DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il) Reynolds number: 50,000 Max Cl/Cd: 26.66 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dfvlrr4-il-50000.txt Download as CSV file: xf-dfvlrr4-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5442 0.10327 0.09587 -0.0394 1.0000 0.2000
-10.000 -0.6164 0.08604 0.07883 -0.0507 1.0000 0.1549
-9.750 -0.6425 0.08071 0.07353 -0.0508 1.0000 0.1485
-9.500 -0.6813 0.07611 0.06899 -0.0493 1.0000 0.1437
-9.250 -0.7492 0.07037 0.06292 -0.0491 1.0000 0.1352
-9.000 -0.7557 0.06627 0.05870 -0.0479 1.0000 0.1336
-8.750 -0.7628 0.06218 0.05439 -0.0468 1.0000 0.1323
-8.500 -0.7656 0.05811 0.05000 -0.0460 1.0000 0.1313
-8.250 -0.7628 0.05414 0.04564 -0.0455 1.0000 0.1309
-8.000 -0.7535 0.05039 0.04146 -0.0452 1.0000 0.1307
-7.750 -0.7392 0.04685 0.03747 -0.0450 1.0000 0.1308
-7.500 -0.7212 0.04369 0.03385 -0.0448 1.0000 0.1323
-7.250 -0.7003 0.04110 0.03061 -0.0448 1.0000 0.1364
-7.000 -0.6799 0.03847 0.02803 -0.0439 1.0000 0.1423
-6.750 -0.6571 0.03638 0.02568 -0.0430 1.0000 0.1488
-6.500 -0.6351 0.03443 0.02366 -0.0419 1.0000 0.1586
-6.250 -0.6133 0.03280 0.02200 -0.0403 1.0000 0.1720
-6.000 -0.5928 0.03138 0.02070 -0.0382 1.0000 0.1896
-5.750 -0.5728 0.03005 0.01952 -0.0361 1.0000 0.2143
-5.500 -0.5536 0.02846 0.01833 -0.0343 1.0000 0.2503
-5.250 -0.5327 0.02566 0.01721 -0.0342 1.0000 0.3800
-5.000 -0.5392 0.02865 0.02133 -0.0202 1.0000 0.5768
-4.750 -0.5371 0.03238 0.02490 -0.0087 1.0000 0.6307
-4.500 -0.5295 0.03495 0.02726 -0.0002 1.0000 0.6672
-4.250 -0.5206 0.03692 0.02906 0.0077 1.0000 0.6968
-4.000 -0.5096 0.03843 0.03040 0.0154 1.0000 0.7229
-3.750 -0.4959 0.03907 0.03086 0.0208 1.0000 0.7494
-3.500 -0.4825 0.03930 0.03093 0.0254 1.0000 0.7778
-3.250 -0.4574 0.03984 0.03130 0.0308 1.0000 0.8187
-3.000 -0.4114 0.03970 0.03087 0.0311 1.0000 0.8659
-2.750 -0.3621 0.03868 0.02959 0.0271 1.0000 0.8873
-2.500 -0.3405 0.03762 0.02837 0.0266 1.0000 0.9005
-2.250 -0.3248 0.03661 0.02724 0.0271 1.0000 0.9123
-2.000 -0.3064 0.03567 0.02618 0.0270 1.0000 0.9234
-1.750 -0.2688 0.03483 0.02518 0.0234 1.0000 0.9339
-1.500 -0.2362 0.03408 0.02430 0.0207 1.0000 0.9444
-1.250 -0.2018 0.03342 0.02353 0.0176 1.0000 0.9551
-1.000 -0.1658 0.03287 0.02287 0.0141 1.0000 0.9654
-0.750 -0.1289 0.03242 0.02234 0.0104 1.0000 0.9751
-0.500 -0.0868 0.03209 0.02193 0.0056 1.0000 0.9842
-0.250 -0.0446 0.03185 0.02164 0.0008 1.0000 0.9928
0.000 -0.0108 0.03167 0.02145 -0.0026 1.0000 1.0000
0.250 -0.0082 0.03139 0.02118 -0.0001 1.0000 1.0000
0.500 -0.0057 0.03113 0.02093 0.0024 1.0000 1.0000
0.750 -0.0033 0.03088 0.02070 0.0049 1.0000 1.0000
1.000 -0.0011 0.03065 0.02049 0.0074 1.0000 1.0000
1.250 0.0011 0.03044 0.02031 0.0099 1.0000 1.0000
1.500 0.0034 0.03024 0.02015 0.0123 1.0000 1.0000
1.750 0.0060 0.03008 0.02003 0.0146 1.0000 1.0000
2.000 0.0092 0.02996 0.01995 0.0167 1.0000 1.0000
2.250 0.0153 0.02995 0.02000 0.0183 1.0000 1.0000
2.500 0.0265 0.03014 0.02025 0.0188 1.0000 1.0000
2.750 0.0422 0.03054 0.02071 0.0184 1.0000 1.0000
3.000 0.0609 0.03112 0.02138 0.0173 1.0000 1.0000
3.250 0.0815 0.03188 0.02223 0.0158 1.0000 1.0000
3.500 0.1031 0.03281 0.02326 0.0139 1.0000 1.0000
3.750 0.1755 0.03509 0.02571 0.0031 0.9750 1.0000
4.000 0.2711 0.03655 0.02741 -0.0095 0.9243 1.0000
4.250 0.3585 0.03625 0.02738 -0.0182 0.8750 1.0000
4.500 0.4452 0.03449 0.02596 -0.0247 0.8319 1.0000
4.750 0.5102 0.03200 0.02384 -0.0268 0.7896 1.0000
5.000 0.5724 0.02807 0.02033 -0.0262 0.7347 1.0000
5.250 0.6627 0.02486 0.01491 -0.0248 0.3923 1.0000
5.500 0.6887 0.02648 0.01595 -0.0246 0.3327 1.0000
5.750 0.7336 0.02803 0.01723 -0.0277 0.2975 1.0000
6.000 0.7758 0.02956 0.01856 -0.0304 0.2751 1.0000
6.250 0.8104 0.03105 0.02001 -0.0319 0.2589 1.0000
6.500 0.8422 0.03263 0.02174 -0.0330 0.2479 1.0000
6.750 0.8726 0.03450 0.02380 -0.0339 0.2399 1.0000
7.000 0.9011 0.03632 0.02576 -0.0345 0.2313 1.0000
7.250 0.9263 0.03840 0.02812 -0.0348 0.2240 1.0000
7.500 0.9505 0.04053 0.03056 -0.0349 0.2176 1.0000
7.750 0.9773 0.04300 0.03311 -0.0356 0.2109 1.0000
8.000 0.9927 0.04566 0.03635 -0.0346 0.2069 1.0000
8.250 1.0085 0.04866 0.03981 -0.0340 0.2036 1.0000
8.500 1.0301 0.05149 0.04283 -0.0342 0.1982 1.0000
8.750 1.0429 0.05503 0.04669 -0.0335 0.1941 1.0000
9.000 1.0426 0.05896 0.05118 -0.0317 0.1924 1.0000
9.250 1.0383 0.06326 0.05596 -0.0299 0.1911 1.0000
9.500 1.0289 0.06801 0.06111 -0.0283 0.1908 1.0000
9.750 1.0149 0.07327 0.06670 -0.0270 0.1920 1.0000
10.000 1.0040 0.07889 0.07254 -0.0265 0.1941 1.0000
10.250 0.8729 0.09444 0.08843 -0.0313 0.2167 1.0000
10.500 0.9098 0.09680 0.09088 -0.0300 0.2127 1.0000
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Polar data table (+)
Polar graphs
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