DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 100,000 Max Cl/Cd: 27.86 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523b-il-100000-n5.txt Download as CSV file: xf-dsma523b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DSMA-523B 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7187 0.09047 0.08410 -0.0407 1.0000 0.0453
-11.750 -0.7593 0.07974 0.07322 -0.0474 1.0000 0.0450
-11.500 -0.7942 0.07248 0.06580 -0.0506 1.0000 0.0448
-11.250 -0.8254 0.06715 0.06033 -0.0513 1.0000 0.0447
-11.000 -0.8545 0.06320 0.05623 -0.0500 1.0000 0.0446
-10.750 -0.8759 0.05879 0.05160 -0.0501 1.0000 0.0446
-10.500 -0.8869 0.05410 0.04653 -0.0519 1.0000 0.0449
-10.250 -0.8892 0.04961 0.04150 -0.0537 1.0000 0.0454
-10.000 -0.8736 0.04792 0.03981 -0.0535 1.0000 0.0461
-9.750 -0.8585 0.04589 0.03765 -0.0538 1.0000 0.0470
-9.500 -0.8424 0.04350 0.03500 -0.0546 1.0000 0.0481
-9.250 -0.8240 0.04092 0.03206 -0.0557 1.0000 0.0492
-9.000 -0.8029 0.03839 0.02909 -0.0568 1.0000 0.0503
-8.750 -0.7797 0.03623 0.02652 -0.0577 1.0000 0.0512
-8.500 -0.7575 0.03473 0.02499 -0.0576 1.0000 0.0522
-8.250 -0.7342 0.03333 0.02350 -0.0576 1.0000 0.0534
-8.000 -0.7095 0.03200 0.02196 -0.0579 1.0000 0.0555
-7.750 -0.6839 0.03070 0.02039 -0.0583 1.0000 0.0575
-7.500 -0.6609 0.02954 0.01928 -0.0578 1.0000 0.0593
-7.250 -0.6368 0.02848 0.01817 -0.0575 1.0000 0.0611
-7.000 -0.6116 0.02753 0.01707 -0.0573 1.0000 0.0631
-6.750 -0.5881 0.02652 0.01617 -0.0568 1.0000 0.0655
-6.500 -0.5630 0.02568 0.01536 -0.0567 1.0000 0.0684
-6.250 -0.5371 0.02488 0.01456 -0.0566 1.0000 0.0711
-6.000 -0.5101 0.02409 0.01388 -0.0570 1.0000 0.0738
-5.750 -0.4818 0.02345 0.01326 -0.0576 1.0000 0.0777
-5.500 -0.4524 0.02284 0.01276 -0.0586 1.0000 0.0820
-5.000 -0.3928 0.02193 0.01193 -0.0604 1.0000 0.0931
-4.750 -0.3626 0.02153 0.01160 -0.0613 1.0000 0.1010
-4.500 -0.3321 0.02117 0.01131 -0.0622 1.0000 0.1123
-4.250 -0.3009 0.02077 0.01109 -0.0633 1.0000 0.1317
-4.000 -0.2685 0.02035 0.01092 -0.0648 1.0000 0.1686
-3.750 -0.2320 0.01980 0.01076 -0.0674 1.0000 0.2358
-3.500 -0.1867 0.01899 0.01062 -0.0725 1.0000 0.3582
-3.250 -0.1649 0.01907 0.01146 -0.0706 1.0000 0.4763
-3.000 -0.1692 0.02019 0.01299 -0.0613 1.0000 0.5287
-2.500 -0.1101 0.02084 0.01355 -0.0621 1.0000 0.6128
-2.250 -0.0798 0.02117 0.01381 -0.0628 1.0000 0.6342
-2.000 -0.0508 0.02153 0.01412 -0.0631 1.0000 0.6509
-1.750 -0.0260 0.02197 0.01454 -0.0622 1.0000 0.6647
-1.500 -0.0094 0.02249 0.01511 -0.0592 1.0000 0.6755
-1.250 0.0113 0.02300 0.01564 -0.0572 1.0000 0.6898
-1.000 0.0341 0.02347 0.01614 -0.0559 1.0000 0.7042
-0.750 0.0465 0.02380 0.01656 -0.0519 1.0000 0.7112
-0.500 0.0704 0.02404 0.01684 -0.0511 1.0000 0.7191
-0.250 0.0971 0.02425 0.01708 -0.0511 1.0000 0.7261
0.000 0.1155 0.02444 0.01736 -0.0490 1.0000 0.7312
0.250 0.1667 0.02454 0.01750 -0.0535 0.9897 0.7398
0.500 0.2367 0.02400 0.01703 -0.0608 0.9669 0.7468
0.750 0.2734 0.02289 0.01601 -0.0612 0.9337 0.7513
1.000 0.3219 0.02184 0.01503 -0.0641 0.8998 0.7547
1.250 0.3452 0.02150 0.01478 -0.0628 0.8511 0.7571
1.500 0.4748 0.02198 0.01248 -0.0809 0.2836 0.7576
1.750 0.5056 0.02291 0.01275 -0.0821 0.1711 0.7600
2.000 0.5377 0.02356 0.01309 -0.0835 0.1316 0.7618
2.250 0.5636 0.02396 0.01338 -0.0832 0.1154 0.7629
2.500 0.5889 0.02436 0.01375 -0.0826 0.1057 0.7644
2.750 0.6144 0.02484 0.01418 -0.0821 0.0985 0.7660
3.000 0.6411 0.02536 0.01468 -0.0820 0.0925 0.7673
3.250 0.6688 0.02586 0.01518 -0.0821 0.0870 0.7684
3.500 0.6956 0.02658 0.01584 -0.0820 0.0832 0.7699
3.750 0.7239 0.02728 0.01657 -0.0822 0.0798 0.7715
4.000 0.7532 0.02793 0.01726 -0.0826 0.0759 0.7729
4.250 0.7825 0.02865 0.01795 -0.0832 0.0725 0.7738
4.500 0.8124 0.02975 0.01895 -0.0839 0.0702 0.7748
4.750 0.8432 0.03062 0.01998 -0.0845 0.0679 0.7757
5.000 0.8733 0.03152 0.02100 -0.0851 0.0650 0.7766
5.250 0.9028 0.03240 0.02193 -0.0857 0.0625 0.7776
5.500 0.9325 0.03354 0.02304 -0.0865 0.0608 0.7788
5.750 0.9627 0.03501 0.02467 -0.0871 0.0593 0.7802
6.000 0.9889 0.03638 0.02637 -0.0868 0.0574 0.7812
6.250 1.0138 0.03763 0.02784 -0.0863 0.0554 0.7820
6.500 1.0383 0.03879 0.02914 -0.0860 0.0537 0.7827
6.750 1.0624 0.04008 0.03053 -0.0856 0.0526 0.7835
7.000 1.0858 0.04173 0.03229 -0.0853 0.0517 0.7842
7.250 1.1046 0.04415 0.03520 -0.0839 0.0508 0.7850
7.500 1.1201 0.04695 0.03851 -0.0821 0.0500 0.7857
7.750 1.1323 0.05003 0.04210 -0.0800 0.0492 0.7865
8.000 1.1417 0.05317 0.04570 -0.0778 0.0483 0.7873
8.250 1.1490 0.05625 0.04918 -0.0754 0.0474 0.7881
8.500 1.1562 0.05893 0.05215 -0.0733 0.0464 0.7892
8.750 1.1633 0.06138 0.05482 -0.0713 0.0457 0.7903
9.000 1.1681 0.06399 0.05763 -0.0692 0.0452 0.7915
9.250 1.1690 0.06694 0.06079 -0.0669 0.0449 0.7925
9.500 1.1613 0.07052 0.06464 -0.0640 0.0447 0.7932
9.750 1.1423 0.07441 0.06879 -0.0602 0.0446 0.7938
10.000 1.1132 0.07932 0.07401 -0.0567 0.0446 0.7942
10.250 0.9511 0.11459 0.11013 -0.0761 0.0468 0.7933
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