DSMA-523A AIRFOIL (dsma523a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: DSMA-523A AIRFOIL (dsma523a-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.31 at α=-0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dsma523a-il-1000000.txt Download as CSV file: xf-dsma523a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0825 0.10607 0.10340 -0.0327 1.0000 0.0204
-17.750 -1.1336 0.09218 0.08927 -0.0409 1.0000 0.0203
-17.500 -1.1647 0.08261 0.07952 -0.0465 1.0000 0.0203
-17.250 -1.1877 0.07483 0.07157 -0.0509 1.0000 0.0203
-17.000 -1.2052 0.06838 0.06497 -0.0543 1.0000 0.0203
-16.750 -1.2181 0.06298 0.05944 -0.0569 1.0000 0.0204
-16.500 -1.2274 0.05842 0.05475 -0.0588 1.0000 0.0205
-16.250 -1.2348 0.05441 0.05062 -0.0602 1.0000 0.0205
-16.000 -1.2403 0.05090 0.04699 -0.0611 1.0000 0.0206
-15.750 -1.2434 0.04790 0.04389 -0.0615 1.0000 0.0207
-15.500 -1.2455 0.04520 0.04108 -0.0615 1.0000 0.0209
-15.250 -1.2466 0.04279 0.03857 -0.0612 1.0000 0.0210
-15.000 -1.2460 0.04068 0.03637 -0.0607 1.0000 0.0211
-14.750 -1.2444 0.03875 0.03434 -0.0600 1.0000 0.0212
-14.500 -1.2419 0.03698 0.03249 -0.0591 1.0000 0.0213
-14.250 -1.2379 0.03540 0.03083 -0.0581 1.0000 0.0214
-14.000 -1.2336 0.03394 0.02929 -0.0569 1.0000 0.0215
-13.750 -1.2270 0.03272 0.02799 -0.0556 1.0000 0.0217
-13.500 -1.2209 0.03157 0.02678 -0.0542 1.0000 0.0217
-13.250 -1.2235 0.02982 0.02493 -0.0519 1.0000 0.0220
-13.000 -1.2271 0.02834 0.02339 -0.0491 1.0000 0.0222
-12.750 -1.2316 0.02729 0.02229 -0.0455 1.0000 0.0225
-12.500 -1.2322 0.02630 0.02127 -0.0425 1.0000 0.0226
-12.250 -1.2239 0.02540 0.02034 -0.0408 1.0000 0.0229
-12.000 -1.2120 0.02453 0.01943 -0.0397 1.0000 0.0231
-11.750 -1.1907 0.02369 0.01856 -0.0402 0.9996 0.0235
-11.500 -1.1638 0.02285 0.01767 -0.0417 0.9986 0.0238
-11.250 -1.1367 0.02203 0.01680 -0.0431 0.9977 0.0242
-11.000 -1.1088 0.02126 0.01598 -0.0446 0.9967 0.0245
-10.750 -1.0796 0.02057 0.01523 -0.0461 0.9959 0.0249
-10.500 -1.0491 0.01995 0.01456 -0.0478 0.9951 0.0253
-10.250 -1.0179 0.01942 0.01398 -0.0495 0.9945 0.0255
-10.000 -0.9875 0.01827 0.01280 -0.0519 0.9940 0.0263
-9.750 -0.9583 0.01760 0.01212 -0.0533 0.9931 0.0269
-9.500 -0.9301 0.01705 0.01155 -0.0543 0.9921 0.0275
-9.250 -0.9005 0.01655 0.01103 -0.0555 0.9912 0.0281
-9.000 -0.8703 0.01609 0.01054 -0.0568 0.9904 0.0288
-8.750 -0.8397 0.01570 0.01011 -0.0580 0.9897 0.0294
-8.500 -0.8081 0.01512 0.00951 -0.0596 0.9891 0.0302
-8.250 -0.7760 0.01464 0.00904 -0.0612 0.9886 0.0313
-8.000 -0.7435 0.01430 0.00869 -0.0626 0.9880 0.0324
-7.750 -0.7109 0.01399 0.00836 -0.0640 0.9875 0.0335
-7.500 -0.6782 0.01363 0.00800 -0.0656 0.9871 0.0348
-7.250 -0.6457 0.01335 0.00776 -0.0669 0.9868 0.0364
-7.000 -0.6132 0.01315 0.00756 -0.0682 0.9864 0.0380
-6.750 -0.5805 0.01295 0.00738 -0.0695 0.9861 0.0399
-6.500 -0.5482 0.01287 0.00734 -0.0706 0.9858 0.0419
-6.250 -0.5156 0.01277 0.00724 -0.0718 0.9855 0.0440
-6.000 -0.4831 0.01274 0.00725 -0.0729 0.9852 0.0460
-5.750 -0.4576 0.01263 0.00715 -0.0725 0.9831 0.0481
-5.500 -0.4267 0.01248 0.00701 -0.0733 0.9820 0.0500
-5.250 -0.3957 0.01239 0.00695 -0.0740 0.9812 0.0520
-5.000 -0.3648 0.01237 0.00693 -0.0747 0.9804 0.0542
-4.750 -0.3311 0.01209 0.00666 -0.0763 0.9801 0.0564
-4.500 -0.2978 0.01188 0.00649 -0.0777 0.9797 0.0584
-4.250 -0.2645 0.01175 0.00636 -0.0790 0.9793 0.0602
-4.000 -0.2297 0.01151 0.00614 -0.0807 0.9789 0.0620
-3.750 -0.1940 0.01124 0.00589 -0.0827 0.9787 0.0641
-3.500 -0.1596 0.01107 0.00574 -0.0842 0.9784 0.0656
-3.250 -0.1255 0.01095 0.00563 -0.0857 0.9781 0.0669
-3.000 -0.0906 0.01082 0.00553 -0.0873 0.9778 0.0685
-2.750 -0.0548 0.01059 0.00533 -0.0889 0.9751 0.0703
-2.500 -0.0028 0.01010 0.00489 -0.0938 0.9715 0.0731
-2.250 0.0425 0.00969 0.00454 -0.0972 0.9677 0.0778
-2.000 0.0915 0.00914 0.00418 -0.1016 0.9657 0.1124
-1.750 0.1467 0.00852 0.00373 -0.1073 0.9644 0.1470
-1.500 0.1512 0.00821 0.00352 -0.1022 0.9472 0.1698
-1.250 0.1889 0.00753 0.00306 -0.1042 0.9364 0.2281
-1.000 0.2521 0.00637 0.00229 -0.1120 0.9288 0.3426
-0.750 0.3445 0.00490 0.00160 -0.1269 0.9083 0.6153
-0.500 0.3535 0.00618 0.00180 -0.1222 0.6352 0.6287
-0.250 0.3700 0.00734 0.00214 -0.1199 0.4266 0.6413
0.000 0.3926 0.00813 0.00248 -0.1186 0.3125 0.6548
0.250 0.4150 0.00885 0.00291 -0.1171 0.2298 0.6627
0.500 0.4390 0.00949 0.00323 -0.1161 0.1501 0.6678
0.750 0.4649 0.00999 0.00347 -0.1156 0.0976 0.6709
1.000 0.4924 0.01027 0.00365 -0.1153 0.0837 0.6731
1.250 0.5189 0.01048 0.00386 -0.1147 0.0768 0.6755
1.500 0.5453 0.01074 0.00410 -0.1141 0.0706 0.6773
1.750 0.5723 0.01096 0.00430 -0.1136 0.0660 0.6790
2.000 0.5992 0.01122 0.00453 -0.1131 0.0613 0.6807
2.250 0.6267 0.01141 0.00471 -0.1128 0.0587 0.6824
2.500 0.6540 0.01165 0.00490 -0.1124 0.0556 0.6841
2.750 0.6810 0.01192 0.00516 -0.1120 0.0529 0.6859
3.000 0.7081 0.01216 0.00540 -0.1116 0.0512 0.6881
3.250 0.7352 0.01242 0.00564 -0.1111 0.0494 0.6901
3.500 0.7616 0.01262 0.00584 -0.1106 0.0474 0.6928
3.750 0.7877 0.01294 0.00617 -0.1100 0.0457 0.6939
4.000 0.8149 0.01312 0.00637 -0.1097 0.0447 0.6949
4.250 0.8412 0.01337 0.00663 -0.1091 0.0435 0.6964
4.500 0.8678 0.01360 0.00685 -0.1086 0.0422 0.6978
4.750 0.8946 0.01389 0.00711 -0.1083 0.0405 0.6985
5.000 0.9213 0.01420 0.00744 -0.1079 0.0392 0.6991
5.250 0.9488 0.01438 0.00763 -0.1077 0.0384 0.6997
5.500 0.9760 0.01460 0.00785 -0.1074 0.0374 0.7003
5.750 1.0031 0.01483 0.00808 -0.1072 0.0364 0.7009
6.000 1.0299 0.01510 0.00834 -0.1068 0.0354 0.7015
6.250 1.0542 0.01573 0.00897 -0.1060 0.0341 0.7022
6.500 1.0809 0.01596 0.00923 -0.1057 0.0336 0.7030
6.750 1.1074 0.01623 0.00952 -0.1053 0.0330 0.7037
7.000 1.1338 0.01651 0.00983 -0.1048 0.0323 0.7042
7.250 1.1599 0.01681 0.01014 -0.1044 0.0316 0.7047
7.500 1.1858 0.01712 0.01046 -0.1039 0.0310 0.7052
7.750 1.2112 0.01748 0.01082 -0.1033 0.0303 0.7057
8.000 1.2350 0.01806 0.01141 -0.1025 0.0296 0.7061
8.250 1.2578 0.01879 0.01220 -0.1015 0.0290 0.7066
8.500 1.2829 0.01914 0.01259 -0.1008 0.0287 0.7069
8.750 1.3075 0.01953 0.01303 -0.1001 0.0283 0.7073
9.000 1.3317 0.01997 0.01352 -0.0993 0.0278 0.7076
9.250 1.3564 0.02036 0.01395 -0.0987 0.0274 0.7084
9.500 1.3806 0.02077 0.01439 -0.0980 0.0269 0.7093
9.750 1.4042 0.02120 0.01486 -0.0972 0.0265 0.7100
10.000 1.4271 0.02165 0.01536 -0.0963 0.0261 0.7107
10.250 1.4492 0.02219 0.01593 -0.0952 0.0258 0.7115
10.500 1.4698 0.02287 0.01665 -0.0939 0.0254 0.7122
10.750 1.4853 0.02426 0.01815 -0.0918 0.0248 0.7128
11.000 1.5059 0.02487 0.01885 -0.0905 0.0246 0.7133
11.250 1.5270 0.02536 0.01941 -0.0893 0.0243 0.7139
11.500 1.5475 0.02588 0.02000 -0.0880 0.0241 0.7145
11.750 1.5665 0.02653 0.02074 -0.0865 0.0238 0.7151
12.000 1.5843 0.02726 0.02156 -0.0848 0.0235 0.7157
12.250 1.6017 0.02795 0.02233 -0.0831 0.0232 0.7163
12.500 1.6179 0.02870 0.02316 -0.0812 0.0230 0.7169
12.750 1.6325 0.02953 0.02407 -0.0791 0.0228 0.7175
13.000 1.6452 0.03032 0.02494 -0.0767 0.0226 0.7181
13.250 1.6536 0.03109 0.02578 -0.0735 0.0224 0.7187
13.500 1.6616 0.03210 0.02688 -0.0704 0.0223 0.7193
13.750 1.6699 0.03306 0.02792 -0.0676 0.0221 0.7199
14.000 1.6773 0.03410 0.02904 -0.0647 0.0219 0.7205
14.250 1.6816 0.03540 0.03043 -0.0616 0.0218 0.7211
14.500 1.6851 0.03677 0.03189 -0.0585 0.0217 0.7217
14.750 1.6871 0.03829 0.03350 -0.0555 0.0215 0.7222
15.000 1.6856 0.04016 0.03550 -0.0524 0.0214 0.7226
15.250 1.6801 0.04247 0.03794 -0.0494 0.0213 0.7231
15.500 1.6714 0.04521 0.04082 -0.0466 0.0212 0.7236
15.750 1.6592 0.04851 0.04428 -0.0444 0.0211 0.7240
16.000 1.6402 0.05287 0.04883 -0.0429 0.0210 0.7244
16.250 1.6170 0.05834 0.05451 -0.0429 0.0209 0.7247
16.500 1.5944 0.06466 0.06103 -0.0448 0.0209 0.7249
16.750 1.5670 0.07289 0.06948 -0.0492 0.0209 0.7250
17.000 1.5407 0.08234 0.07913 -0.0555 0.0209 0.7251
17.250 1.5091 0.09370 0.09070 -0.0635 0.0210 0.7252
17.500 1.4557 0.10980 0.10704 -0.0743 0.0211 0.7251
|
Polar data table (+)
Polar graphs
<< Back to DSMA-523A AIRFOIL (dsma523a-il)