DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523A AIRFOIL (dsma523a-il) Reynolds number: 200,000 Max Cl/Cd: 37.4 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523a-il-200000-n5.txt Download as CSV file: xf-dsma523a-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8637 0.07519 0.07022 -0.0502 1.0000 0.0303
-13.000 -0.9094 0.06526 0.05999 -0.0557 1.0000 0.0302
-12.750 -0.9392 0.05908 0.05356 -0.0576 1.0000 0.0302
-12.500 -0.9621 0.05437 0.04860 -0.0579 1.0000 0.0304
-12.250 -0.9807 0.05051 0.04451 -0.0572 1.0000 0.0305
-12.000 -0.9962 0.04726 0.04104 -0.0557 1.0000 0.0307
-11.750 -1.0099 0.04451 0.03806 -0.0534 1.0000 0.0310
-11.500 -1.0228 0.04219 0.03552 -0.0504 1.0000 0.0312
-11.250 -1.0282 0.03972 0.03279 -0.0485 1.0000 0.0315
-11.000 -1.0235 0.03780 0.03071 -0.0473 1.0000 0.0318
-10.750 -1.0133 0.03645 0.02930 -0.0465 1.0000 0.0321
-10.500 -1.0010 0.03521 0.02799 -0.0458 1.0000 0.0324
-10.250 -0.9871 0.03402 0.02672 -0.0453 1.0000 0.0328
-10.000 -0.9717 0.03290 0.02551 -0.0448 1.0000 0.0332
-9.750 -0.9553 0.03181 0.02430 -0.0442 1.0000 0.0339
-9.500 -0.9381 0.03063 0.02299 -0.0437 1.0000 0.0346
-9.250 -0.9200 0.02937 0.02153 -0.0431 1.0000 0.0356
-9.000 -0.9009 0.02819 0.02019 -0.0425 1.0000 0.0364
-8.750 -0.8799 0.02749 0.01948 -0.0422 1.0000 0.0370
-8.500 -0.8581 0.02681 0.01876 -0.0420 1.0000 0.0377
-8.250 -0.8360 0.02608 0.01797 -0.0417 1.0000 0.0385
-8.000 -0.8133 0.02532 0.01712 -0.0414 1.0000 0.0397
-7.750 -0.7904 0.02450 0.01613 -0.0410 1.0000 0.0412
-7.500 -0.7665 0.02395 0.01561 -0.0410 1.0000 0.0421
-7.250 -0.7421 0.02341 0.01505 -0.0410 1.0000 0.0433
-7.000 -0.7176 0.02281 0.01439 -0.0408 1.0000 0.0448
-6.750 -0.6928 0.02219 0.01365 -0.0406 1.0000 0.0464
-6.500 -0.6679 0.02161 0.01311 -0.0406 1.0000 0.0476
-6.250 -0.6423 0.02110 0.01260 -0.0406 1.0000 0.0493
-6.000 -0.6159 0.02068 0.01208 -0.0407 1.0000 0.0517
-5.750 -0.5898 0.02010 0.01155 -0.0409 1.0000 0.0536
-5.500 -0.5629 0.01957 0.01104 -0.0412 1.0000 0.0559
-5.250 -0.5354 0.01920 0.01059 -0.0415 1.0000 0.0583
-5.000 -0.5064 0.01847 0.00998 -0.0425 1.0000 0.0609
-4.750 -0.4768 0.01800 0.00951 -0.0434 1.0000 0.0638
-4.500 -0.4452 0.01743 0.00899 -0.0449 1.0000 0.0666
-4.250 -0.4128 0.01696 0.00854 -0.0464 0.9999 0.0697
-4.000 -0.3781 0.01658 0.00819 -0.0484 0.9992 0.0733
-3.750 -0.3439 0.01624 0.00792 -0.0502 0.9987 0.0774
-3.500 -0.3093 0.01595 0.00773 -0.0521 0.9980 0.0838
-3.250 -0.2738 0.01569 0.00759 -0.0541 0.9972 0.0995
-3.000 -0.2372 0.01536 0.00746 -0.0565 0.9966 0.1298
-2.750 -0.1997 0.01499 0.00734 -0.0592 0.9962 0.1751
-2.500 -0.1614 0.01465 0.00724 -0.0620 0.9958 0.2244
-2.250 -0.1189 0.01409 0.00711 -0.0660 0.9961 0.3123
-2.000 -0.0723 0.01333 0.00715 -0.0710 0.9973 0.4752
-1.750 -0.0567 0.01437 0.00881 -0.0666 0.9938 0.5694
-1.500 -0.0305 0.01482 0.00933 -0.0657 0.9903 0.6027
-1.250 0.0064 0.01493 0.00940 -0.0677 0.9884 0.6224
-1.000 0.0522 0.01507 0.00948 -0.0717 0.9857 0.6454
-0.500 0.1427 0.01595 0.01043 -0.0762 0.9610 0.6803
-0.250 0.1593 0.01575 0.01031 -0.0725 0.9408 0.6838
0.000 0.2064 0.01517 0.00976 -0.0748 0.9262 0.6875
0.250 0.2456 0.01469 0.00929 -0.0760 0.9035 0.6911
0.500 0.2708 0.01444 0.00903 -0.0753 0.8653 0.6953
0.750 0.3657 0.01531 0.00805 -0.0868 0.4562 0.6991
1.000 0.3808 0.01621 0.00838 -0.0840 0.3305 0.7011
1.250 0.4003 0.01690 0.00866 -0.0822 0.2383 0.7034
1.500 0.4222 0.01751 0.00892 -0.0809 0.1617 0.7063
1.750 0.4474 0.01801 0.00916 -0.0804 0.1184 0.7100
2.000 0.4792 0.01834 0.00933 -0.0816 0.0994 0.7148
2.500 0.5311 0.01890 0.00981 -0.0806 0.0837 0.7186
2.750 0.5579 0.01918 0.01005 -0.0804 0.0780 0.7193
3.000 0.5850 0.01946 0.01031 -0.0803 0.0736 0.7201
3.250 0.6123 0.01972 0.01058 -0.0802 0.0697 0.7208
3.500 0.6392 0.02006 0.01089 -0.0800 0.0667 0.7216
3.750 0.6661 0.02047 0.01127 -0.0799 0.0640 0.7224
4.000 0.6937 0.02078 0.01161 -0.0799 0.0612 0.7232
4.250 0.7209 0.02113 0.01195 -0.0798 0.0586 0.7243
4.500 0.7476 0.02159 0.01237 -0.0797 0.0567 0.7255
4.750 0.7749 0.02211 0.01291 -0.0796 0.0549 0.7266
5.000 0.8029 0.02254 0.01338 -0.0797 0.0529 0.7275
5.250 0.8309 0.02297 0.01382 -0.0799 0.0509 0.7283
5.500 0.8586 0.02344 0.01427 -0.0800 0.0493 0.7292
5.750 0.8857 0.02416 0.01494 -0.0801 0.0480 0.7301
6.000 0.9138 0.02479 0.01568 -0.0802 0.0468 0.7310
6.250 0.9417 0.02548 0.01646 -0.0803 0.0455 0.7318
6.500 0.9692 0.02612 0.01717 -0.0804 0.0441 0.7327
6.750 0.9963 0.02671 0.01777 -0.0805 0.0428 0.7335
7.000 1.0232 0.02736 0.01839 -0.0806 0.0418 0.7346
7.250 1.0480 0.02827 0.01938 -0.0802 0.0408 0.7354
7.500 1.0722 0.02926 0.02058 -0.0795 0.0400 0.7361
7.750 1.0959 0.03032 0.02184 -0.0788 0.0390 0.7367
8.000 1.1190 0.03137 0.02305 -0.0781 0.0381 0.7373
8.250 1.1415 0.03233 0.02415 -0.0773 0.0373 0.7379
8.500 1.1636 0.03317 0.02509 -0.0765 0.0366 0.7385
8.750 1.1852 0.03400 0.02597 -0.0757 0.0360 0.7391
9.000 1.2062 0.03501 0.02702 -0.0749 0.0354 0.7398
9.250 1.2234 0.03672 0.02907 -0.0734 0.0347 0.7404
9.500 1.2380 0.03878 0.03150 -0.0716 0.0340 0.7411
9.750 1.2501 0.04101 0.03408 -0.0696 0.0334 0.7418
10.000 1.2597 0.04334 0.03674 -0.0674 0.0329 0.7425
10.250 1.2665 0.04574 0.03946 -0.0650 0.0324 0.7432
10.500 1.2703 0.04822 0.04223 -0.0623 0.0320 0.7440
10.750 1.2701 0.05084 0.04513 -0.0593 0.0317 0.7449
11.000 1.2645 0.05340 0.04795 -0.0558 0.0315 0.7459
11.250 1.2522 0.05629 0.05108 -0.0519 0.0313 0.7468
11.500 1.2361 0.05971 0.05476 -0.0485 0.0311 0.7476
11.750 1.2116 0.06418 0.05952 -0.0458 0.0310 0.7481
12.000 1.1702 0.07133 0.06702 -0.0453 0.0310 0.7485
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