RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 100,000 Max Cl/Cd: 42.69 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5213-il-100000.txt Download as CSV file: xf-rae5213-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5213 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 -0.4882 0.09540 0.09014 -0.0202 1.0000 0.1276
-8.750 -0.4975 0.09182 0.08664 -0.0233 1.0000 0.1341
-8.500 -0.5533 0.08623 0.08122 -0.0349 1.0000 0.1363
-8.250 -0.4066 0.07560 0.07086 -0.0255 1.0000 0.1567
-8.000 -0.4051 0.07248 0.06778 -0.0254 1.0000 0.1655
-7.500 -0.5132 0.07358 0.06876 -0.0280 1.0000 0.1617
-7.250 -0.5587 0.06717 0.06221 -0.0376 1.0000 0.1706
-7.000 -0.5257 0.06576 0.06101 -0.0316 1.0000 0.1796
-6.750 -0.5300 0.06223 0.05750 -0.0321 1.0000 0.1920
-6.500 -0.5316 0.05921 0.05449 -0.0319 1.0000 0.2077
-6.250 -0.5262 0.05692 0.05225 -0.0301 1.0000 0.2254
-6.000 -0.5243 0.03921 0.03207 -0.0410 1.0000 0.0948
-5.750 -0.5045 0.03481 0.02709 -0.0396 1.0000 0.0801
-5.500 -0.4858 0.03169 0.02371 -0.0385 1.0000 0.0768
-5.250 -0.4655 0.02910 0.02069 -0.0372 1.0000 0.0750
-5.000 -0.4449 0.02735 0.01868 -0.0361 1.0000 0.0769
-4.750 -0.4232 0.02562 0.01668 -0.0348 1.0000 0.0779
-4.500 -0.4010 0.02403 0.01486 -0.0336 1.0000 0.0787
-4.250 -0.3787 0.02305 0.01359 -0.0323 1.0000 0.0816
-4.000 -0.3572 0.02147 0.01213 -0.0313 1.0000 0.0851
-3.750 -0.3353 0.02048 0.01114 -0.0301 1.0000 0.0886
-3.500 -0.3135 0.01973 0.01032 -0.0289 1.0000 0.0939
-3.250 -0.2923 0.01870 0.00951 -0.0279 1.0000 0.0998
-3.000 -0.2708 0.01801 0.00884 -0.0268 1.0000 0.1075
-2.750 -0.2493 0.01724 0.00822 -0.0260 1.0000 0.1230
-2.500 -0.2258 0.01590 0.00734 -0.0259 1.0000 0.1822
-2.250 -0.2161 0.01486 0.00838 -0.0218 1.0000 0.6535
-2.000 -0.2026 0.01533 0.00887 -0.0183 1.0000 0.6962
-1.750 -0.1913 0.01572 0.00932 -0.0143 1.0000 0.7325
-1.500 -0.1834 0.01602 0.00972 -0.0095 1.0000 0.7688
-1.250 -0.1792 0.01618 0.00999 -0.0039 1.0000 0.8056
-1.000 -0.1752 0.01619 0.01007 0.0015 1.0000 0.8386
-0.750 -0.1528 0.01634 0.01023 0.0032 0.9925 0.8693
-0.500 -0.1151 0.01655 0.01036 0.0010 0.9840 0.8850
-0.250 -0.0752 0.01673 0.01045 -0.0019 0.9752 0.8967
0.000 -0.0370 0.01683 0.01052 -0.0045 0.9659 0.9079
0.250 0.0031 0.01697 0.01061 -0.0073 0.9567 0.9201
0.500 0.0515 0.01718 0.01082 -0.0117 0.9489 0.9320
0.750 0.0942 0.01727 0.01091 -0.0151 0.9385 0.9451
1.000 0.1484 0.01742 0.01109 -0.0206 0.9295 0.9568
1.250 0.2160 0.01734 0.01105 -0.0278 0.9174 0.9640
1.500 0.2900 0.01641 0.01014 -0.0340 0.8910 0.9652
1.750 0.3572 0.01531 0.00909 -0.0387 0.8686 0.9673
2.000 0.4083 0.01472 0.00856 -0.0418 0.8498 0.9749
2.250 0.4550 0.01417 0.00808 -0.0442 0.8270 0.9844
2.500 0.4989 0.01363 0.00758 -0.0461 0.7969 0.9955
2.750 0.5197 0.01332 0.00727 -0.0441 0.7633 1.0000
3.000 0.5358 0.01310 0.00697 -0.0413 0.7232 1.0000
3.250 0.5541 0.01298 0.00669 -0.0387 0.6524 1.0000
3.500 0.5637 0.01395 0.00632 -0.0343 0.3993 1.0000
3.750 0.5766 0.01593 0.00708 -0.0326 0.2507 1.0000
4.000 0.6002 0.01700 0.00779 -0.0323 0.2177 1.0000
4.250 0.6254 0.01796 0.00852 -0.0321 0.1983 1.0000
4.500 0.6518 0.01890 0.00930 -0.0321 0.1837 1.0000
4.750 0.6789 0.01993 0.01020 -0.0321 0.1720 1.0000
5.000 0.7062 0.02118 0.01123 -0.0322 0.1616 1.0000
5.250 0.7336 0.02209 0.01221 -0.0321 0.1519 1.0000
5.500 0.7610 0.02345 0.01347 -0.0321 0.1432 1.0000
5.750 0.7875 0.02450 0.01455 -0.0319 0.1346 1.0000
6.000 0.8140 0.02603 0.01612 -0.0318 0.1272 1.0000
6.250 0.8397 0.02722 0.01738 -0.0315 0.1199 1.0000
6.500 0.8648 0.02905 0.01929 -0.0312 0.1140 1.0000
6.750 0.8890 0.03054 0.02103 -0.0306 0.1082 1.0000
7.000 0.9138 0.03250 0.02291 -0.0305 0.1036 1.0000
7.250 0.9337 0.03464 0.02554 -0.0293 0.0997 1.0000
7.500 0.9534 0.03693 0.02822 -0.0282 0.0965 1.0000
7.750 0.9724 0.03944 0.03102 -0.0272 0.0944 1.0000
8.000 0.9936 0.04170 0.03332 -0.0268 0.0921 1.0000
8.250 1.0096 0.04551 0.03724 -0.0262 0.0902 1.0000
8.500 1.0178 0.04872 0.04104 -0.0243 0.0894 1.0000
8.750 1.0256 0.05274 0.04546 -0.0228 0.0894 1.0000
9.000 1.0343 0.05730 0.05025 -0.0219 0.0900 1.0000
9.250 0.9884 0.06685 0.06097 -0.0185 0.1002 1.0000
9.500 0.9027 0.09650 0.09144 -0.0267 0.1785 1.0000
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Polar data table (+)
Polar graphs
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