DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 200,000 Max Cl/Cd: 39.29 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523b-il-200000-n5.txt Download as CSV file: xf-dsma523b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9065 0.07120 0.06603 -0.0523 1.0000 0.0302
-13.250 -0.9414 0.06353 0.05811 -0.0558 1.0000 0.0302
-13.000 -0.9694 0.05782 0.05214 -0.0571 1.0000 0.0303
-12.750 -0.9937 0.05322 0.04728 -0.0569 1.0000 0.0304
-12.500 -1.0153 0.04952 0.04334 -0.0555 1.0000 0.0305
-12.250 -1.0314 0.04692 0.04057 -0.0530 1.0000 0.0307
-12.000 -1.0312 0.04493 0.03850 -0.0520 1.0000 0.0309
-11.750 -1.0248 0.04311 0.03660 -0.0517 1.0000 0.0311
-11.500 -1.0145 0.04148 0.03489 -0.0519 1.0000 0.0315
-11.250 -1.0017 0.03981 0.03312 -0.0524 1.0000 0.0318
-11.000 -0.9866 0.03815 0.03132 -0.0531 1.0000 0.0323
-10.750 -0.9701 0.03644 0.02943 -0.0536 1.0000 0.0329
-10.500 -0.9522 0.03467 0.02746 -0.0541 1.0000 0.0335
-10.250 -0.9330 0.03284 0.02539 -0.0545 1.0000 0.0342
-10.000 -0.9125 0.03103 0.02330 -0.0548 1.0000 0.0350
-9.750 -0.8904 0.02980 0.02197 -0.0550 1.0000 0.0355
-9.500 -0.8670 0.02898 0.02111 -0.0554 1.0000 0.0360
-9.250 -0.8429 0.02817 0.02025 -0.0557 1.0000 0.0366
-9.000 -0.8182 0.02742 0.01943 -0.0561 1.0000 0.0375
-8.750 -0.7932 0.02660 0.01848 -0.0564 1.0000 0.0387
-8.500 -0.7680 0.02564 0.01734 -0.0565 1.0000 0.0402
-8.250 -0.7422 0.02508 0.01680 -0.0569 1.0000 0.0409
-8.000 -0.7159 0.02452 0.01622 -0.0573 1.0000 0.0419
-7.750 -0.6895 0.02390 0.01553 -0.0576 1.0000 0.0432
-7.500 -0.6626 0.02325 0.01478 -0.0579 1.0000 0.0448
-7.250 -0.6355 0.02270 0.01421 -0.0583 1.0000 0.0462
-7.000 -0.6079 0.02224 0.01376 -0.0588 1.0000 0.0478
-6.750 -0.5798 0.02182 0.01324 -0.0593 1.0000 0.0501
-6.500 -0.5517 0.02131 0.01273 -0.0598 1.0000 0.0520
-6.250 -0.5231 0.02080 0.01226 -0.0604 1.0000 0.0540
-6.000 -0.4941 0.02042 0.01181 -0.0611 1.0000 0.0565
-5.750 -0.4636 0.01984 0.01131 -0.0622 1.0000 0.0590
-5.500 -0.4326 0.01938 0.01087 -0.0634 1.0000 0.0620
-5.250 -0.4001 0.01891 0.01041 -0.0650 1.0000 0.0646
-5.000 -0.3658 0.01842 0.00997 -0.0671 1.0000 0.0678
-4.750 -0.3326 0.01809 0.00965 -0.0687 1.0000 0.0711
-4.250 -0.2651 0.01750 0.00917 -0.0722 1.0000 0.0793
-4.000 -0.2317 0.01728 0.00907 -0.0739 1.0000 0.0865
-3.750 -0.1980 0.01708 0.00901 -0.0756 1.0000 0.1059
-3.500 -0.1624 0.01684 0.00895 -0.0777 1.0000 0.1375
-3.250 -0.1253 0.01658 0.00893 -0.0802 1.0000 0.1810
-3.000 -0.0868 0.01632 0.00893 -0.0831 1.0000 0.2356
-2.750 -0.0401 0.01585 0.00894 -0.0881 1.0000 0.3372
-2.500 0.0048 0.01551 0.00911 -0.0924 1.0000 0.4470
-2.250 0.0245 0.01589 0.01007 -0.0901 1.0000 0.5394
-1.750 0.0637 0.01678 0.01116 -0.0857 1.0000 0.6038
-1.500 0.0933 0.01699 0.01136 -0.0863 1.0000 0.6211
-1.250 0.1355 0.01719 0.01156 -0.0890 0.9954 0.6404
-1.000 0.1917 0.01737 0.01176 -0.0937 0.9829 0.6634
-0.750 0.2417 0.01725 0.01171 -0.0970 0.9721 0.6729
-0.500 0.2762 0.01677 0.01127 -0.0975 0.9537 0.6773
0.000 0.4473 0.01436 0.00796 -0.1184 0.6706 0.6881
0.250 0.4539 0.01627 0.00850 -0.1135 0.3894 0.6909
0.500 0.4735 0.01714 0.00885 -0.1116 0.2754 0.6941
0.750 0.4977 0.01783 0.00910 -0.1109 0.1836 0.6977
1.000 0.5267 0.01840 0.00931 -0.1115 0.1234 0.7021
1.250 0.5557 0.01878 0.00954 -0.1118 0.1021 0.7058
1.500 0.5793 0.01911 0.00983 -0.1105 0.0921 0.7078
1.750 0.6049 0.01944 0.01012 -0.1098 0.0844 0.7095
2.000 0.6319 0.01973 0.01040 -0.1095 0.0788 0.7109
2.250 0.6596 0.02002 0.01069 -0.1094 0.0743 0.7122
2.500 0.6872 0.02045 0.01104 -0.1094 0.0703 0.7133
2.750 0.7156 0.02073 0.01135 -0.1095 0.0670 0.7147
3.000 0.7439 0.02106 0.01167 -0.1096 0.0638 0.7162
3.250 0.7723 0.02148 0.01204 -0.1098 0.0613 0.7174
3.500 0.8006 0.02197 0.01251 -0.1100 0.0592 0.7184
3.750 0.8296 0.02236 0.01295 -0.1102 0.0568 0.7195
4.000 0.8585 0.02277 0.01334 -0.1105 0.0545 0.7205
4.250 0.8871 0.02324 0.01377 -0.1108 0.0527 0.7215
4.500 0.9154 0.02391 0.01441 -0.1110 0.0511 0.7225
4.750 0.9446 0.02446 0.01503 -0.1114 0.0495 0.7236
5.000 0.9714 0.02498 0.01560 -0.1111 0.0477 0.7246
5.250 0.9973 0.02547 0.01612 -0.1106 0.0462 0.7253
5.500 1.0231 0.02604 0.01670 -0.1103 0.0450 0.7260
5.750 1.0490 0.02687 0.01754 -0.1099 0.0440 0.7266
6.000 1.0753 0.02767 0.01849 -0.1095 0.0429 0.7273
6.250 1.1013 0.02852 0.01948 -0.1091 0.0418 0.7280
6.500 1.1268 0.02940 0.02048 -0.1087 0.0408 0.7287
6.750 1.1519 0.03023 0.02140 -0.1082 0.0399 0.7294
7.000 1.1765 0.03098 0.02219 -0.1077 0.0391 0.7301
7.250 1.2006 0.03179 0.02303 -0.1071 0.0383 0.7309
7.500 1.2240 0.03297 0.02435 -0.1064 0.0375 0.7317
7.750 1.2464 0.03431 0.02598 -0.1054 0.0366 0.7325
8.000 1.2677 0.03578 0.02771 -0.1043 0.0358 0.7333
8.250 1.2877 0.03725 0.02942 -0.1031 0.0350 0.7343
8.500 1.3068 0.03865 0.03101 -0.1017 0.0344 0.7355
8.750 1.3256 0.03986 0.03238 -0.1004 0.0338 0.7366
9.000 1.3438 0.04099 0.03362 -0.0990 0.0333 0.7375
9.250 1.3613 0.04215 0.03488 -0.0976 0.0329 0.7383
9.500 1.3778 0.04337 0.03617 -0.0961 0.0325 0.7391
9.750 1.3852 0.04590 0.03907 -0.0933 0.0320 0.7398
10.000 1.3832 0.04941 0.04312 -0.0893 0.0314 0.7404
10.250 1.3737 0.05335 0.04755 -0.0846 0.0310 0.7410
10.500 1.3554 0.05742 0.05204 -0.0791 0.0307 0.7415
10.750 1.3263 0.06153 0.05651 -0.0726 0.0305 0.7420
11.000 1.2903 0.06713 0.06250 -0.0675 0.0303 0.7424
11.250 1.2413 0.07501 0.07078 -0.0648 0.0303 0.7426
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