0.01943 -0.0258 0.0184 1.0000
13.750 1.5050 0.02647 0.02056 -0.0243 0.0178 1.0000
14.000 1.5134 0.02766 0.02180 -0.0229 0.0172 1.0000
14.250 1.5206 0.02900 0.02318 -0.0215 0.0165 1.0000
14.500 1.5266 0.03048 0.02472 -0.0202 0.0158 1.0000
14.750 1.5338 0.03194 0.02624 -0.0191 0.0154 1.0000
15.000 1.5407 0.03346 0.02784 -0.0182 0.0151 1.0000
15.250 1.5466 0.03513 0.02958 -0.0173 0.0146 1.0000
15.500 1.5515 0.03698 0.03149 -0.0166 0.0139 1.0000
15.750 1.5553 0.03899 0.03357 -0.0160 0.0135 1.0000
16.000 1.5572 0.04127 0.03591 -0.0155 0.0129 1.0000
16.250 1.5586 0.04371 0.03842 -0.0152 0.0124 1.0000
16.500 1.5607 0.04617 0.04096 -0.0151 0.0117 1.0000
16.750 1.5607 0.04895 0.04382 -0.0152 0.0109 1.0000
17.000 1.5601 0.05190 0.04685 -0.0155 0.0106 1.0000
17.250 1.5563 0.05537 0.05039 -0.0160 0.0096 1.0000
17.500 1.5529 0.05892 0.05403 -0.0167 0.0089 1.0000
17.750 1.5469 0.06292 0.05810 -0.0177 0.0079 1.0000
18.000 1.5387 0.06739 0.06265 -0.0191 0.0072 1.0000
18.250 1.5293 0.07217 0.06753 -0.0207 0.0064 1.0000
18.500 1.5177 0.07746 0.07293 -0.0227 0.0058 1.0000
18.750 1.5056 0.08297 0.07854 -0.0250 0.0053 1.0000
19.000 1.4918 0.08895 0.08463 -0.0276 0.0049 1.0000
19.250 1.4793 0.09485 0.09065 -0.0303 0.0047 1.0000
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