DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523A AIRFOIL (dsma523a-il) Reynolds number: 500,000 Max Cl/Cd: 59.35 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523a-il-500000-n5.txt Download as CSV file: xf-dsma523a-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0926 0.08958 0.08577 -0.0409 1.0000 0.0204
-16.750 -1.1193 0.08064 0.07664 -0.0461 1.0000 0.0204
-16.500 -1.1380 0.07351 0.06934 -0.0502 1.0000 0.0205
-16.250 -1.1521 0.06754 0.06322 -0.0534 1.0000 0.0205
-16.000 -1.1619 0.06258 0.05813 -0.0558 1.0000 0.0206
-15.750 -1.1690 0.05836 0.05379 -0.0575 1.0000 0.0207
-15.500 -1.1741 0.05466 0.04997 -0.0587 1.0000 0.0208
-15.250 -1.1777 0.05142 0.04662 -0.0595 1.0000 0.0209
-15.000 -1.1802 0.04854 0.04364 -0.0598 1.0000 0.0211
-14.750 -1.1816 0.04599 0.04097 -0.0597 1.0000 0.0212
-14.500 -1.1821 0.04366 0.03854 -0.0594 1.0000 0.0213
-14.250 -1.1811 0.04157 0.03635 -0.0588 1.0000 0.0214
-14.000 -1.1792 0.03965 0.03433 -0.0581 1.0000 0.0216
-13.750 -1.1766 0.03788 0.03247 -0.0571 1.0000 0.0218
-13.500 -1.1729 0.03627 0.03077 -0.0560 1.0000 0.0219
-13.250 -1.1691 0.03476 0.02917 -0.0547 1.0000 0.0221
-13.000 -1.1643 0.03340 0.02772 -0.0532 1.0000 0.0223
-12.750 -1.1600 0.03212 0.02636 -0.0515 1.0000 0.0225
-12.500 -1.1561 0.03095 0.02511 -0.0495 1.0000 0.0226
-12.250 -1.1539 0.02989 0.02397 -0.0470 1.0000 0.0228
-12.000 -1.1539 0.02891 0.02293 -0.0440 1.0000 0.0230
-11.750 -1.1409 0.02788 0.02181 -0.0433 0.9995 0.0232
-11.500 -1.1193 0.02678 0.02064 -0.0442 0.9984 0.0234
-11.250 -1.0964 0.02562 0.01943 -0.0454 0.9969 0.0238
-11.000 -1.0709 0.02464 0.01842 -0.0469 0.9956 0.0242
-10.750 -1.0442 0.02378 0.01753 -0.0483 0.9946 0.0245
-10.500 -1.0167 0.02301 0.01670 -0.0497 0.9938 0.0250
-10.250 -0.9924 0.02223 0.01588 -0.0504 0.9922 0.0254
-10.000 -0.9663 0.02151 0.01511 -0.0514 0.9909 0.0260
-9.750 -0.9391 0.02082 0.01436 -0.0524 0.9897 0.0265
-9.500 -0.9109 0.02018 0.01367 -0.0536 0.9887 0.0270
-9.250 -0.8819 0.01953 0.01297 -0.0550 0.9878 0.0276
-9.000 -0.8519 0.01888 0.01232 -0.0565 0.9870 0.0283
-8.750 -0.8210 0.01834 0.01177 -0.0580 0.9864 0.0291
-8.500 -0.7897 0.01785 0.01125 -0.0596 0.9858 0.0299
-8.250 -0.7612 0.01737 0.01073 -0.0605 0.9847 0.0308
-8.000 -0.7329 0.01691 0.01023 -0.0613 0.9834 0.0316
-7.750 -0.7033 0.01646 0.00980 -0.0623 0.9824 0.0328
-7.500 -0.6730 0.01610 0.00945 -0.0634 0.9816 0.0340
-7.250 -0.6424 0.01577 0.00911 -0.0645 0.9809 0.0356
-7.000 -0.6112 0.01548 0.00885 -0.0656 0.9803 0.0373
-6.750 -0.5796 0.01528 0.00866 -0.0667 0.9797 0.0392
-6.500 -0.5474 0.01503 0.00841 -0.0680 0.9791 0.0413
-6.250 -0.5153 0.01488 0.00828 -0.0691 0.9787 0.0432
-6.000 -0.4859 0.01470 0.00809 -0.0697 0.9776 0.0456
-5.750 -0.4568 0.01449 0.00788 -0.0702 0.9764 0.0473
-5.500 -0.4264 0.01431 0.00772 -0.0710 0.9755 0.0492
-5.250 -0.3956 0.01417 0.00756 -0.0718 0.9747 0.0515
-5.000 -0.3635 0.01392 0.00733 -0.0730 0.9741 0.0532
-4.750 -0.3306 0.01367 0.00709 -0.0744 0.9736 0.0549
-4.500 -0.2975 0.01347 0.00690 -0.0757 0.9731 0.0569
-4.250 -0.2647 0.01334 0.00676 -0.0769 0.9726 0.0584
-4.000 -0.2303 0.01297 0.00644 -0.0787 0.9724 0.0602
-3.750 -0.1992 0.01275 0.00625 -0.0797 0.9714 0.0617
-3.500 -0.1684 0.01257 0.00609 -0.0805 0.9702 0.0634
-3.250 -0.1362 0.01243 0.00596 -0.0816 0.9693 0.0647
-3.000 -0.1025 0.01224 0.00581 -0.0830 0.9686 0.0664
-2.750 -0.0685 0.01205 0.00566 -0.0845 0.9681 0.0691
-2.500 -0.0350 0.01192 0.00556 -0.0858 0.9677 0.0714
-2.250 0.0000 0.01179 0.00549 -0.0874 0.9671 0.0742
-2.000 0.0414 0.01140 0.00522 -0.0902 0.9627 0.0844
-1.750 0.0583 0.01097 0.00490 -0.0878 0.9483 0.1113
-1.500 0.0924 0.01044 0.00451 -0.0890 0.9384 0.1380
-1.250 0.1399 0.00968 0.00394 -0.0929 0.9317 0.1795
-1.000 0.2110 0.00842 0.00305 -0.1021 0.9233 0.2783
-0.750 0.3015 0.00756 0.00248 -0.1163 0.6864 0.6084
-0.500 0.3105 0.00924 0.00308 -0.1123 0.4208 0.6336
-0.250 0.3341 0.00997 0.00339 -0.1112 0.3208 0.6482
0.000 0.3588 0.01052 0.00365 -0.1104 0.2488 0.6536
0.250 0.3852 0.01098 0.00381 -0.1100 0.1819 0.6575
0.500 0.4128 0.01140 0.00392 -0.1100 0.1238 0.6615
0.750 0.4388 0.01176 0.00416 -0.1094 0.0975 0.6644
1.000 0.4645 0.01209 0.00445 -0.1086 0.0860 0.6674
1.250 0.4909 0.01240 0.00471 -0.1080 0.0776 0.6708
1.500 0.5185 0.01263 0.00491 -0.1077 0.0720 0.6741
1.750 0.5468 0.01285 0.00505 -0.1077 0.0667 0.6763
2.000 0.5756 0.01304 0.00520 -0.1077 0.0631 0.6781
2.250 0.6044 0.01323 0.00535 -0.1078 0.0596 0.6795
2.500 0.6313 0.01346 0.00554 -0.1074 0.0561 0.6805
2.750 0.6579 0.01367 0.00577 -0.1069 0.0539 0.6819
3.000 0.6840 0.01392 0.00604 -0.1062 0.0517 0.6836
3.250 0.7097 0.01423 0.00633 -0.1055 0.0496 0.6857
3.500 0.7359 0.01453 0.00663 -0.1050 0.0476 0.6876
3.750 0.7631 0.01476 0.00687 -0.1047 0.0460 0.6890
4.000 0.7908 0.01498 0.00708 -0.1045 0.0445 0.6897
4.250 0.8182 0.01522 0.00731 -0.1043 0.0431 0.6904
4.500 0.8452 0.01553 0.00759 -0.1041 0.0417 0.6911
4.750 0.8723 0.01583 0.00790 -0.1038 0.0406 0.6918
5.000 0.8995 0.01610 0.00818 -0.1035 0.0396 0.6925
5.250 0.9266 0.01636 0.00846 -0.1033 0.0383 0.6931
5.500 0.9535 0.01665 0.00874 -0.1030 0.0372 0.6940
5.750 0.9801 0.01698 0.00905 -0.1027 0.0362 0.6948
6.000 1.0058 0.01743 0.00949 -0.1022 0.0352 0.6956
6.250 1.0323 0.01775 0.00986 -0.1018 0.0345 0.6961
6.500 1.0585 0.01809 0.01023 -0.1014 0.0336 0.6966
6.750 1.0846 0.01843 0.01059 -0.1010 0.0327 0.6971
7.000 1.1104 0.01878 0.01096 -0.1005 0.0319 0.6975
7.250 1.1359 0.01914 0.01133 -0.1000 0.0311 0.6981
7.500 1.1604 0.01960 0.01180 -0.0993 0.0305 0.6987
7.750 1.1845 0.02012 0.01237 -0.0986 0.0299 0.6992
8.000 1.2090 0.02057 0.01290 -0.0978 0.0294 0.6997
8.250 1.2331 0.02106 0.01345 -0.0970 0.0289 0.7002
8.500 1.2569 0.02156 0.01402 -0.0962 0.0283 0.7008
8.750 1.2804 0.02207 0.01460 -0.0954 0.0278 0.7013
9.000 1.3037 0.02258 0.01517 -0.0945 0.0274 0.7018
9.250 1.3266 0.02311 0.01575 -0.0936 0.0269 0.7024
9.500 1.3491 0.02365 0.01635 -0.0926 0.0265 0.7030
9.750 1.3707 0.02427 0.01701 -0.0915 0.0262 0.7037
10.000 1.3912 0.02499 0.01779 -0.0902 0.0257 0.7045
10.250 1.4108 0.02583 0.01870 -0.0888 0.0254 0.7052
10.500 1.4311 0.02656 0.01955 -0.0875 0.0252 0.7058
10.750 1.4505 0.02734 0.02044 -0.0861 0.0249 0.7064
11.000 1.4692 0.02816 0.02138 -0.0846 0.0246 0.7070
11.250 1.4869 0.02903 0.02237 -0.0829 0.0243 0.7076
11.500 1.5037 0.02992 0.02338 -0.0812 0.0240 0.7083
11.750 1.5198 0.03079 0.02436 -0.0794 0.0237 0.7089
12.000 1.5347 0.03171 0.02538 -0.0774 0.0234 0.7095
12.250 1.5485 0.03261 0.02638 -0.0753 0.0232 0.7101
12.500 1.5579 0.03350 0.02738 -0.0724 0.0229 0.7108
12.750 1.5666 0.03450 0.02849 -0.0695 0.0227 0.7114
13.000 1.5753 0.03554 0.02961 -0.0668 0.0225 0.7120
13.250 1.5820 0.03674 0.03093 -0.0640 0.0224 0.7125
13.500 1.5873 0.03805 0.03235 -0.0611 0.0222 0.7131
13.750 1.5910 0.03948 0.03389 -0.0582 0.0221 0.7136
14.000 1.5929 0.04110 0.03562 -0.0553 0.0219 0.7141
14.250 1.5924 0.04296 0.03761 -0.0525 0.0218 0.7145
14.500 1.5894 0.04513 0.03990 -0.0498 0.0217 0.7149
14.750 1.5835 0.04768 0.04258 -0.0475 0.0215 0.7153
15.000 1.5739 0.05079 0.04584 -0.0455 0.0214 0.7156
15.250 1.5644 0.05421 0.04945 -0.0443 0.0213 0.7160
15.500 1.5520 0.05835 0.05380 -0.0441 0.0213 0.7164
15.750 1.5350 0.06370 0.05937 -0.0454 0.0212 0.7169
16.000 1.5128 0.07085 0.06675 -0.0489 0.0211 0.7174
16.250 1.4793 0.08162 0.07780 -0.0563 0.0212 0.7176
16.500 1.4173 0.10018 0.09671 -0.0696 0.0213 0.7175
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