RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: RAE 5215 AIRFOIL (rae5215-il) Reynolds number: 50,000 Max Cl/Cd: 26.66 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5215-il-50000-n5.txt Download as CSV file: xf-rae5215-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5215 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5767 0.08989 0.08228 -0.0276 1.0000 0.0549
-9.000 -0.5796 0.08485 0.07727 -0.0305 1.0000 0.0543
-8.750 -0.5873 0.07964 0.07208 -0.0340 1.0000 0.0537
-8.500 -0.5970 0.07436 0.06676 -0.0378 1.0000 0.0530
-8.250 -0.6046 0.06920 0.06148 -0.0407 1.0000 0.0523
-8.000 -0.6090 0.06422 0.05630 -0.0430 1.0000 0.0517
-7.750 -0.6088 0.05954 0.05134 -0.0445 1.0000 0.0512
-7.500 -0.6041 0.05515 0.04662 -0.0454 1.0000 0.0510
-7.250 -0.5952 0.05113 0.04223 -0.0459 1.0000 0.0510
-7.000 -0.5826 0.04766 0.03838 -0.0460 1.0000 0.0517
-6.750 -0.5677 0.04442 0.03470 -0.0460 1.0000 0.0532
-6.500 -0.5505 0.04127 0.03096 -0.0457 1.0000 0.0547
-6.250 -0.5311 0.03865 0.02803 -0.0452 1.0000 0.0559
-6.000 -0.5107 0.03650 0.02572 -0.0446 1.0000 0.0572
-5.750 -0.4896 0.03461 0.02361 -0.0438 1.0000 0.0597
-5.500 -0.4672 0.03273 0.02134 -0.0430 1.0000 0.0625
-5.250 -0.4451 0.03099 0.01946 -0.0419 1.0000 0.0645
-5.000 -0.4232 0.02959 0.01804 -0.0408 1.0000 0.0673
-4.750 -0.4010 0.02838 0.01666 -0.0395 1.0000 0.0715
-4.500 -0.3797 0.02720 0.01550 -0.0380 1.0000 0.0750
-4.250 -0.3585 0.02619 0.01447 -0.0366 1.0000 0.0791
-4.000 -0.3374 0.02525 0.01349 -0.0353 1.0000 0.0851
-3.750 -0.3160 0.02435 0.01256 -0.0342 1.0000 0.0925
-3.500 -0.2939 0.02340 0.01165 -0.0336 1.0000 0.1026
-3.250 -0.2708 0.02241 0.01071 -0.0333 1.0000 0.1205
-3.000 -0.2447 0.02088 0.00962 -0.0342 1.0000 0.1744
-2.750 -0.2272 0.01912 0.00999 -0.0325 1.0000 0.5494
-2.500 -0.2115 0.01960 0.01055 -0.0288 1.0000 0.6470
-2.250 -0.2001 0.02004 0.01107 -0.0239 1.0000 0.7105
-2.000 -0.1948 0.02030 0.01145 -0.0172 1.0000 0.7634
-1.750 -0.1854 0.02025 0.01142 -0.0121 1.0000 0.7993
-1.500 -0.1644 0.02008 0.01111 -0.0107 1.0000 0.8154
-1.250 -0.1411 0.01992 0.01081 -0.0101 1.0000 0.8270
-1.000 -0.1175 0.01977 0.01056 -0.0097 1.0000 0.8382
-0.750 -0.0929 0.01967 0.01036 -0.0096 1.0000 0.8501
-0.500 -0.0690 0.01958 0.01021 -0.0093 1.0000 0.8622
-0.250 -0.0453 0.01951 0.01009 -0.0089 1.0000 0.8747
0.000 -0.0213 0.01946 0.01003 -0.0088 1.0000 0.8885
0.250 0.0032 0.01945 0.01002 -0.0088 1.0000 0.9041
0.500 0.0289 0.01947 0.01006 -0.0091 1.0000 0.9230
0.750 0.0561 0.01953 0.01016 -0.0101 1.0000 0.9505
1.000 0.0972 0.01968 0.01035 -0.0140 0.9897 1.0000
1.250 0.1423 0.02007 0.01073 -0.0186 0.9811 1.0000
1.500 0.2004 0.02039 0.01108 -0.0250 0.9629 1.0000
1.750 0.2981 0.01964 0.01045 -0.0355 0.9037 1.0000
2.000 0.3503 0.01903 0.00991 -0.0383 0.8648 1.0000
2.250 0.3873 0.01870 0.00966 -0.0390 0.8319 1.0000
2.500 0.4206 0.01839 0.00942 -0.0388 0.7902 1.0000
2.750 0.4495 0.01813 0.00918 -0.0377 0.7243 1.0000
3.000 0.4820 0.01808 0.00826 -0.0355 0.5075 1.0000
3.500 0.5191 0.02105 0.00933 -0.0329 0.2671 1.0000
3.750 0.5439 0.02210 0.01007 -0.0329 0.2372 1.0000
4.000 0.5702 0.02301 0.01082 -0.0329 0.2173 1.0000
4.250 0.5972 0.02392 0.01159 -0.0330 0.2018 1.0000
4.500 0.6253 0.02479 0.01243 -0.0332 0.1884 1.0000
4.750 0.6542 0.02567 0.01332 -0.0334 0.1764 1.0000
5.000 0.6831 0.02667 0.01422 -0.0336 0.1663 1.0000
5.250 0.7118 0.02764 0.01522 -0.0337 0.1562 1.0000
5.500 0.7405 0.02878 0.01640 -0.0339 0.1474 1.0000
5.750 0.7682 0.02994 0.01756 -0.0339 0.1393 1.0000
6.000 0.7957 0.03131 0.01905 -0.0339 0.1316 1.0000
6.250 0.8221 0.03264 0.02046 -0.0339 0.1245 1.0000
6.500 0.8476 0.03423 0.02220 -0.0337 0.1179 1.0000
6.750 0.8722 0.03576 0.02392 -0.0334 0.1113 1.0000
7.000 0.8960 0.03745 0.02570 -0.0332 0.1060 1.0000
7.250 0.9180 0.03942 0.02807 -0.0326 0.1001 1.0000
7.500 0.9404 0.04101 0.02967 -0.0322 0.0959 1.0000
7.750 0.9584 0.04366 0.03283 -0.0314 0.0915 1.0000
8.000 0.9759 0.04611 0.03562 -0.0305 0.0877 1.0000
8.250 0.9949 0.04805 0.03765 -0.0300 0.0849 1.0000
8.500 1.0057 0.05137 0.04143 -0.0288 0.0821 1.0000
8.750 1.0111 0.05526 0.04586 -0.0275 0.0795 1.0000
9.000 1.0160 0.05893 0.04991 -0.0263 0.0778 1.0000
9.250 1.0200 0.06245 0.05371 -0.0253 0.0764 1.0000
9.500 1.0280 0.06519 0.05657 -0.0244 0.0751 1.0000
9.750 1.0264 0.06898 0.06057 -0.0234 0.0740 1.0000
10.000 1.0037 0.07471 0.06668 -0.0225 0.0736 1.0000
10.250 0.9764 0.08025 0.07245 -0.0220 0.0735 1.0000
10.500 0.9475 0.08682 0.07917 -0.0239 0.0737 1.0000
10.750 0.9188 0.09500 0.08746 -0.0285 0.0739 1.0000
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Polar data table (+)
Polar graphs
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