DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il) Reynolds number: 50,000 Max Cl/Cd: 25.37 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dfvlrr4-il-50000-n5.txt Download as CSV file: xf-dfvlrr4-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DFVLR R-4 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5813 0.10251 0.09453 -0.0527 1.0000 0.0569
-12.000 -0.6009 0.09484 0.08686 -0.0567 1.0000 0.0564
-11.750 -0.6258 0.08754 0.07954 -0.0605 1.0000 0.0559
-11.500 -0.6522 0.08132 0.07327 -0.0631 1.0000 0.0555
-11.250 -0.6787 0.07620 0.06807 -0.0642 1.0000 0.0552
-11.000 -0.7046 0.07206 0.06384 -0.0638 1.0000 0.0550
-10.750 -0.7302 0.06874 0.06044 -0.0620 1.0000 0.0548
-10.500 -0.7548 0.06592 0.05753 -0.0592 1.0000 0.0547
-10.250 -0.7727 0.06282 0.05425 -0.0572 1.0000 0.0548
-10.000 -0.7857 0.05979 0.05099 -0.0550 1.0000 0.0550
-9.750 -0.7939 0.05680 0.04771 -0.0529 1.0000 0.0557
-9.500 -0.7980 0.05382 0.04435 -0.0510 1.0000 0.0567
-9.250 -0.7971 0.05095 0.04106 -0.0493 1.0000 0.0579
-9.000 -0.7864 0.04896 0.03905 -0.0480 1.0000 0.0596
-8.750 -0.7753 0.04697 0.03690 -0.0466 1.0000 0.0614
-8.500 -0.7624 0.04482 0.03451 -0.0452 1.0000 0.0632
-8.250 -0.7473 0.04272 0.03209 -0.0438 1.0000 0.0651
-8.000 -0.7308 0.04084 0.02979 -0.0424 1.0000 0.0681
-7.750 -0.7139 0.03944 0.02849 -0.0411 1.0000 0.0714
-7.500 -0.6959 0.03813 0.02705 -0.0396 1.0000 0.0757
-7.250 -0.6762 0.03689 0.02556 -0.0376 1.0000 0.0801
-7.000 -0.6588 0.03582 0.02461 -0.0359 1.0000 0.0855
-6.750 -0.6400 0.03493 0.02353 -0.0340 1.0000 0.0930
-6.500 -0.6237 0.03393 0.02264 -0.0324 1.0000 0.1012
-6.250 -0.6069 0.03295 0.02166 -0.0309 1.0000 0.1111
-6.000 -0.5899 0.03192 0.02062 -0.0297 1.0000 0.1238
-5.750 -0.5724 0.03076 0.01952 -0.0289 1.0000 0.1394
-5.500 -0.5534 0.02936 0.01831 -0.0289 1.0000 0.1623
-5.250 -0.5313 0.02753 0.01692 -0.0302 1.0000 0.2091
-5.000 -0.5109 0.02556 0.01650 -0.0310 1.0000 0.4005
-4.750 -0.4977 0.02614 0.01751 -0.0265 1.0000 0.5062
-4.500 -0.4815 0.02694 0.01830 -0.0229 1.0000 0.5591
-4.250 -0.4645 0.02777 0.01902 -0.0198 1.0000 0.5940
-4.000 -0.4466 0.02859 0.01968 -0.0170 1.0000 0.6227
-3.500 -0.4211 0.03085 0.02176 -0.0078 1.0000 0.6731
-3.250 -0.4052 0.03163 0.02241 -0.0046 1.0000 0.6979
-3.000 -0.3892 0.03202 0.02268 -0.0018 1.0000 0.7136
-2.750 -0.3715 0.03205 0.02259 0.0003 1.0000 0.7228
-2.500 -0.3484 0.03185 0.02223 0.0003 1.0000 0.7319
-2.250 -0.3258 0.03170 0.02193 0.0005 1.0000 0.7408
-2.000 -0.3042 0.03157 0.02169 0.0010 1.0000 0.7491
-1.750 -0.2796 0.03146 0.02145 0.0005 1.0000 0.7588
-1.500 -0.2568 0.03138 0.02128 0.0010 0.9987 0.7659
-1.250 -0.2227 0.03142 0.02119 -0.0014 0.9952 0.7746
-1.000 -0.1937 0.03141 0.02110 -0.0022 0.9909 0.7813
-0.750 -0.1602 0.03149 0.02108 -0.0043 0.9865 0.7895
-0.500 -0.1300 0.03152 0.02105 -0.0055 0.9818 0.7965
-0.250 -0.0983 0.03159 0.02106 -0.0072 0.9768 0.8038
0.000 -0.0641 0.03172 0.02114 -0.0093 0.9721 0.8106
0.250 -0.0353 0.03173 0.02114 -0.0103 0.9655 0.8171
0.500 0.0019 0.03192 0.02130 -0.0131 0.9601 0.8238
0.750 0.0288 0.03193 0.02133 -0.0136 0.9531 0.8300
1.000 0.0656 0.03214 0.02154 -0.0163 0.9467 0.8371
1.250 0.0940 0.03216 0.02161 -0.0169 0.9388 0.8430
1.500 0.1298 0.03231 0.02180 -0.0192 0.9311 0.8497
1.750 0.1597 0.03236 0.02192 -0.0203 0.9218 0.8556
2.000 0.1981 0.03244 0.02207 -0.0227 0.9137 0.8615
2.250 0.2297 0.03249 0.02220 -0.0241 0.9019 0.8672
2.500 0.2606 0.03241 0.02224 -0.0249 0.8905 0.8723
2.750 0.3002 0.03229 0.02224 -0.0272 0.8790 0.8777
3.000 0.3365 0.03189 0.02198 -0.0284 0.8609 0.8828
3.250 0.3766 0.03091 0.02114 -0.0292 0.8371 0.8876
3.500 0.4142 0.02973 0.02009 -0.0292 0.8084 0.8923
3.750 0.4494 0.02859 0.01912 -0.0289 0.7798 0.8967
4.000 0.4766 0.02758 0.01825 -0.0273 0.7494 0.9012
4.250 0.4976 0.02702 0.01785 -0.0254 0.7120 0.9064
4.500 0.5206 0.02647 0.01745 -0.0237 0.6620 0.9113
4.750 0.5744 0.02462 0.01530 -0.0243 0.5537 0.9145
5.000 0.6075 0.02497 0.01464 -0.0237 0.4002 0.9183
5.250 0.6194 0.02616 0.01520 -0.0216 0.3134 0.9235
5.500 0.6331 0.02719 0.01581 -0.0198 0.2626 0.9283
5.750 0.6519 0.02810 0.01650 -0.0190 0.2313 0.9334
6.000 0.6745 0.02898 0.01724 -0.0188 0.2104 0.9384
6.250 0.6993 0.02977 0.01795 -0.0187 0.1960 0.9434
6.500 0.7294 0.03055 0.01877 -0.0195 0.1835 0.9483
6.750 0.7618 0.03136 0.01964 -0.0206 0.1727 0.9533
7.000 0.7959 0.03225 0.02045 -0.0220 0.1634 0.9585
7.250 0.8327 0.03320 0.02162 -0.0237 0.1558 0.9638
7.500 0.8696 0.03434 0.02281 -0.0256 0.1499 0.9693
7.750 0.9051 0.03567 0.02430 -0.0273 0.1441 0.9760
8.250 0.9685 0.03842 0.02724 -0.0301 0.1326 1.0000
8.500 0.9950 0.04014 0.02936 -0.0307 0.1274 1.0000
8.750 1.0214 0.04190 0.03140 -0.0314 0.1226 1.0000
9.000 1.0491 0.04376 0.03336 -0.0324 0.1188 1.0000
9.250 1.0710 0.04599 0.03592 -0.0326 0.1149 1.0000
9.500 1.0872 0.04820 0.03859 -0.0321 0.1101 1.0000
9.750 1.1062 0.05019 0.04079 -0.0320 0.1060 1.0000
10.000 1.1300 0.05226 0.04282 -0.0328 0.1026 1.0000
10.250 1.1318 0.05554 0.04676 -0.0307 0.1000 1.0000
10.500 1.1320 0.05904 0.05081 -0.0289 0.0980 1.0000
10.750 1.1284 0.06264 0.05484 -0.0269 0.0962 1.0000
11.000 1.1205 0.06611 0.05866 -0.0248 0.0946 1.0000
11.250 1.1118 0.06955 0.06237 -0.0229 0.0930 1.0000
11.500 1.1115 0.07255 0.06552 -0.0221 0.0911 1.0000
11.750 1.1254 0.07493 0.06786 -0.0222 0.0887 1.0000
12.000 1.0941 0.08013 0.07343 -0.0207 0.0884 1.0000
12.250 1.0601 0.08635 0.07994 -0.0211 0.0883 1.0000
12.500 1.0231 0.09399 0.08782 -0.0235 0.0883 1.0000
12.750 0.9842 0.10356 0.09756 -0.0286 0.0886 1.0000
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