RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5215 AIRFOIL (rae5215-il) Reynolds number: 100,000 Max Cl/Cd: 37.97 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5215-il-100000.txt Download as CSV file: xf-rae5215-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5215 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5424 0.09648 0.09135 -0.0145 1.0000 0.1264
-8.500 -0.5347 0.09342 0.08831 -0.0145 1.0000 0.1321
-8.250 -0.5757 0.08654 0.08157 -0.0285 1.0000 0.1374
-8.000 -0.5471 0.08445 0.07950 -0.0204 1.0000 0.1423
-7.750 -0.5434 0.08127 0.07635 -0.0210 1.0000 0.1487
-7.500 -0.5718 0.07306 0.06815 -0.0338 1.0000 0.1565
-7.250 -0.5489 0.07163 0.06680 -0.0288 1.0000 0.1632
-7.000 -0.5585 0.06622 0.06134 -0.0340 1.0000 0.1746
-6.750 -0.5623 0.06232 0.05733 -0.0369 1.0000 0.1896
-6.500 -0.5434 0.06031 0.05547 -0.0332 1.0000 0.1978
-6.250 -0.5374 0.05752 0.05271 -0.0325 1.0000 0.2147
-6.000 -0.5194 0.03840 0.03057 -0.0456 1.0000 0.0834
-5.750 -0.4995 0.03495 0.02708 -0.0449 1.0000 0.0812
-5.500 -0.4783 0.03164 0.02345 -0.0442 1.0000 0.0774
-5.250 -0.4541 0.02881 0.01985 -0.0432 1.0000 0.0737
-5.000 -0.4318 0.02684 0.01776 -0.0423 1.0000 0.0748
-4.750 -0.4095 0.02540 0.01624 -0.0414 1.0000 0.0779
-4.500 -0.3857 0.02395 0.01458 -0.0404 1.0000 0.0799
-4.250 -0.3616 0.02286 0.01324 -0.0394 1.0000 0.0828
-4.000 -0.3382 0.02135 0.01186 -0.0387 1.0000 0.0869
-3.750 -0.3141 0.02033 0.01084 -0.0378 1.0000 0.0907
-3.500 -0.2898 0.01936 0.00990 -0.0371 1.0000 0.0968
-3.250 -0.2652 0.01850 0.00918 -0.0366 1.0000 0.1049
-3.000 -0.2396 0.01760 0.00841 -0.0363 1.0000 0.1169
-2.750 -0.2106 0.01648 0.00752 -0.0369 1.0000 0.1550
-2.500 -0.1871 0.01493 0.00828 -0.0356 1.0000 0.6497
-2.250 -0.1693 0.01544 0.00878 -0.0325 1.0000 0.6947
-2.000 -0.1549 0.01584 0.00926 -0.0285 1.0000 0.7316
-1.750 -0.1442 0.01616 0.00967 -0.0236 1.0000 0.7684
-1.500 -0.1365 0.01631 0.00993 -0.0181 1.0000 0.8047
-1.250 -0.1282 0.01629 0.00995 -0.0129 1.0000 0.8364
-1.000 -0.1141 0.01617 0.00982 -0.0098 1.0000 0.8584
-0.750 -0.0920 0.01605 0.00965 -0.0090 1.0000 0.8708
-0.500 -0.0666 0.01600 0.00954 -0.0093 1.0000 0.8822
-0.250 -0.0441 0.01592 0.00944 -0.0087 1.0000 0.8935
0.000 -0.0204 0.01589 0.00939 -0.0086 1.0000 0.9054
0.250 0.0035 0.01589 0.00939 -0.0085 1.0000 0.9188
0.500 0.0272 0.01591 0.00942 -0.0084 1.0000 0.9344
0.750 0.0526 0.01596 0.00951 -0.0089 1.0000 0.9544
1.000 0.0923 0.01613 0.00972 -0.0126 0.9945 0.9881
1.250 0.2033 0.01612 0.00971 -0.0275 0.9565 0.9794
1.500 0.2635 0.01585 0.00951 -0.0333 0.9369 1.0000
1.750 0.3265 0.01540 0.00916 -0.0393 0.9182 1.0000
2.000 0.3863 0.01462 0.00849 -0.0436 0.8957 1.0000
2.250 0.4239 0.01393 0.00788 -0.0439 0.8643 1.0000
2.500 0.4553 0.01317 0.00717 -0.0424 0.8163 1.0000
2.750 0.4780 0.01259 0.00606 -0.0381 0.6222 1.0000
3.000 0.4887 0.01508 0.00637 -0.0351 0.2971 1.0000
3.250 0.5156 0.01620 0.00701 -0.0356 0.2556 1.0000
3.500 0.5449 0.01705 0.00766 -0.0364 0.2327 1.0000
3.750 0.5745 0.01794 0.00834 -0.0371 0.2162 1.0000
4.000 0.6039 0.01892 0.00909 -0.0378 0.2024 1.0000
4.250 0.6337 0.01970 0.00984 -0.0383 0.1902 1.0000
4.500 0.6631 0.02073 0.01083 -0.0388 0.1798 1.0000
4.750 0.6920 0.02187 0.01178 -0.0392 0.1698 1.0000
5.000 0.7208 0.02288 0.01292 -0.0394 0.1606 1.0000
5.250 0.7490 0.02432 0.01421 -0.0397 0.1518 1.0000
5.500 0.7765 0.02527 0.01536 -0.0396 0.1429 1.0000
5.750 0.8033 0.02685 0.01689 -0.0397 0.1352 1.0000
6.000 0.8296 0.02796 0.01822 -0.0394 0.1270 1.0000
6.250 0.8551 0.02981 0.02007 -0.0393 0.1204 1.0000
6.500 0.8796 0.03130 0.02193 -0.0387 0.1138 1.0000
6.750 0.9047 0.03301 0.02352 -0.0387 0.1083 1.0000
7.000 0.9255 0.03547 0.02656 -0.0376 0.1039 1.0000
7.250 0.9464 0.03769 0.02913 -0.0367 0.0998 1.0000
7.500 0.9706 0.03927 0.03056 -0.0367 0.0960 1.0000
7.750 0.9859 0.04281 0.03457 -0.0355 0.0938 1.0000
8.000 0.9978 0.04681 0.03914 -0.0339 0.0930 1.0000
8.250 1.0060 0.05129 0.04412 -0.0324 0.0927 1.0000
8.500 1.0100 0.05612 0.04941 -0.0309 0.0928 1.0000
8.750 1.0111 0.06115 0.05480 -0.0297 0.0931 1.0000
9.000 1.0131 0.06610 0.05998 -0.0288 0.0939 1.0000
9.250 0.8294 0.10314 0.09817 -0.0502 0.1632 1.0000
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Polar data table (+)
Polar graphs
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