RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 15A 2.5/13.0 AIRFOIL (rg15a213-il) Reynolds number: 50,000 Max Cl/Cd: 29.15 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15a213-il-50000.txt Download as CSV file: xf-rg15a213-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3831 0.11742 0.11020 -0.0253 1.0000 0.2755
-9.750 -0.3606 0.11243 0.10517 -0.0241 1.0000 0.2845
-9.500 -0.3844 0.11149 0.10440 -0.0244 1.0000 0.2926
-9.250 -0.3586 0.10649 0.09935 -0.0232 1.0000 0.3008
-9.000 -0.3748 0.10456 0.09756 -0.0229 1.0000 0.3094
-8.750 -0.3627 0.10113 0.09414 -0.0217 1.0000 0.3205
-8.500 -0.3589 0.09783 0.09090 -0.0206 1.0000 0.3301
-8.250 -0.4918 0.08091 0.07444 -0.0402 1.0000 0.1638
-8.000 -0.5774 0.07004 0.06343 -0.0452 1.0000 0.1367
-7.750 -0.5806 0.06610 0.05943 -0.0438 1.0000 0.1352
-7.500 -0.5871 0.06208 0.05531 -0.0425 1.0000 0.1343
-7.250 -0.5917 0.05804 0.05110 -0.0412 1.0000 0.1332
-7.000 -0.5945 0.05387 0.04665 -0.0401 1.0000 0.1325
-6.750 -0.5931 0.04975 0.04215 -0.0391 1.0000 0.1323
-6.500 -0.5869 0.04581 0.03772 -0.0381 1.0000 0.1325
-6.250 -0.5765 0.04221 0.03353 -0.0372 1.0000 0.1346
-6.000 -0.5618 0.03966 0.03083 -0.0361 1.0000 0.1404
-5.750 -0.5452 0.03730 0.02809 -0.0350 1.0000 0.1485
-5.500 -0.5269 0.03502 0.02563 -0.0340 1.0000 0.1580
-5.250 -0.5079 0.03316 0.02360 -0.0330 1.0000 0.1736
-5.000 -0.4883 0.03157 0.02180 -0.0320 1.0000 0.1949
-4.750 -0.4700 0.03043 0.02076 -0.0308 1.0000 0.2216
-4.500 -0.4509 0.02928 0.01963 -0.0297 1.0000 0.2500
-4.250 -0.4306 0.02813 0.01845 -0.0286 1.0000 0.2783
-4.000 -0.4109 0.02712 0.01753 -0.0275 1.0000 0.3099
-3.750 -0.3919 0.02618 0.01680 -0.0261 1.0000 0.3476
-3.500 -0.3733 0.02527 0.01617 -0.0247 1.0000 0.3985
-3.250 -0.3563 0.02442 0.01580 -0.0226 1.0000 0.4701
-3.000 -0.3445 0.02409 0.01615 -0.0189 1.0000 0.5608
-2.750 -0.3384 0.02440 0.01686 -0.0133 1.0000 0.6534
-2.500 -0.3362 0.02480 0.01744 -0.0068 1.0000 0.7294
-2.250 -0.3366 0.02506 0.01777 0.0002 1.0000 0.7930
-2.000 -0.3367 0.02516 0.01790 0.0071 1.0000 0.8538
-1.750 -0.3046 0.02569 0.01831 0.0086 1.0000 0.9305
-1.500 -0.1359 0.02762 0.01943 -0.0171 1.0000 1.0000
-1.250 -0.1487 0.02713 0.01888 -0.0137 1.0000 1.0000
-1.000 -0.1590 0.02668 0.01835 -0.0104 1.0000 1.0000
-0.750 -0.1644 0.02636 0.01793 -0.0078 1.0000 1.0000
-0.500 -0.1272 0.02714 0.01848 -0.0123 0.9889 1.0000
-0.250 -0.0804 0.02818 0.01927 -0.0181 0.9735 1.0000
0.000 -0.0347 0.02916 0.02003 -0.0234 0.9584 1.0000
0.250 0.0089 0.03004 0.02072 -0.0280 0.9433 1.0000
0.500 0.0483 0.03080 0.02132 -0.0317 0.9278 1.0000
0.750 0.0876 0.03155 0.02193 -0.0352 0.9122 1.0000
1.000 0.1265 0.03229 0.02254 -0.0384 0.8969 1.0000
1.250 0.1645 0.03298 0.02313 -0.0412 0.8814 1.0000
1.500 0.2022 0.03365 0.02371 -0.0439 0.8660 1.0000
1.750 0.2391 0.03429 0.02429 -0.0462 0.8505 1.0000
2.000 0.2757 0.03489 0.02483 -0.0483 0.8350 1.0000
2.250 0.3122 0.03545 0.02535 -0.0503 0.8195 1.0000
2.500 0.3497 0.03595 0.02583 -0.0522 0.8044 1.0000
2.750 0.3850 0.03642 0.02630 -0.0537 0.7889 1.0000
3.000 0.4186 0.03688 0.02676 -0.0548 0.7733 1.0000
3.250 0.4524 0.03728 0.02717 -0.0557 0.7577 1.0000
3.500 0.4858 0.03764 0.02756 -0.0565 0.7422 1.0000
3.750 0.5195 0.03793 0.02789 -0.0571 0.7267 1.0000
4.000 0.5537 0.03813 0.02815 -0.0577 0.7112 1.0000
4.250 0.5889 0.03821 0.02828 -0.0581 0.6958 1.0000
4.500 0.6245 0.03823 0.02837 -0.0586 0.6803 1.0000
4.750 0.6618 0.03813 0.02837 -0.0590 0.6648 1.0000
5.000 0.6985 0.03795 0.02827 -0.0591 0.6491 1.0000
5.250 0.7357 0.03768 0.02809 -0.0592 0.6333 1.0000
5.500 0.7748 0.03724 0.02775 -0.0593 0.6173 1.0000
5.750 0.8164 0.03663 0.02722 -0.0596 0.6010 1.0000
6.000 0.8594 0.03592 0.02660 -0.0599 0.5841 1.0000
6.250 0.8731 0.03689 0.02765 -0.0578 0.5651 1.0000
6.500 0.8983 0.03720 0.02804 -0.0566 0.5463 1.0000
6.750 0.9312 0.03706 0.02798 -0.0560 0.5275 1.0000
7.000 0.9717 0.03647 0.02741 -0.0560 0.5081 1.0000
7.250 1.0052 0.03639 0.02734 -0.0555 0.4885 1.0000
7.500 1.0203 0.03733 0.02839 -0.0534 0.4688 1.0000
7.750 1.0459 0.03770 0.02880 -0.0522 0.4486 1.0000
8.000 1.0868 0.03728 0.02826 -0.0524 0.4273 1.0000
8.250 1.0977 0.03852 0.02963 -0.0499 0.4080 1.0000
8.500 1.1148 0.03946 0.03066 -0.0480 0.3885 1.0000
8.750 1.1399 0.04001 0.03118 -0.0469 0.3685 1.0000
9.000 1.1680 0.04057 0.03165 -0.0462 0.3487 1.0000
9.250 1.1791 0.04201 0.03324 -0.0438 0.3314 1.0000
9.500 1.1917 0.04348 0.03480 -0.0417 0.3147 1.0000
9.750 1.2046 0.04501 0.03642 -0.0397 0.2986 1.0000
10.000 1.2168 0.04656 0.03805 -0.0377 0.2830 1.0000
10.250 1.2291 0.04826 0.03982 -0.0357 0.2686 1.0000
10.500 1.2409 0.04987 0.04148 -0.0337 0.2541 1.0000
10.750 1.2534 0.05146 0.04312 -0.0319 0.2400 1.0000
11.000 1.2665 0.05297 0.04463 -0.0301 0.2260 1.0000
11.250 1.2412 0.05651 0.04856 -0.0255 0.2208 1.0000
11.500 1.2506 0.05832 0.05038 -0.0236 0.2094 1.0000
11.750 1.2169 0.06240 0.05475 -0.0191 0.2072 1.0000
12.000 1.1740 0.06798 0.06056 -0.0161 0.2074 1.0000
12.250 1.1198 0.07605 0.06879 -0.0157 0.2100 1.0000
12.500 1.0644 0.08663 0.07942 -0.0185 0.2122 1.0000
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Polar data table (+)
Polar graphs
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