DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 500,000 Max Cl/Cd: 60.04 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dsma523b-il-500000-n5.txt Download as CSV file: xf-dsma523b-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0667 0.09496 0.09136 -0.0362 1.0000 0.0209
-16.750 -1.1068 0.08304 0.07919 -0.0433 1.0000 0.0209
-16.500 -1.1318 0.07453 0.07049 -0.0483 1.0000 0.0209
-16.250 -1.1494 0.06785 0.06363 -0.0520 1.0000 0.0210
-16.000 -1.1626 0.06232 0.05795 -0.0547 1.0000 0.0210
-15.750 -1.1728 0.05769 0.05316 -0.0566 1.0000 0.0211
-15.500 -1.1802 0.05382 0.04915 -0.0577 1.0000 0.0212
-15.250 -1.1866 0.05043 0.04563 -0.0583 1.0000 0.0213
-15.000 -1.1908 0.04749 0.04256 -0.0585 1.0000 0.0214
-14.750 -1.1935 0.04488 0.03983 -0.0582 1.0000 0.0215
-14.500 -1.1948 0.04255 0.03738 -0.0577 1.0000 0.0217
-14.250 -1.1955 0.04042 0.03514 -0.0568 1.0000 0.0218
-14.000 -1.1950 0.03853 0.03314 -0.0557 1.0000 0.0219
-13.750 -1.1946 0.03680 0.03130 -0.0542 1.0000 0.0221
-13.500 -1.1953 0.03523 0.02964 -0.0523 1.0000 0.0222
-13.250 -1.1987 0.03380 0.02813 -0.0495 1.0000 0.0223
-13.000 -1.1929 0.03239 0.02662 -0.0483 1.0000 0.0224
-12.750 -1.1833 0.03088 0.02504 -0.0477 1.0000 0.0226
-12.500 -1.1701 0.02944 0.02355 -0.0477 1.0000 0.0228
-12.250 -1.1534 0.02820 0.02225 -0.0480 1.0000 0.0231
-12.000 -1.1303 0.02705 0.02105 -0.0493 0.9996 0.0234
-11.750 -1.1034 0.02601 0.01995 -0.0511 0.9989 0.0237
-11.500 -1.0756 0.02504 0.01893 -0.0530 0.9982 0.0241
-11.250 -1.0471 0.02413 0.01795 -0.0548 0.9975 0.0245
-11.000 -1.0178 0.02328 0.01703 -0.0567 0.9968 0.0249
-10.750 -0.9878 0.02247 0.01616 -0.0585 0.9962 0.0254
-10.500 -0.9574 0.02173 0.01534 -0.0604 0.9957 0.0258
-10.250 -0.9263 0.02105 0.01459 -0.0622 0.9951 0.0262
-10.000 -0.8944 0.02029 0.01380 -0.0643 0.9947 0.0268
-9.750 -0.8621 0.01966 0.01316 -0.0663 0.9942 0.0275
-9.500 -0.8298 0.01912 0.01259 -0.0681 0.9939 0.0282
-9.250 -0.7984 0.01862 0.01206 -0.0697 0.9933 0.0289
-9.000 -0.7677 0.01815 0.01155 -0.0710 0.9927 0.0298
-8.750 -0.7365 0.01771 0.01106 -0.0724 0.9920 0.0306
-8.500 -0.7046 0.01724 0.01060 -0.0739 0.9914 0.0317
-8.250 -0.6729 0.01688 0.01025 -0.0753 0.9908 0.0329
-8.000 -0.6410 0.01655 0.00990 -0.0767 0.9902 0.0343
-7.750 -0.6088 0.01623 0.00959 -0.0781 0.9897 0.0359
-7.500 -0.5768 0.01601 0.00940 -0.0793 0.9891 0.0375
-7.250 -0.5443 0.01578 0.00916 -0.0807 0.9885 0.0392
-7.000 -0.5114 0.01556 0.00895 -0.0821 0.9880 0.0409
-6.750 -0.4789 0.01540 0.00881 -0.0834 0.9875 0.0427
-6.500 -0.4463 0.01523 0.00862 -0.0846 0.9871 0.0451
-6.250 -0.4137 0.01508 0.00848 -0.0859 0.9867 0.0469
-6.000 -0.3813 0.01496 0.00837 -0.0871 0.9863 0.0492
-5.750 -0.3487 0.01486 0.00824 -0.0882 0.9859 0.0512
-5.500 -0.3149 0.01462 0.00803 -0.0899 0.9857 0.0529
-5.250 -0.2816 0.01447 0.00789 -0.0913 0.9854 0.0549
-5.000 -0.2512 0.01435 0.00777 -0.0920 0.9843 0.0567
-4.750 -0.2175 0.01409 0.00753 -0.0936 0.9836 0.0584
-4.500 -0.1836 0.01387 0.00735 -0.0952 0.9829 0.0599
-4.250 -0.1504 0.01372 0.00721 -0.0965 0.9824 0.0618
-4.000 -0.1175 0.01361 0.00711 -0.0978 0.9818 0.0632
-3.750 -0.0837 0.01346 0.00700 -0.0993 0.9813 0.0647
-3.500 -0.0496 0.01332 0.00689 -0.1008 0.9810 0.0667
-3.250 -0.0158 0.01321 0.00681 -0.1023 0.9805 0.0690
-3.000 0.0181 0.01312 0.00675 -0.1037 0.9800 0.0710
-2.750 0.0525 0.01304 0.00673 -0.1052 0.9796 0.0740
-2.500 0.0963 0.01268 0.00655 -0.1088 0.9786 0.1023
-2.250 0.1505 0.01194 0.00594 -0.1143 0.9730 0.1279
-2.000 0.1994 0.01135 0.00552 -0.1189 0.9687 0.1626
-1.750 0.2516 0.01066 0.00505 -0.1242 0.9640 0.2160
-1.250 0.3882 0.00846 0.00310 -0.1426 0.6896 0.5647
-1.000 0.3992 0.01041 0.00383 -0.1389 0.3797 0.6134
-0.750 0.4241 0.01112 0.00416 -0.1381 0.2831 0.6336
-0.500 0.4500 0.01170 0.00443 -0.1375 0.2113 0.6445
-0.250 0.4768 0.01219 0.00465 -0.1372 0.1509 0.6503
0.000 0.5029 0.01265 0.00490 -0.1366 0.1061 0.6533
0.250 0.5300 0.01296 0.00512 -0.1362 0.0889 0.6563
0.500 0.5578 0.01321 0.00532 -0.1359 0.0800 0.6594
0.750 0.5861 0.01346 0.00551 -0.1358 0.0735 0.6629
1.000 0.6151 0.01369 0.00568 -0.1359 0.0684 0.6659
1.250 0.6432 0.01390 0.00585 -0.1357 0.0639 0.6680
1.500 0.6700 0.01417 0.00610 -0.1352 0.0599 0.6698
1.750 0.6972 0.01438 0.00633 -0.1348 0.0573 0.6715
2.000 0.7243 0.01464 0.00657 -0.1344 0.0546 0.6733
2.250 0.7516 0.01492 0.00681 -0.1341 0.0520 0.6749
2.500 0.7792 0.01516 0.00706 -0.1338 0.0501 0.6768
2.750 0.8068 0.01540 0.00730 -0.1335 0.0481 0.6788
3.000 0.8345 0.01567 0.00754 -0.1333 0.0463 0.6811
3.250 0.8621 0.01598 0.00781 -0.1331 0.0444 0.6823
3.500 0.8901 0.01622 0.00805 -0.1330 0.0431 0.6833
3.750 0.9180 0.01647 0.00830 -0.1329 0.0417 0.6840
4.000 0.9456 0.01673 0.00856 -0.1327 0.0405 0.6846
4.250 0.9730 0.01703 0.00885 -0.1324 0.0393 0.6851
4.500 0.9998 0.01741 0.00920 -0.1321 0.0381 0.6856
4.750 1.0267 0.01772 0.00953 -0.1318 0.0373 0.6862
5.000 1.0535 0.01801 0.00986 -0.1314 0.0363 0.6868
5.250 1.0801 0.01831 0.01019 -0.1310 0.0353 0.6873
5.500 1.1065 0.01863 0.01053 -0.1305 0.0343 0.6878
5.750 1.1327 0.01896 0.01086 -0.1301 0.0334 0.6883
6.000 1.1581 0.01943 0.01134 -0.1295 0.0324 0.6889
6.250 1.1840 0.01979 0.01174 -0.1289 0.0317 0.6894
6.500 1.2096 0.02016 0.01217 -0.1283 0.0309 0.6900
6.750 1.2350 0.02057 0.01263 -0.1277 0.0302 0.6905
7.000 1.2601 0.02100 0.01310 -0.1270 0.0296 0.6912
7.250 1.2850 0.02142 0.01356 -0.1263 0.0290 0.6919
7.500 1.3095 0.02187 0.01404 -0.1256 0.0284 0.6927
7.750 1.3335 0.02240 0.01460 -0.1247 0.0279 0.6934
8.000 1.3565 0.02306 0.01529 -0.1237 0.0274 0.6940
8.250 1.3803 0.02359 0.01590 -0.1228 0.0270 0.6946
8.500 1.4034 0.02417 0.01658 -0.1218 0.0266 0.6952
8.750 1.4262 0.02478 0.01726 -0.1207 0.0262 0.6958
9.000 1.4486 0.02540 0.01797 -0.1196 0.0258 0.6965
9.250 1.4705 0.02605 0.01869 -0.1184 0.0254 0.6971
9.500 1.4920 0.02669 0.01941 -0.1172 0.0250 0.6978
9.750 1.5130 0.02735 0.02015 -0.1159 0.0247 0.6984
10.000 1.5334 0.02802 0.02089 -0.1145 0.0244 0.6991
10.250 1.5531 0.02872 0.02166 -0.1130 0.0241 0.6997
10.500 1.5718 0.02947 0.02248 -0.1113 0.0238 0.7004
10.750 1.5892 0.03031 0.02339 -0.1095 0.0236 0.7010
11.000 1.6043 0.03129 0.02444 -0.1073 0.0233 0.7016
11.250 1.6179 0.03236 0.02563 -0.1048 0.0230 0.7022
11.500 1.6316 0.03333 0.02674 -0.1024 0.0229 0.7028
11.750 1.6432 0.03440 0.02795 -0.0996 0.0227 0.7035
12.000 1.6532 0.03553 0.02922 -0.0967 0.0225 0.7041
12.250 1.6603 0.03672 0.03056 -0.0933 0.0223 0.7047
12.500 1.6635 0.03798 0.03197 -0.0893 0.0222 0.7054
12.750 1.6674 0.03940 0.03355 -0.0857 0.0220 0.7060
13.000 1.6704 0.04095 0.03526 -0.0821 0.0218 0.7066
13.250 1.6718 0.04264 0.03711 -0.0786 0.0216 0.7072
13.500 1.6719 0.04448 0.03911 -0.0752 0.0215 0.7077
13.750 1.6703 0.04648 0.04127 -0.0718 0.0213 0.7083
14.000 1.6671 0.04872 0.04368 -0.0687 0.0212 0.7088
14.250 1.6611 0.05134 0.04646 -0.0658 0.0211 0.7094
14.500 1.6522 0.05440 0.04971 -0.0632 0.0210 0.7098
14.750 1.6430 0.05774 0.05322 -0.0614 0.0209 0.7103
15.000 1.6284 0.06203 0.05771 -0.0603 0.0208 0.7108
15.250 1.6126 0.06705 0.06291 -0.0606 0.0207 0.7112
15.500 1.5863 0.07462 0.07073 -0.0633 0.0207 0.7116
15.750 1.5456 0.08695 0.08338 -0.0713 0.0207 0.7117
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