RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 500,000 Max Cl/Cd: 84.75 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15a213-il-500000-n5.txt Download as CSV file: xf-rg15a213-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7303 0.09533 0.09232 -0.0476 1.0000 0.0092
-15.250 -0.7771 0.08267 0.07948 -0.0546 1.0000 0.0091
-15.000 -0.8128 0.07252 0.06916 -0.0604 1.0000 0.0090
-14.750 -0.8427 0.06358 0.06004 -0.0658 1.0000 0.0089
-14.500 -0.8637 0.05639 0.05269 -0.0703 1.0000 0.0089
-14.250 -0.8777 0.05078 0.04694 -0.0738 1.0000 0.0090
-14.000 -0.8899 0.04605 0.04207 -0.0764 1.0000 0.0090
-13.750 -0.8988 0.04232 0.03822 -0.0778 1.0000 0.0091
-13.500 -0.9049 0.03938 0.03518 -0.0783 1.0000 0.0092
-13.250 -0.9154 0.03640 0.03206 -0.0780 1.0000 0.0093
-13.000 -0.9188 0.03445 0.03002 -0.0770 1.0000 0.0094
-12.750 -0.9255 0.03259 0.02805 -0.0752 1.0000 0.0096
-12.500 -0.9357 0.03100 0.02636 -0.0722 1.0000 0.0096
-12.250 -0.9491 0.02995 0.02522 -0.0676 1.0000 0.0098
-12.000 -0.9570 0.02884 0.02402 -0.0633 1.0000 0.0099
-11.750 -0.9349 0.02740 0.02241 -0.0645 0.9978 0.0102
-11.500 -0.9107 0.02594 0.02079 -0.0660 0.9951 0.0104
-11.250 -0.8850 0.02483 0.01951 -0.0671 0.9928 0.0107
-11.000 -0.8627 0.02350 0.01807 -0.0677 0.9894 0.0109
-10.750 -0.8368 0.02244 0.01694 -0.0688 0.9866 0.0113
-10.500 -0.8081 0.02155 0.01598 -0.0701 0.9844 0.0116
-10.250 -0.7798 0.02075 0.01511 -0.0711 0.9822 0.0121
-10.000 -0.7562 0.02005 0.01432 -0.0711 0.9777 0.0125
-9.750 -0.7284 0.01928 0.01346 -0.0718 0.9746 0.0130
-9.500 -0.6979 0.01866 0.01274 -0.0729 0.9724 0.0136
-9.250 -0.6707 0.01791 0.01191 -0.0734 0.9691 0.0140
-9.000 -0.6479 0.01704 0.01100 -0.0732 0.9637 0.0145
-8.750 -0.6187 0.01637 0.01027 -0.0740 0.9606 0.0150
-8.500 -0.5875 0.01575 0.00960 -0.0751 0.9584 0.0156
-8.250 -0.5633 0.01522 0.00902 -0.0747 0.9525 0.0163
-8.000 -0.5345 0.01472 0.00846 -0.0752 0.9483 0.0169
-7.750 -0.5028 0.01416 0.00783 -0.0763 0.9454 0.0177
-7.500 -0.4727 0.01356 0.00719 -0.0771 0.9413 0.0186
-7.250 -0.4438 0.01309 0.00668 -0.0775 0.9354 0.0194
-7.000 -0.4102 0.01264 0.00619 -0.0789 0.9315 0.0205
-6.750 -0.3777 0.01225 0.00574 -0.0800 0.9266 0.0217
-6.500 -0.3472 0.01182 0.00529 -0.0807 0.9196 0.0236
-6.000 -0.2837 0.01105 0.00452 -0.0826 0.9052 0.0327
-5.750 -0.2519 0.01068 0.00418 -0.0836 0.8973 0.0461
-5.500 -0.2232 0.01039 0.00391 -0.0838 0.8870 0.0574
-5.000 -0.1653 0.00993 0.00343 -0.0844 0.8662 0.0789
-4.750 -0.1378 0.00973 0.00323 -0.0843 0.8544 0.0893
-4.500 -0.1106 0.00954 0.00303 -0.0842 0.8425 0.1004
-4.250 -0.0837 0.00935 0.00285 -0.0840 0.8305 0.1165
-4.000 -0.0569 0.00917 0.00268 -0.0838 0.8182 0.1360
-3.750 -0.0305 0.00900 0.00253 -0.0835 0.8055 0.1563
-3.500 -0.0042 0.00884 0.00239 -0.0832 0.7926 0.1806
-3.250 0.0218 0.00865 0.00227 -0.0829 0.7796 0.2121
-3.000 0.0478 0.00847 0.00215 -0.0825 0.7668 0.2461
-2.750 0.0738 0.00831 0.00204 -0.0822 0.7538 0.2781
-2.500 0.0997 0.00816 0.00195 -0.0818 0.7406 0.3148
-2.250 0.1254 0.00796 0.00186 -0.0815 0.7271 0.3637
-2.000 0.1511 0.00777 0.00178 -0.0811 0.7137 0.4144
-1.750 0.1770 0.00764 0.00172 -0.0807 0.7001 0.4556
-1.500 0.2027 0.00750 0.00168 -0.0803 0.6867 0.5049
-1.250 0.2281 0.00736 0.00170 -0.0798 0.6732 0.5683
-1.000 0.2542 0.00735 0.00173 -0.0793 0.6597 0.6078
-0.750 0.2805 0.00739 0.00176 -0.0788 0.6459 0.6333
-0.250 0.3336 0.00751 0.00181 -0.0781 0.6179 0.6638
0.000 0.3603 0.00759 0.00184 -0.0778 0.6038 0.6751
0.250 0.3867 0.00767 0.00188 -0.0773 0.5892 0.6869
0.500 0.4131 0.00775 0.00193 -0.0769 0.5749 0.6979
0.750 0.4394 0.00785 0.00198 -0.0765 0.5599 0.7079
1.000 0.4656 0.00795 0.00204 -0.0761 0.5453 0.7168
1.250 0.4917 0.00806 0.00210 -0.0757 0.5300 0.7255
1.500 0.5177 0.00817 0.00217 -0.0753 0.5149 0.7345
1.750 0.5437 0.00829 0.00225 -0.0748 0.5000 0.7425
2.000 0.5695 0.00842 0.00234 -0.0744 0.4846 0.7509
2.250 0.5952 0.00855 0.00244 -0.0739 0.4697 0.7590
2.500 0.6208 0.00869 0.00254 -0.0734 0.4539 0.7674
2.750 0.6463 0.00883 0.00265 -0.0729 0.4391 0.7751
3.000 0.6717 0.00898 0.00277 -0.0724 0.4242 0.7829
3.250 0.6971 0.00914 0.00289 -0.0719 0.4087 0.7891
3.500 0.7222 0.00931 0.00302 -0.0714 0.3941 0.7953
3.750 0.7474 0.00949 0.00316 -0.0709 0.3791 0.8021
4.000 0.7721 0.00966 0.00331 -0.0703 0.3644 0.8084
4.500 0.8214 0.01004 0.00365 -0.0691 0.3354 0.8230
4.750 0.8454 0.01025 0.00383 -0.0684 0.3199 0.8318
5.000 0.8687 0.01049 0.00402 -0.0675 0.3028 0.8407
5.250 0.8918 0.01074 0.00424 -0.0667 0.2841 0.8506
5.500 0.9146 0.01097 0.00445 -0.0657 0.2693 0.8617
5.750 0.9368 0.01119 0.00467 -0.0647 0.2566 0.8749
6.000 0.9583 0.01140 0.00491 -0.0634 0.2444 0.8914
6.250 0.9789 0.01158 0.00513 -0.0620 0.2328 0.9134
6.500 1.0018 0.01182 0.00537 -0.0611 0.2190 0.9482
6.750 1.0303 0.01220 0.00568 -0.0616 0.2007 1.0000
7.000 1.0526 0.01256 0.00598 -0.0608 0.1865 1.0000
7.250 1.0747 0.01292 0.00629 -0.0600 0.1738 1.0000
7.500 1.0958 0.01333 0.00663 -0.0590 0.1592 1.0000
7.750 1.1166 0.01374 0.00700 -0.0579 0.1462 1.0000
8.000 1.1370 0.01415 0.00736 -0.0568 0.1351 1.0000
8.250 1.1559 0.01458 0.00775 -0.0554 0.1241 1.0000
8.500 1.1741 0.01502 0.00815 -0.0539 0.1143 1.0000
8.750 1.1924 0.01543 0.00856 -0.0524 0.1055 1.0000
9.000 1.2095 0.01591 0.00901 -0.0507 0.0970 1.0000
9.250 1.2263 0.01641 0.00948 -0.0491 0.0890 1.0000
9.500 1.2435 0.01688 0.00996 -0.0475 0.0829 1.0000
9.750 1.2591 0.01744 0.01050 -0.0457 0.0763 1.0000
10.000 1.2757 0.01793 0.01102 -0.0441 0.0714 1.0000
10.250 1.2905 0.01854 0.01162 -0.0424 0.0658 1.0000
10.500 1.3056 0.01912 0.01223 -0.0407 0.0612 1.0000
10.750 1.3191 0.01979 0.01290 -0.0388 0.0560 1.0000
11.000 1.3326 0.02048 0.01362 -0.0370 0.0514 1.0000
11.250 1.3446 0.02126 0.01441 -0.0351 0.0463 1.0000
11.500 1.3564 0.02207 0.01524 -0.0333 0.0421 1.0000
11.750 1.3667 0.02299 0.01617 -0.0314 0.0383 1.0000
12.000 1.3769 0.02394 0.01715 -0.0296 0.0353 1.0000
12.250 1.3866 0.02495 0.01821 -0.0279 0.0330 1.0000
12.500 1.3940 0.02616 0.01945 -0.0261 0.0306 1.0000
12.750 1.4032 0.02728 0.02064 -0.0245 0.0293 1.0000
13.000 1.4116 0.02851 0.02193 -0.0231 0.0280 1.0000
13.250 1.4185 0.02989 0.02337 -0.0217 0.0269 1.0000
13.500 1.4239 0.03146 0.02500 -0.0203 0.0257 1.0000
13.750 1.4277 0.03323 0.02684 -0.0191 0.0247 1.0000
14.000 1.4340 0.03485 0.02854 -0.0181 0.0240 1.0000
14.250 1.4392 0.03664 0.03043 -0.0172 0.0234 1.0000
14.500 1.4435 0.03860 0.03249 -0.0165 0.0229 1.0000
14.750 1.4466 0.04073 0.03471 -0.0160 0.0221 1.0000
15.000 1.4483 0.04310 0.03716 -0.0156 0.0214 1.0000
15.250 1.4483 0.04576 0.03990 -0.0154 0.0208 1.0000
15.500 1.4464 0.04875 0.04298 -0.0154 0.0200 1.0000
15.750 1.4434 0.05200 0.04633 -0.0157 0.0197 1.0000
16.000 1.4444 0.05488 0.04932 -0.0161 0.0192 1.0000
16.250 1.4437 0.05809 0.05264 -0.0167 0.0189 1.0000
16.500 1.4433 0.06134 0.05600 -0.0174 0.0181 1.0000
16.750 1.4403 0.06505 0.05982 -0.0184 0.0176 1.0000
17.000 1.4352 0.06918 0.06407 -0.0197 0.0175 1.0000
17.250 1.4294 0.07355 0.06856 -0.0212 0.0171 1.0000
17.500 1.4223 0.07820 0.07332 -0.0230 0.0165 1.0000
17.750 1.4139 0.08321 0.07843 -0.0250 0.0162 1.0000
18.000 1.4037 0.08864 0.08397 -0.0273 0.0160 1.0000
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Polar data table (+)
Polar graphs
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