DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DSMA-523A AIRFOIL (dsma523a-il) Reynolds number: 100,000 Max Cl/Cd: 20.63 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dsma523a-il-100000.txt Download as CSV file: xf-dsma523a-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5525 0.09745 0.09177 -0.0173 1.0000 0.1934
-8.500 -0.7998 0.05822 0.05153 -0.0435 1.0000 0.1009
-8.250 -0.7920 0.05410 0.04732 -0.0433 1.0000 0.0995
-8.000 -0.7853 0.04948 0.04240 -0.0438 1.0000 0.0975
-7.750 -0.7752 0.04388 0.03620 -0.0452 1.0000 0.0944
-7.500 -0.7551 0.03880 0.03002 -0.0475 1.0000 0.0914
-7.250 -0.7323 0.03594 0.02687 -0.0478 1.0000 0.0915
-7.000 -0.7094 0.03362 0.02443 -0.0477 1.0000 0.0927
-6.750 -0.6860 0.03216 0.02298 -0.0473 1.0000 0.0952
-6.500 -0.6608 0.03056 0.02119 -0.0474 1.0000 0.0980
-6.250 -0.6344 0.02893 0.01928 -0.0473 1.0000 0.1001
-6.000 -0.6082 0.02745 0.01755 -0.0471 1.0000 0.1024
-5.750 -0.5848 0.02617 0.01642 -0.0464 1.0000 0.1064
-5.500 -0.5591 0.02522 0.01542 -0.0460 1.0000 0.1113
-5.250 -0.5335 0.02422 0.01431 -0.0453 1.0000 0.1154
-5.000 -0.5098 0.02325 0.01352 -0.0445 1.0000 0.1214
-4.750 -0.4836 0.02258 0.01279 -0.0441 1.0000 0.1287
-4.500 -0.4598 0.02168 0.01212 -0.0433 1.0000 0.1364
-4.250 -0.4339 0.02105 0.01154 -0.0428 1.0000 0.1472
-4.000 -0.4075 0.02040 0.01106 -0.0426 1.0000 0.1614
-3.750 -0.3802 0.01967 0.01063 -0.0426 1.0000 0.1857
-3.500 -0.3356 0.01738 0.01039 -0.0477 1.0000 0.4450
-3.250 -0.3594 0.01955 0.01331 -0.0321 1.0000 0.5366
-3.000 -0.3271 0.02090 0.01449 -0.0323 1.0000 0.6419
-2.750 -0.3027 0.02197 0.01542 -0.0307 1.0000 0.6725
-2.500 -0.2896 0.02291 0.01632 -0.0261 1.0000 0.6903
-2.250 -0.2819 0.02358 0.01699 -0.0202 1.0000 0.7013
-2.000 -0.2694 0.02408 0.01747 -0.0158 1.0000 0.7153
-1.750 -0.2548 0.02445 0.01781 -0.0121 1.0000 0.7305
-1.500 -0.2394 0.02475 0.01809 -0.0087 1.0000 0.7463
-1.250 -0.2261 0.02492 0.01825 -0.0049 1.0000 0.7600
-1.000 -0.2157 0.02488 0.01821 -0.0005 1.0000 0.7714
-0.750 -0.1997 0.02486 0.01818 0.0023 1.0000 0.7852
-0.500 -0.1850 0.02483 0.01816 0.0054 1.0000 0.8007
-0.250 -0.1775 0.02469 0.01805 0.0104 1.0000 0.8186
0.000 -0.1727 0.02440 0.01779 0.0160 1.0000 0.8377
0.250 -0.1660 0.02402 0.01745 0.0209 1.0000 0.8567
0.500 -0.1530 0.02366 0.01710 0.0239 1.0000 0.8713
0.750 -0.1335 0.02341 0.01688 0.0250 1.0000 0.8816
1.000 -0.1125 0.02321 0.01669 0.0257 1.0000 0.8893
1.250 -0.0887 0.02306 0.01659 0.0256 1.0000 0.8943
1.500 -0.0665 0.02294 0.01651 0.0259 1.0000 0.9000
1.750 -0.0455 0.02282 0.01645 0.0264 1.0000 0.9068
2.000 -0.0221 0.02287 0.01657 0.0262 1.0000 0.9139
2.250 0.0532 0.02317 0.01698 0.0179 0.9708 0.9242
2.500 0.1268 0.02234 0.01628 0.0107 0.9355 0.9274
2.750 0.1926 0.02117 0.01526 0.0054 0.9023 0.9281
3.000 0.2356 0.01973 0.01399 0.0047 0.8547 0.9286
3.250 0.3513 0.02102 0.01197 -0.0061 0.2014 0.9301
3.500 0.3726 0.02167 0.01239 -0.0053 0.1741 0.9308
3.750 0.3968 0.02232 0.01291 -0.0050 0.1581 0.9314
4.000 0.4247 0.02316 0.01356 -0.0054 0.1460 0.9314
4.250 0.4546 0.02385 0.01425 -0.0061 0.1374 0.9317
4.500 0.4874 0.02508 0.01529 -0.0075 0.1296 0.9324
4.750 0.5176 0.02577 0.01611 -0.0080 0.1236 0.9326
5.000 0.5498 0.02682 0.01721 -0.0091 0.1190 0.9324
5.250 0.5830 0.02843 0.01872 -0.0107 0.1142 0.9323
5.500 0.6121 0.02967 0.02021 -0.0111 0.1106 0.9322
5.750 0.6408 0.03109 0.02192 -0.0115 0.1081 0.9321
6.000 0.6675 0.03265 0.02375 -0.0114 0.1060 0.9326
6.250 0.6928 0.03413 0.02543 -0.0114 0.1032 0.9333
6.500 0.7193 0.03582 0.02716 -0.0118 0.1004 0.9335
6.750 0.7433 0.03821 0.02985 -0.0117 0.0998 0.9334
7.000 0.7604 0.04118 0.03349 -0.0103 0.1015 0.9333
7.250 0.7702 0.04587 0.03896 -0.0083 0.1064 0.9331
7.500 0.7827 0.04999 0.04346 -0.0074 0.1092 0.9331
7.750 0.7982 0.05437 0.04803 -0.0074 0.1117 0.9331
8.000 0.7130 0.07658 0.07221 -0.0103 0.2033 0.9326
8.250 0.7011 0.08029 0.07604 -0.0121 0.1943 0.9326
8.500 0.7448 0.08295 0.07861 -0.0108 0.1894 0.9332
8.750 0.6919 0.09017 0.08597 -0.0170 0.1829 0.9334
9.000 0.6774 0.09616 0.09197 -0.0241 0.1748 0.9337
9.250 0.7047 0.09802 0.09385 -0.0212 0.1704 0.9341
9.500 0.7576 0.10164 0.09737 -0.0150 0.1669 0.9345
9.750 0.6742 0.11102 0.10681 -0.0348 0.1585 0.9337
10.000 0.6850 0.11455 0.11034 -0.0360 0.1535 0.9338
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