DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il) Reynolds number: 100,000 Max Cl/Cd: 33.64 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dfvlrr4-il-100000.txt Download as CSV file: xf-dfvlrr4-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5545 0.10573 0.10053 -0.0442 1.0000 0.1683
-10.500 -0.5650 0.06804 0.06309 -0.0586 1.0000 0.0882
-10.250 -0.6084 0.06225 0.05726 -0.0580 1.0000 0.0863
-10.000 -0.6537 0.05827 0.05322 -0.0552 1.0000 0.0850
-9.750 -0.7605 0.06716 0.06170 -0.0519 1.0000 0.0894
-9.500 -0.8058 0.06053 0.05444 -0.0492 1.0000 0.0781
-9.250 -0.8069 0.05646 0.05024 -0.0476 1.0000 0.0760
-9.000 -0.8108 0.05194 0.04535 -0.0463 1.0000 0.0732
-8.750 -0.8143 0.04631 0.03864 -0.0453 1.0000 0.0690
-8.500 -0.8006 0.04324 0.03535 -0.0447 1.0000 0.0697
-8.250 -0.7839 0.04118 0.03327 -0.0439 1.0000 0.0716
-8.000 -0.7663 0.03885 0.03067 -0.0434 1.0000 0.0730
-7.750 -0.7465 0.03643 0.02792 -0.0429 1.0000 0.0739
-7.500 -0.7251 0.03427 0.02544 -0.0423 1.0000 0.0752
-7.250 -0.7026 0.03246 0.02331 -0.0418 1.0000 0.0774
-7.000 -0.6794 0.03073 0.02133 -0.0413 1.0000 0.0811
-6.750 -0.6572 0.02932 0.01997 -0.0407 1.0000 0.0857
-6.500 -0.6337 0.02811 0.01862 -0.0399 1.0000 0.0908
-6.250 -0.6115 0.02671 0.01733 -0.0390 1.0000 0.0978
-6.000 -0.5880 0.02568 0.01625 -0.0384 1.0000 0.1081
-5.750 -0.5643 0.02470 0.01536 -0.0380 1.0000 0.1209
-5.500 -0.5398 0.02351 0.01442 -0.0381 1.0000 0.1399
-5.250 -0.5111 0.02225 0.01347 -0.0394 1.0000 0.1722
-5.000 -0.4644 0.01920 0.01286 -0.0458 1.0000 0.5129
-4.750 -0.4489 0.02014 0.01391 -0.0420 1.0000 0.5875
-4.500 -0.4330 0.02114 0.01483 -0.0385 1.0000 0.6193
-4.250 -0.4221 0.02229 0.01594 -0.0337 1.0000 0.6377
-4.000 -0.4099 0.02337 0.01696 -0.0292 1.0000 0.6537
-3.750 -0.3965 0.02435 0.01787 -0.0252 1.0000 0.6687
-3.500 -0.3828 0.02526 0.01871 -0.0214 1.0000 0.6833
-3.250 -0.3706 0.02619 0.01958 -0.0172 1.0000 0.6981
-3.000 -0.3596 0.02706 0.02041 -0.0126 1.0000 0.7131
-2.750 -0.3542 0.02784 0.02120 -0.0065 1.0000 0.7246
-2.500 -0.3445 0.02840 0.02173 -0.0018 1.0000 0.7385
-2.250 -0.3327 0.02875 0.02203 0.0021 1.0000 0.7526
-2.000 -0.3174 0.02889 0.02212 0.0048 1.0000 0.7660
-1.750 -0.2957 0.02887 0.02202 0.0053 1.0000 0.7783
-1.500 -0.2773 0.02874 0.02184 0.0067 1.0000 0.7867
-1.250 -0.2530 0.02858 0.02161 0.0062 1.0000 0.7954
-1.000 -0.2304 0.02850 0.02148 0.0063 1.0000 0.8045
-0.750 -0.2112 0.02836 0.02130 0.0073 1.0000 0.8129
-0.500 -0.1832 0.02841 0.02129 0.0058 1.0000 0.8228
-0.250 -0.1682 0.02822 0.02109 0.0079 1.0000 0.8305
0.000 -0.1409 0.02828 0.02112 0.0065 1.0000 0.8389
0.250 -0.1222 0.02820 0.02103 0.0074 1.0000 0.8463
0.500 -0.0969 0.02830 0.02112 0.0065 1.0000 0.8541
0.750 -0.0563 0.02862 0.02143 0.0032 0.9917 0.8618
1.000 -0.0108 0.02901 0.02181 -0.0013 0.9817 0.8690
1.250 0.0319 0.02933 0.02213 -0.0049 0.9721 0.8756
1.500 0.0751 0.02957 0.02239 -0.0089 0.9607 0.8820
1.750 0.1074 0.02952 0.02238 -0.0102 0.9486 0.8883
2.000 0.1489 0.02969 0.02260 -0.0137 0.9365 0.8943
2.250 0.1903 0.02955 0.02251 -0.0163 0.9220 0.8997
2.500 0.2462 0.02890 0.02192 -0.0205 0.9009 0.9058
2.750 0.3079 0.02767 0.02076 -0.0248 0.8778 0.9112
3.000 0.3489 0.02650 0.01968 -0.0257 0.8591 0.9168
3.250 0.3935 0.02546 0.01875 -0.0276 0.8439 0.9221
3.500 0.4361 0.02425 0.01767 -0.0288 0.8299 0.9271
3.750 0.4750 0.02292 0.01647 -0.0291 0.8132 0.9318
4.000 0.5184 0.02125 0.01494 -0.0297 0.7921 0.9359
4.250 0.5528 0.01966 0.01347 -0.0287 0.7609 0.9404
4.500 0.5786 0.01837 0.01225 -0.0264 0.7059 0.9461
4.750 0.6189 0.01840 0.01044 -0.0253 0.3854 0.9494
5.000 0.6264 0.01985 0.01096 -0.0223 0.2759 0.9538
5.250 0.6466 0.02076 0.01152 -0.0215 0.2372 0.9584
5.500 0.6708 0.02155 0.01210 -0.0214 0.2155 0.9631
5.750 0.6995 0.02229 0.01273 -0.0220 0.2008 0.9675
6.000 0.7316 0.02319 0.01354 -0.0232 0.1899 0.9716
6.250 0.7665 0.02422 0.01442 -0.0251 0.1809 0.9759
6.500 0.8020 0.02517 0.01550 -0.0269 0.1731 0.9805
7.000 0.8750 0.02753 0.01791 -0.0313 0.1590 0.9897
7.250 0.9077 0.02858 0.01911 -0.0327 0.1530 0.9985
7.500 0.9415 0.03035 0.02080 -0.0346 0.1483 1.0000
7.750 0.9665 0.03158 0.02238 -0.0347 0.1436 1.0000
8.000 0.9934 0.03278 0.02376 -0.0353 0.1377 1.0000
8.250 1.0248 0.03494 0.02584 -0.0371 0.1324 1.0000
8.500 1.0466 0.03663 0.02802 -0.0366 0.1291 1.0000
8.750 1.0692 0.03872 0.03052 -0.0365 0.1255 1.0000
9.000 1.0931 0.04091 0.03299 -0.0368 0.1221 1.0000
9.250 1.1203 0.04330 0.03540 -0.0379 0.1186 1.0000
9.500 1.1335 0.04661 0.03916 -0.0369 0.1157 1.0000
9.750 1.1397 0.04967 0.04282 -0.0349 0.1130 1.0000
10.000 1.1450 0.05301 0.04662 -0.0331 0.1104 1.0000
10.250 1.1542 0.05584 0.04973 -0.0320 0.1074 1.0000
10.500 1.1885 0.05847 0.05209 -0.0346 0.1031 1.0000
10.750 1.1771 0.06275 0.05688 -0.0315 0.1018 1.0000
11.000 1.1592 0.06697 0.06159 -0.0281 0.1011 1.0000
11.250 1.1375 0.07144 0.06641 -0.0250 0.1009 1.0000
11.500 1.1134 0.07633 0.07157 -0.0226 0.1011 1.0000
11.750 1.0892 0.08185 0.07732 -0.0215 0.1015 1.0000
12.000 1.0685 0.08804 0.08367 -0.0217 0.1021 1.0000
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Polar data table (+)
Polar graphs
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