DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il) Reynolds number: 200,000 Max Cl/Cd: 47.93 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dfvlrr4-il-200000-n5.txt Download as CSV file: xf-dfvlrr4-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7912 0.07447 0.06974 -0.0658 1.0000 0.0191
-14.000 -0.8196 0.06691 0.06194 -0.0699 1.0000 0.0190
-13.750 -0.8388 0.06147 0.05629 -0.0721 1.0000 0.0191
-13.500 -0.8537 0.05707 0.05169 -0.0733 1.0000 0.0191
-13.250 -0.8652 0.05342 0.04787 -0.0736 1.0000 0.0192
-13.000 -0.8746 0.05030 0.04457 -0.0733 1.0000 0.0194
-12.750 -0.8826 0.04760 0.04171 -0.0724 1.0000 0.0195
-12.500 -0.8895 0.04526 0.03922 -0.0709 1.0000 0.0197
-12.250 -0.8958 0.04318 0.03700 -0.0689 1.0000 0.0199
-12.000 -0.9025 0.04138 0.03506 -0.0663 1.0000 0.0201
-11.750 -0.9104 0.03984 0.03340 -0.0629 1.0000 0.0202
-11.500 -0.9210 0.03859 0.03205 -0.0588 1.0000 0.0204
-11.250 -0.9322 0.03748 0.03083 -0.0543 1.0000 0.0207
-11.000 -0.9350 0.03618 0.02939 -0.0512 1.0000 0.0210
-10.750 -0.9170 0.03439 0.02737 -0.0519 0.9978 0.0216
-10.500 -0.8932 0.03269 0.02539 -0.0533 0.9952 0.0223
-10.250 -0.8699 0.03116 0.02380 -0.0543 0.9926 0.0228
-10.000 -0.8454 0.02990 0.02249 -0.0555 0.9897 0.0234
-9.750 -0.8196 0.02873 0.02123 -0.0567 0.9872 0.0241
-9.500 -0.7926 0.02760 0.01999 -0.0579 0.9853 0.0248
-9.250 -0.7683 0.02654 0.01884 -0.0585 0.9823 0.0257
-9.000 -0.7433 0.02553 0.01772 -0.0591 0.9790 0.0266
-8.750 -0.7161 0.02453 0.01665 -0.0603 0.9764 0.0278
-8.500 -0.6868 0.02366 0.01575 -0.0619 0.9743 0.0293
-8.250 -0.6562 0.02283 0.01487 -0.0636 0.9727 0.0312
-8.000 -0.6336 0.02209 0.01403 -0.0636 0.9683 0.0328
-7.750 -0.6064 0.02118 0.01312 -0.0647 0.9653 0.0348
-7.500 -0.5763 0.02045 0.01236 -0.0663 0.9630 0.0377
-7.250 -0.5448 0.01972 0.01160 -0.0681 0.9613 0.0418
-7.000 -0.5118 0.01908 0.01093 -0.0701 0.9599 0.0473
-6.750 -0.4813 0.01843 0.01029 -0.0717 0.9576 0.0533
-6.500 -0.4544 0.01792 0.00978 -0.0723 0.9535 0.0603
-6.250 -0.4229 0.01742 0.00929 -0.0739 0.9510 0.0701
-6.000 -0.3898 0.01692 0.00879 -0.0758 0.9491 0.0820
-5.750 -0.3555 0.01634 0.00830 -0.0780 0.9476 0.0999
-5.500 -0.3201 0.01569 0.00780 -0.0806 0.9465 0.1310
-5.250 -0.2827 0.01476 0.00719 -0.0841 0.9456 0.1979
-5.000 -0.2406 0.01330 0.00653 -0.0894 0.9452 0.3664
-4.750 -0.2030 0.01281 0.00630 -0.0922 0.9444 0.4440
-4.500 -0.1747 0.01263 0.00629 -0.0927 0.9404 0.4924
-4.250 -0.1446 0.01254 0.00635 -0.0933 0.9373 0.5330
-4.000 -0.1135 0.01256 0.00646 -0.0939 0.9349 0.5691
-3.750 -0.0829 0.01268 0.00667 -0.0942 0.9328 0.5960
-3.500 -0.0508 0.01279 0.00677 -0.0950 0.9312 0.6142
-3.250 -0.0185 0.01290 0.00687 -0.0957 0.9297 0.6270
-3.000 0.0111 0.01304 0.00699 -0.0960 0.9270 0.6389
-2.750 0.0375 0.01320 0.00712 -0.0957 0.9226 0.6491
-2.500 0.0665 0.01332 0.00723 -0.0959 0.9198 0.6547
-2.250 0.0975 0.01339 0.00728 -0.0965 0.9176 0.6597
-2.000 0.1323 0.01336 0.00719 -0.0982 0.9159 0.6671
-1.750 0.1633 0.01345 0.00730 -0.0986 0.9142 0.6709
-1.500 0.1912 0.01358 0.00743 -0.0986 0.9108 0.6761
-1.250 0.2207 0.01364 0.00746 -0.0992 0.9068 0.6827
-1.000 0.2490 0.01374 0.00759 -0.0992 0.9037 0.6855
-0.750 0.2801 0.01379 0.00765 -0.0998 0.9012 0.6892
-0.500 0.3147 0.01374 0.00759 -0.1012 0.8991 0.6947
-0.250 0.3446 0.01370 0.00758 -0.1015 0.8935 0.6991
0.000 0.3755 0.01346 0.00736 -0.1014 0.8838 0.7020
0.250 0.4074 0.01301 0.00687 -0.1012 0.8665 0.7054
0.500 0.4375 0.01266 0.00647 -0.1009 0.8445 0.7096
0.750 0.4673 0.01250 0.00628 -0.1010 0.8258 0.7138
1.000 0.4939 0.01247 0.00627 -0.1003 0.8091 0.7161
1.250 0.5217 0.01244 0.00623 -0.0998 0.7897 0.7188
1.500 0.5500 0.01241 0.00618 -0.0996 0.7648 0.7220
1.750 0.5798 0.01240 0.00606 -0.0998 0.7271 0.7262
2.000 0.6053 0.01263 0.00588 -0.0987 0.6296 0.7296
2.250 0.6182 0.01359 0.00613 -0.0954 0.4988 0.7321
2.500 0.6329 0.01456 0.00657 -0.0930 0.3935 0.7352
2.750 0.6517 0.01538 0.00697 -0.0915 0.3049 0.7390
3.000 0.6743 0.01611 0.00732 -0.0911 0.2346 0.7432
3.250 0.6967 0.01668 0.00766 -0.0903 0.1907 0.7455
3.500 0.7191 0.01715 0.00801 -0.0894 0.1645 0.7475
3.750 0.7424 0.01757 0.00837 -0.0886 0.1475 0.7499
4.000 0.7668 0.01795 0.00871 -0.0881 0.1350 0.7526
4.250 0.7922 0.01831 0.00906 -0.0878 0.1262 0.7558
4.500 0.8185 0.01873 0.00942 -0.0879 0.1187 0.7594
4.750 0.8426 0.01910 0.00982 -0.0873 0.1136 0.7615
5.000 0.8656 0.01948 0.01024 -0.0865 0.1090 0.7634
5.250 0.8884 0.01994 0.01070 -0.0857 0.1050 0.7654
5.500 0.9113 0.02044 0.01121 -0.0849 0.1014 0.7676
5.750 0.9358 0.02082 0.01165 -0.0845 0.0975 0.7701
6.000 0.9604 0.02124 0.01209 -0.0842 0.0934 0.7730
6.250 0.9846 0.02182 0.01263 -0.0839 0.0898 0.7758
6.500 1.0070 0.02232 0.01319 -0.0831 0.0873 0.7775
6.750 1.0294 0.02276 0.01373 -0.0822 0.0850 0.7793
7.000 1.0518 0.02325 0.01429 -0.0813 0.0826 0.7814
7.250 1.0742 0.02376 0.01487 -0.0806 0.0803 0.7836
7.500 1.0963 0.02434 0.01547 -0.0798 0.0781 0.7859
7.750 1.1179 0.02514 0.01625 -0.0791 0.0760 0.7884
8.000 1.1421 0.02567 0.01691 -0.0787 0.0743 0.7910
8.250 1.1646 0.02625 0.01761 -0.0780 0.0723 0.7930
8.500 1.1853 0.02683 0.01830 -0.0770 0.0702 0.7947
8.750 1.2056 0.02742 0.01897 -0.0759 0.0682 0.7967
9.000 1.2251 0.02806 0.01966 -0.0748 0.0664 0.7987
9.250 1.2441 0.02881 0.02048 -0.0736 0.0643 0.8007
9.500 1.2628 0.02938 0.02120 -0.0723 0.0619 0.8028
9.750 1.2800 0.02994 0.02185 -0.0709 0.0595 0.8051
10.000 1.2974 0.03057 0.02254 -0.0696 0.0576 0.8075
10.250 1.3123 0.03145 0.02344 -0.0679 0.0558 0.8092
10.500 1.3293 0.03230 0.02450 -0.0665 0.0541 0.8110
10.750 1.3456 0.03316 0.02554 -0.0651 0.0520 0.8129
11.000 1.3607 0.03399 0.02649 -0.0636 0.0501 0.8148
11.250 1.3745 0.03480 0.02737 -0.0620 0.0484 0.8168
11.500 1.3875 0.03583 0.02848 -0.0605 0.0468 0.8189
11.750 1.4022 0.03686 0.02975 -0.0592 0.0446 0.8210
12.000 1.4153 0.03781 0.03084 -0.0577 0.0425 0.8230
12.250 1.4262 0.03870 0.03183 -0.0561 0.0409 0.8249
12.500 1.4359 0.03990 0.03315 -0.0544 0.0394 0.8270
12.750 1.4459 0.04123 0.03467 -0.0528 0.0377 0.8291
13.000 1.4548 0.04259 0.03617 -0.0513 0.0362 0.8313
13.250 1.4625 0.04402 0.03769 -0.0499 0.0349 0.8334
13.500 1.4669 0.04579 0.03953 -0.0484 0.0338 0.8355
13.750 1.4716 0.04786 0.04183 -0.0470 0.0325 0.8375
14.000 1.4736 0.05003 0.04421 -0.0455 0.0313 0.8394
14.250 1.4745 0.05232 0.04668 -0.0442 0.0302 0.8414
14.500 1.4737 0.05486 0.04937 -0.0432 0.0292 0.8436
14.750 1.4703 0.05778 0.05241 -0.0424 0.0285 0.8458
15.000 1.4640 0.06124 0.05604 -0.0419 0.0278 0.8479
15.250 1.4564 0.06511 0.06014 -0.0418 0.0270 0.8498
15.500 1.4463 0.06955 0.06480 -0.0423 0.0264 0.8516
15.750 1.4340 0.07454 0.07000 -0.0435 0.0259 0.8532
16.000 1.4188 0.08039 0.07606 -0.0456 0.0254 0.8548
16.250 1.4001 0.08739 0.08328 -0.0488 0.0251 0.8565
16.500 1.3761 0.09597 0.09210 -0.0534 0.0250 0.8580
16.750 1.3440 0.10692 0.10331 -0.0599 0.0250 0.8590
17.000 1.2912 0.12325 0.11998 -0.0701 0.0256 0.8589
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