RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 100,000 Max Cl/Cd: 40.25 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5214-il-100000.txt Download as CSV file: xf-rae5214-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5214 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4945 0.09542 0.09015 -0.0200 1.0000 0.1275
-8.750 -0.5004 0.09192 0.08673 -0.0224 1.0000 0.1337
-8.500 -0.5591 0.08628 0.08125 -0.0344 1.0000 0.1364
-8.250 -0.5007 0.08449 0.07941 -0.0240 1.0000 0.1427
-8.000 -0.5123 0.08089 0.07590 -0.0263 1.0000 0.1496
-7.250 -0.5677 0.06730 0.06233 -0.0371 1.0000 0.1706
-7.000 -0.5336 0.06571 0.06095 -0.0310 1.0000 0.1781
-6.750 -0.5402 0.06211 0.05736 -0.0318 1.0000 0.1914
-6.500 -0.5430 0.05907 0.05430 -0.0318 1.0000 0.2070
-6.000 -0.5331 0.03940 0.03223 -0.0400 1.0000 0.0948
-5.750 -0.5134 0.03497 0.02723 -0.0386 1.0000 0.0802
-5.500 -0.4946 0.03179 0.02379 -0.0375 1.0000 0.0769
-5.250 -0.4741 0.02914 0.02069 -0.0363 1.0000 0.0748
-5.000 -0.4533 0.02741 0.01872 -0.0351 1.0000 0.0768
-4.750 -0.4313 0.02568 0.01671 -0.0339 1.0000 0.0779
-4.500 -0.4087 0.02408 0.01487 -0.0327 1.0000 0.0787
-4.250 -0.3859 0.02304 0.01355 -0.0314 1.0000 0.0816
-4.000 -0.3639 0.02147 0.01208 -0.0305 1.0000 0.0851
-3.750 -0.3415 0.02045 0.01106 -0.0293 1.0000 0.0887
-3.500 -0.3190 0.01967 0.01021 -0.0282 1.0000 0.0940
-3.250 -0.2973 0.01861 0.00938 -0.0271 1.0000 0.1003
-3.000 -0.2751 0.01784 0.00865 -0.0261 1.0000 0.1085
-2.750 -0.2528 0.01704 0.00800 -0.0253 1.0000 0.1248
-2.500 -0.2289 0.01418 0.00700 -0.0261 1.0000 0.4273
-2.250 -0.2191 0.01476 0.00823 -0.0208 1.0000 0.6596
-2.000 -0.2050 0.01518 0.00868 -0.0172 1.0000 0.7002
-1.750 -0.1934 0.01553 0.00910 -0.0130 1.0000 0.7374
-1.500 -0.1854 0.01578 0.00945 -0.0079 1.0000 0.7751
-1.250 -0.1801 0.01589 0.00964 -0.0024 1.0000 0.8116
-1.000 -0.1759 0.01582 0.00965 0.0032 1.0000 0.8436
-0.750 -0.1673 0.01568 0.00953 0.0073 1.0000 0.8686
-0.500 -0.1510 0.01557 0.00939 0.0092 1.0000 0.8860
-0.250 -0.1295 0.01553 0.00930 0.0096 1.0000 0.8994
0.000 -0.1072 0.01552 0.00926 0.0099 1.0000 0.9138
0.250 -0.0660 0.01581 0.00953 0.0065 0.9932 0.9278
0.500 -0.0154 0.01622 0.00992 0.0013 0.9850 0.9421
0.750 0.0435 0.01661 0.01031 -0.0055 0.9744 0.9560
1.000 0.1109 0.01683 0.01053 -0.0133 0.9562 0.9673
1.250 0.1939 0.01672 0.01043 -0.0226 0.9327 0.9694
1.500 0.2662 0.01608 0.00985 -0.0292 0.9072 0.9719
1.750 0.3323 0.01544 0.00930 -0.0351 0.8897 0.9754
2.000 0.3915 0.01470 0.00865 -0.0393 0.8698 0.9805
2.250 0.4423 0.01395 0.00799 -0.0419 0.8415 0.9884
2.500 0.4855 0.01323 0.00732 -0.0431 0.7988 1.0000
2.750 0.5013 0.01281 0.00683 -0.0397 0.7424 1.0000
3.000 0.5144 0.01278 0.00613 -0.0352 0.5671 1.0000
3.250 0.5186 0.01478 0.00641 -0.0313 0.3124 1.0000
3.500 0.5400 0.01600 0.00706 -0.0308 0.2568 1.0000
3.750 0.5654 0.01699 0.00773 -0.0309 0.2298 1.0000
4.000 0.5923 0.01797 0.00845 -0.0311 0.2111 1.0000
4.250 0.6203 0.01886 0.00923 -0.0313 0.1960 1.0000
4.500 0.6485 0.01984 0.01014 -0.0316 0.1835 1.0000
4.750 0.6767 0.02101 0.01114 -0.0318 0.1729 1.0000
5.000 0.7044 0.02193 0.01209 -0.0318 0.1627 1.0000
5.250 0.7321 0.02319 0.01333 -0.0319 0.1537 1.0000
5.500 0.7589 0.02423 0.01432 -0.0319 0.1447 1.0000
5.750 0.7852 0.02554 0.01577 -0.0316 0.1365 1.0000
6.000 0.8112 0.02668 0.01683 -0.0315 0.1288 1.0000
6.250 0.8358 0.02816 0.01858 -0.0309 0.1216 1.0000
6.500 0.8610 0.02941 0.01979 -0.0307 0.1153 1.0000
6.750 0.8836 0.03136 0.02207 -0.0299 0.1097 1.0000
7.000 0.9066 0.03305 0.02397 -0.0292 0.1047 1.0000
7.250 0.9301 0.03527 0.02604 -0.0292 0.1005 1.0000
7.500 0.9463 0.03770 0.02917 -0.0275 0.0971 1.0000
7.750 0.9617 0.04082 0.03277 -0.0261 0.0951 1.0000
8.000 0.9755 0.04405 0.03639 -0.0248 0.0935 1.0000
8.250 0.9903 0.04678 0.03933 -0.0237 0.0916 1.0000
8.500 1.0135 0.04909 0.04141 -0.0240 0.0890 1.0000
8.750 1.0189 0.05341 0.04615 -0.0224 0.0885 1.0000
9.000 1.0252 0.05768 0.05079 -0.0211 0.0890 1.0000
9.250 0.9675 0.06937 0.06361 -0.0181 0.0986 1.0000
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Polar data table (+)
Polar graphs
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