DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DSMA-523A AIRFOIL (dsma523a-il) Reynolds number: 50,000 Max Cl/Cd: 20.8 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dsma523a-il-50000.txt Download as CSV file: xf-dsma523a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DSMA-523A 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5195 0.11590 0.10784 -0.0009 1.0000 0.3695
-8.500 -0.4728 0.10934 0.10119 -0.0002 1.0000 0.3782
-8.250 -0.6982 0.07900 0.07107 -0.0327 1.0000 0.1815
-8.000 -0.6783 0.07501 0.06713 -0.0308 1.0000 0.1764
-7.750 -0.7374 0.06403 0.05552 -0.0390 1.0000 0.1622
-7.500 -0.7290 0.05949 0.05089 -0.0391 1.0000 0.1598
-7.250 -0.7221 0.05467 0.04578 -0.0403 1.0000 0.1571
-7.000 -0.7100 0.05016 0.04088 -0.0419 1.0000 0.1559
-6.750 -0.6923 0.04635 0.03665 -0.0433 1.0000 0.1573
-6.500 -0.6704 0.04291 0.03274 -0.0448 1.0000 0.1593
-6.250 -0.6451 0.03979 0.02914 -0.0460 1.0000 0.1610
-6.000 -0.6184 0.03708 0.02600 -0.0470 1.0000 0.1643
-5.750 -0.5956 0.03504 0.02404 -0.0464 1.0000 0.1704
-5.500 -0.5696 0.03323 0.02203 -0.0462 1.0000 0.1769
-5.250 -0.5433 0.03146 0.02001 -0.0459 1.0000 0.1842
-5.000 -0.5207 0.03012 0.01879 -0.0445 1.0000 0.1943
-4.750 -0.4980 0.02889 0.01752 -0.0427 1.0000 0.2052
-4.500 -0.4767 0.02794 0.01662 -0.0406 1.0000 0.2203
-4.250 -0.4575 0.02698 0.01587 -0.0379 1.0000 0.2392
-4.000 -0.4381 0.02590 0.01511 -0.0354 1.0000 0.2674
-3.750 -0.4170 0.02392 0.01416 -0.0342 1.0000 0.3499
-3.500 -0.4346 0.02524 0.01737 -0.0184 1.0000 0.5054
-3.250 -0.4242 0.02943 0.02137 -0.0089 1.0000 0.6617
-3.000 -0.4143 0.03122 0.02297 -0.0020 1.0000 0.7082
-2.750 -0.4102 0.03219 0.02386 0.0068 1.0000 0.7396
-2.500 -0.4027 0.03249 0.02406 0.0139 1.0000 0.7705
-2.250 -0.3930 0.03235 0.02382 0.0197 1.0000 0.8020
-2.000 -0.3817 0.03191 0.02327 0.0253 1.0000 0.8352
-1.750 -0.3615 0.03112 0.02234 0.0292 1.0000 0.8698
-1.500 -0.3238 0.03014 0.02119 0.0292 1.0000 0.9061
-1.250 -0.0377 0.02752 0.01784 -0.0171 1.0000 1.0000
-1.000 -0.0275 0.02712 0.01744 -0.0152 1.0000 1.0000
-0.750 -0.0174 0.02676 0.01709 -0.0132 1.0000 1.0000
-0.500 -0.0073 0.02645 0.01679 -0.0112 1.0000 1.0000
-0.250 0.0026 0.02617 0.01654 -0.0090 1.0000 1.0000
0.000 0.0124 0.02591 0.01633 -0.0069 1.0000 1.0000
0.250 0.0220 0.02569 0.01615 -0.0046 1.0000 1.0000
0.500 0.0313 0.02550 0.01602 -0.0024 1.0000 1.0000
0.750 0.0403 0.02533 0.01592 0.0000 1.0000 1.0000
1.000 0.0489 0.02519 0.01585 0.0024 1.0000 1.0000
1.250 0.0570 0.02507 0.01582 0.0048 1.0000 1.0000
1.500 0.0647 0.02498 0.01582 0.0073 1.0000 1.0000
1.750 0.0718 0.02491 0.01586 0.0098 1.0000 1.0000
2.000 0.0782 0.02487 0.01593 0.0124 1.0000 1.0000
2.250 0.0840 0.02485 0.01605 0.0150 1.0000 1.0000
2.500 0.0890 0.02487 0.01620 0.0176 1.0000 1.0000
2.750 0.0932 0.02493 0.01641 0.0201 1.0000 1.0000
3.000 0.0967 0.02504 0.01668 0.0226 1.0000 1.0000
3.250 0.0996 0.02523 0.01704 0.0249 1.0000 1.0000
3.500 0.5648 0.02759 0.01636 -0.0387 0.2180 1.0000
3.750 0.5989 0.02893 0.01758 -0.0398 0.2044 1.0000
4.000 0.6239 0.02999 0.01878 -0.0392 0.1937 1.0000
4.250 0.6515 0.03174 0.02047 -0.0394 0.1868 1.0000
4.500 0.6715 0.03302 0.02215 -0.0377 0.1820 1.0000
4.750 0.6900 0.03441 0.02380 -0.0361 0.1763 1.0000
5.000 0.7084 0.03600 0.02551 -0.0345 0.1720 1.0000
5.250 0.7251 0.03793 0.02766 -0.0327 0.1700 1.0000
5.500 0.7394 0.04021 0.03012 -0.0307 0.1682 1.0000
5.750 0.7487 0.04247 0.03266 -0.0279 0.1667 1.0000
6.000 0.7539 0.04438 0.03498 -0.0243 0.1657 1.0000
6.250 0.7580 0.04659 0.03752 -0.0208 0.1654 1.0000
6.500 0.7627 0.04922 0.04038 -0.0177 0.1663 1.0000
6.750 0.7649 0.05161 0.04308 -0.0141 0.1683 1.0000
7.000 0.7354 0.05436 0.04669 -0.0067 0.1765 1.0000
7.250 0.7293 0.05778 0.05040 -0.0036 0.1814 1.0000
7.500 0.7363 0.06171 0.05444 -0.0024 0.1852 1.0000
7.750 0.6873 0.06982 0.06344 -0.0026 0.2203 1.0000
8.000 0.5556 0.09596 0.09009 -0.0393 0.4468 1.0000
8.250 0.5572 0.09874 0.09285 -0.0395 0.4261 1.0000
8.500 0.5562 0.10163 0.09571 -0.0401 0.4067 1.0000
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