RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 50,000 Max Cl/Cd: 27.54 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5214-il-50000-n5.txt Download as CSV file: xf-rae5214-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5226 0.09849 0.09071 -0.0243 1.0000 0.0574
-9.500 -0.5446 0.08858 0.08086 -0.0329 1.0000 0.0539
-9.250 -0.5469 0.08394 0.07626 -0.0350 1.0000 0.0534
-9.000 -0.5544 0.07908 0.07143 -0.0377 1.0000 0.0528
-8.750 -0.5673 0.07442 0.06679 -0.0402 1.0000 0.0522
-8.500 -0.5798 0.06990 0.06223 -0.0423 1.0000 0.0516
-8.250 -0.5895 0.06548 0.05768 -0.0437 1.0000 0.0511
-8.000 -0.5954 0.06121 0.05323 -0.0444 1.0000 0.0508
-7.750 -0.5969 0.05724 0.04902 -0.0446 1.0000 0.0508
-7.500 -0.5945 0.05354 0.04503 -0.0445 1.0000 0.0513
-7.250 -0.5890 0.04999 0.04110 -0.0441 1.0000 0.0522
-7.000 -0.5804 0.04659 0.03724 -0.0435 1.0000 0.0531
-6.750 -0.5684 0.04336 0.03349 -0.0427 1.0000 0.0538
-6.500 -0.5528 0.04059 0.03040 -0.0418 1.0000 0.0544
-6.250 -0.5352 0.03831 0.02797 -0.0409 1.0000 0.0554
-6.000 -0.5169 0.03635 0.02582 -0.0399 1.0000 0.0575
-5.750 -0.4974 0.03439 0.02353 -0.0388 1.0000 0.0600
-5.500 -0.4766 0.03248 0.02118 -0.0376 1.0000 0.0620
-5.250 -0.4561 0.03082 0.01953 -0.0364 1.0000 0.0640
-5.000 -0.4354 0.02950 0.01814 -0.0351 1.0000 0.0674
-4.750 -0.4139 0.02826 0.01667 -0.0336 1.0000 0.0710
-4.500 -0.3938 0.02705 0.01553 -0.0319 1.0000 0.0738
-4.250 -0.3739 0.02608 0.01454 -0.0303 1.0000 0.0782
-4.000 -0.3545 0.02515 0.01356 -0.0287 1.0000 0.0837
-3.750 -0.3352 0.02425 0.01266 -0.0272 1.0000 0.0899
-3.500 -0.3156 0.02336 0.01179 -0.0260 1.0000 0.0984
-3.250 -0.2949 0.02243 0.01090 -0.0252 1.0000 0.1123
-3.000 -0.2733 0.02133 0.00996 -0.0248 1.0000 0.1401
-2.750 -0.2534 0.01881 0.00919 -0.0253 1.0000 0.3875
-2.500 -0.2431 0.01897 0.01006 -0.0204 1.0000 0.6045
-2.250 -0.2311 0.01938 0.01053 -0.0161 1.0000 0.6764
-2.000 -0.2257 0.01972 0.01101 -0.0099 1.0000 0.7331
-1.750 -0.2218 0.01985 0.01124 -0.0034 1.0000 0.7819
-1.500 -0.2117 0.01975 0.01112 0.0010 1.0000 0.8141
-1.250 -0.1920 0.01959 0.01082 0.0023 1.0000 0.8282
-1.000 -0.1709 0.01943 0.01055 0.0032 1.0000 0.8401
-0.750 -0.1491 0.01932 0.01033 0.0038 1.0000 0.8526
-0.500 -0.1264 0.01924 0.01018 0.0042 0.9997 0.8658
-0.250 -0.0896 0.01935 0.01020 0.0019 0.9917 0.8784
0.000 -0.0506 0.01951 0.01030 -0.0009 0.9840 0.8916
0.250 -0.0100 0.01966 0.01042 -0.0039 0.9756 0.9056
0.500 0.0324 0.01981 0.01057 -0.0074 0.9665 0.9208
0.750 0.0791 0.01999 0.01076 -0.0117 0.9573 0.9383
1.250 0.1757 0.02033 0.01117 -0.0211 0.9363 1.0000
1.500 0.2252 0.02042 0.01131 -0.0254 0.9192 1.0000
1.750 0.2878 0.02001 0.01098 -0.0306 0.8877 1.0000
2.000 0.3447 0.01928 0.01033 -0.0338 0.8506 1.0000
2.250 0.3820 0.01881 0.00991 -0.0342 0.8157 1.0000
2.500 0.4157 0.01843 0.00956 -0.0339 0.7769 1.0000
2.750 0.4441 0.01820 0.00933 -0.0330 0.7282 1.0000
3.000 0.4732 0.01801 0.00904 -0.0318 0.6551 1.0000
3.250 0.5017 0.01822 0.00852 -0.0299 0.4957 1.0000
3.500 0.5174 0.01954 0.00876 -0.0277 0.3431 1.0000
3.750 0.5367 0.02084 0.00943 -0.0268 0.2732 1.0000
4.000 0.5593 0.02193 0.01018 -0.0264 0.2388 1.0000
4.250 0.5836 0.02292 0.01097 -0.0261 0.2157 1.0000
4.500 0.6091 0.02388 0.01182 -0.0259 0.1984 1.0000
4.750 0.6359 0.02483 0.01270 -0.0259 0.1840 1.0000
5.000 0.6635 0.02583 0.01361 -0.0259 0.1719 1.0000
5.250 0.6913 0.02681 0.01459 -0.0260 0.1609 1.0000
5.500 0.7195 0.02787 0.01571 -0.0260 0.1508 1.0000
5.750 0.7469 0.02904 0.01674 -0.0260 0.1426 1.0000
6.000 0.7742 0.03024 0.01817 -0.0259 0.1340 1.0000
6.250 0.8004 0.03152 0.01931 -0.0258 0.1273 1.0000
6.500 0.8257 0.03293 0.02104 -0.0255 0.1197 1.0000
6.750 0.8504 0.03424 0.02229 -0.0253 0.1139 1.0000
7.000 0.8734 0.03599 0.02441 -0.0247 0.1074 1.0000
7.250 0.8963 0.03742 0.02587 -0.0243 0.1022 1.0000
7.500 0.9170 0.03949 0.02825 -0.0237 0.0974 1.0000
7.750 0.9365 0.04150 0.03056 -0.0229 0.0927 1.0000
8.000 0.9572 0.04320 0.03228 -0.0224 0.0894 1.0000
8.250 0.9706 0.04619 0.03577 -0.0213 0.0861 1.0000
8.500 0.9821 0.04909 0.03910 -0.0201 0.0829 1.0000
8.750 0.9956 0.05155 0.04178 -0.0192 0.0805 1.0000
9.000 1.0101 0.05388 0.04420 -0.0185 0.0787 1.0000
9.250 1.0103 0.05786 0.04863 -0.0171 0.0772 1.0000
9.500 1.0009 0.06253 0.05380 -0.0155 0.0760 1.0000
9.750 0.9868 0.06724 0.05888 -0.0143 0.0750 1.0000
10.000 0.9664 0.07202 0.06392 -0.0133 0.0745 1.0000
10.250 0.9379 0.07744 0.06953 -0.0133 0.0745 1.0000
10.500 0.9038 0.08473 0.07696 -0.0164 0.0750 1.0000
10.750 0.8689 0.09451 0.08681 -0.0229 0.0756 1.0000
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Polar data table (+)
Polar graphs
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