lrn1007 (lrn1007-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: lrn1007 (lrn1007-il) Reynolds number: 500,000 Max Cl/Cd: 125.28 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lrn1007-il-500000.txt Download as CSV file: xf-lrn1007-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: lrn1007
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.6490 0.23992 0.23756 0.0363 1.0000 0.0010
-19.750 -0.6403 0.23694 0.23459 0.0342 1.0000 0.0010
-19.500 -0.6315 0.23391 0.23156 0.0321 1.0000 0.0010
-19.250 -0.6226 0.23092 0.22857 0.0300 1.0000 0.0010
-19.000 -0.6137 0.22792 0.22558 0.0279 1.0000 0.0010
-18.750 -0.6048 0.22490 0.22256 0.0258 1.0000 0.0010
-18.500 -0.5960 0.22186 0.21952 0.0237 1.0000 0.0010
-18.250 -0.5870 0.21876 0.21643 0.0216 1.0000 0.0010
-18.000 -0.5779 0.21568 0.21336 0.0195 1.0000 0.0010
-17.750 -0.5688 0.21257 0.21025 0.0174 1.0000 0.0010
-17.500 -0.5597 0.20944 0.20713 0.0153 1.0000 0.0010
-17.250 -0.5505 0.20647 0.20416 0.0132 0.9566 0.0010
-17.000 -0.5307 0.20185 0.19947 0.0074 0.9280 0.0010
-16.750 -0.5185 0.19832 0.19577 0.0043 0.9062 0.0009
-16.500 -0.5101 0.19528 0.19265 0.0026 0.8950 0.0009
-16.250 -0.5016 0.19222 0.18953 0.0009 0.8884 0.0009
-16.000 -0.4930 0.18914 0.18641 -0.0009 0.8836 0.0009
-15.750 -0.4845 0.18598 0.18322 -0.0027 0.8799 0.0009
-15.500 -0.4759 0.18289 0.18009 -0.0045 0.8770 0.0009
-15.250 -0.4671 0.17972 0.17691 -0.0063 0.8746 0.0009
-15.000 -0.4584 0.17656 0.17373 -0.0082 0.8725 0.0009
-14.750 -0.4498 0.17338 0.17053 -0.0100 0.8705 0.0009
-14.500 -0.4411 0.17020 0.16733 -0.0117 0.8688 0.0009
-14.250 -0.4326 0.16703 0.16414 -0.0135 0.8672 0.0009
-14.000 -0.4240 0.16386 0.16095 -0.0153 0.8658 0.0009
-13.750 -0.4154 0.16066 0.15774 -0.0170 0.8644 0.0009
-13.500 -0.4069 0.15746 0.15454 -0.0188 0.8633 0.0009
-13.250 -0.3982 0.15425 0.15133 -0.0206 0.8621 0.0010
-13.000 -0.3896 0.15108 0.14815 -0.0223 0.8610 0.0010
-12.750 -0.3811 0.14790 0.14496 -0.0241 0.8599 0.0010
-12.500 -0.3727 0.14473 0.14179 -0.0258 0.8589 0.0010
-12.250 -0.3642 0.14161 0.13866 -0.0275 0.8578 0.0010
-12.000 -0.3558 0.13842 0.13547 -0.0291 0.8569 0.0010
-11.750 -0.3474 0.13532 0.13237 -0.0308 0.8560 0.0010
-11.500 -0.3391 0.13229 0.12933 -0.0324 0.8550 0.0010
-11.250 -0.3308 0.12917 0.12621 -0.0340 0.8542 0.0010
-11.000 -0.3224 0.12622 0.12320 -0.0356 0.8534 0.0010
-10.750 -0.3143 0.12316 0.12013 -0.0372 0.8526 0.0010
-10.500 -0.3060 0.12020 0.11716 -0.0387 0.8518 0.0010
-10.250 -0.2976 0.11725 0.11423 -0.0403 0.8511 0.0010
-10.000 -0.2894 0.11433 0.11131 -0.0419 0.8504 0.0010
-9.750 -0.2811 0.11144 0.10844 -0.0434 0.8497 0.0010
-9.500 -0.2729 0.10861 0.10562 -0.0449 0.8490 0.0010
-9.250 -0.2648 0.10578 0.10280 -0.0464 0.8480 0.0010
-9.000 -0.2568 0.10303 0.10007 -0.0479 0.8470 0.0010
-8.750 -0.2489 0.10034 0.09739 -0.0493 0.8461 0.0010
-8.500 -0.2411 0.09763 0.09469 -0.0507 0.8453 0.0010
-8.250 -0.2335 0.09503 0.09210 -0.0521 0.8444 0.0010
-2.500 0.1953 0.03007 0.02601 -0.1008 0.8240 0.0040
-2.250 0.2214 0.02737 0.02318 -0.1017 0.8230 0.0045
-2.000 0.2499 0.02536 0.02102 -0.1022 0.8220 0.0050
-1.750 0.2790 0.02359 0.01907 -0.1023 0.8209 0.0056
-1.500 0.3082 0.02196 0.01725 -0.1022 0.8196 0.0062
-1.250 0.3373 0.02044 0.01554 -0.1019 0.8184 0.0066
-1.000 0.3665 0.01908 0.01400 -0.1016 0.8174 0.0072
-0.750 0.3957 0.01803 0.01276 -0.1010 0.8163 0.0081
-0.500 0.4250 0.01785 0.01240 -0.1002 0.8149 0.0092
-0.250 0.4508 0.01531 0.00964 -0.1001 0.8132 0.0150
1.250 0.6110 0.01111 0.00500 -0.0979 0.7942 0.0263
1.500 0.6377 0.01089 0.00472 -0.0976 0.7909 0.0206
1.750 0.6642 0.01046 0.00420 -0.0973 0.7881 0.0180
2.000 0.6907 0.01028 0.00400 -0.0972 0.7840 0.0160
2.250 0.7175 0.01015 0.00379 -0.0971 0.7795 0.0154
2.500 0.7447 0.01003 0.00361 -0.0970 0.7763 0.0178
2.750 0.7764 0.00822 0.00371 -0.0985 0.7738 1.0000
3.000 0.7993 0.00638 0.00158 -0.0956 0.7013 1.0000
3.250 0.8095 0.00759 0.00160 -0.0923 0.4685 1.0000
3.500 0.8016 0.01148 0.00312 -0.0876 0.0083 1.0000
3.750 0.8271 0.01171 0.00343 -0.0872 0.0068 1.0000
4.000 0.8528 0.01195 0.00389 -0.0866 0.0084 1.0000
4.250 0.8772 0.01240 0.00458 -0.0856 0.0105 1.0000
4.500 0.9007 0.01298 0.00534 -0.0844 0.0148 1.0000
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Polar data table (+)
Polar graphs
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