DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.25 at α=-1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dsma523b-il-1000000.txt Download as CSV file: xf-dsma523b-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.1047 0.10514 0.10250 -0.0295 1.0000 0.0204
-17.750 -1.1590 0.09049 0.08758 -0.0382 1.0000 0.0203
-17.500 -1.1922 0.08045 0.07734 -0.0440 1.0000 0.0203
-17.250 -1.2147 0.07272 0.06944 -0.0484 1.0000 0.0203
-17.000 -1.2292 0.06669 0.06328 -0.0516 1.0000 0.0204
-16.750 -1.2416 0.06134 0.05779 -0.0542 1.0000 0.0204
-16.500 -1.2506 0.05685 0.05317 -0.0561 1.0000 0.0205
-16.250 -1.2565 0.05306 0.04928 -0.0573 1.0000 0.0206
-16.000 -1.2617 0.04968 0.04579 -0.0581 1.0000 0.0207
-15.750 -1.2663 0.04665 0.04265 -0.0583 1.0000 0.0208
-15.500 -1.2679 0.04411 0.04002 -0.0582 1.0000 0.0209
-15.250 -1.2698 0.04168 0.03749 -0.0578 1.0000 0.0210
-15.000 -1.2698 0.03955 0.03527 -0.0572 1.0000 0.0211
-14.750 -1.2685 0.03766 0.03330 -0.0563 1.0000 0.0213
-14.500 -1.2676 0.03589 0.03144 -0.0551 1.0000 0.0214
-14.250 -1.2654 0.03440 0.02987 -0.0536 1.0000 0.0216
-14.000 -1.2675 0.03292 0.02831 -0.0513 1.0000 0.0217
-13.750 -1.2712 0.03153 0.02685 -0.0485 1.0000 0.0218
-13.500 -1.2607 0.03030 0.02555 -0.0478 1.0000 0.0220
-13.250 -1.2468 0.02914 0.02432 -0.0476 1.0000 0.0222
-13.000 -1.2299 0.02811 0.02322 -0.0477 1.0000 0.0223
-12.750 -1.2147 0.02647 0.02148 -0.0482 1.0000 0.0226
-12.500 -1.1970 0.02482 0.01976 -0.0491 1.0000 0.0231
-12.250 -1.1749 0.02370 0.01860 -0.0501 1.0000 0.0234
-12.000 -1.1508 0.02278 0.01764 -0.0512 1.0000 0.0237
-11.750 -1.1253 0.02198 0.01681 -0.0524 1.0000 0.0240
-11.500 -1.0987 0.02125 0.01604 -0.0536 1.0000 0.0244
-11.250 -1.0714 0.02056 0.01531 -0.0548 1.0000 0.0248
-11.000 -1.0423 0.01992 0.01461 -0.0563 0.9999 0.0252
-10.750 -1.0097 0.01931 0.01396 -0.0583 0.9995 0.0256
-10.500 -0.9773 0.01878 0.01338 -0.0602 0.9990 0.0260
-10.250 -0.9450 0.01833 0.01287 -0.0619 0.9985 0.0263
-10.000 -0.9111 0.01737 0.01188 -0.0645 0.9983 0.0272
-9.750 -0.8777 0.01683 0.01134 -0.0665 0.9978 0.0279
-9.500 -0.8443 0.01642 0.01091 -0.0684 0.9973 0.0286
-9.250 -0.8111 0.01604 0.01051 -0.0701 0.9969 0.0293
-9.000 -0.7781 0.01571 0.01015 -0.0718 0.9965 0.0301
-8.750 -0.7452 0.01544 0.00984 -0.0733 0.9961 0.0306
-8.500 -0.7103 0.01488 0.00929 -0.0756 0.9960 0.0321
-8.250 -0.6768 0.01459 0.00902 -0.0772 0.9957 0.0332
-8.000 -0.6434 0.01435 0.00876 -0.0788 0.9954 0.0344
-7.750 -0.6096 0.01409 0.00849 -0.0805 0.9951 0.0357
-7.500 -0.5760 0.01389 0.00833 -0.0820 0.9948 0.0376
-7.250 -0.5429 0.01376 0.00821 -0.0834 0.9946 0.0393
-7.000 -0.5096 0.01364 0.00812 -0.0848 0.9943 0.0413
-6.750 -0.4768 0.01361 0.00812 -0.0860 0.9940 0.0434
-6.500 -0.4436 0.01361 0.00811 -0.0872 0.9937 0.0454
-6.250 -0.4134 0.01344 0.00798 -0.0879 0.9922 0.0474
-6.000 -0.3830 0.01341 0.00797 -0.0885 0.9913 0.0496
-5.750 -0.3517 0.01337 0.00793 -0.0893 0.9905 0.0516
-5.500 -0.3188 0.01323 0.00783 -0.0906 0.9900 0.0537
-5.250 -0.2868 0.01319 0.00779 -0.0916 0.9894 0.0560
-5.000 -0.2534 0.01305 0.00766 -0.0930 0.9890 0.0580
-4.750 -0.2180 0.01281 0.00745 -0.0950 0.9888 0.0601
-4.500 -0.1837 0.01268 0.00734 -0.0965 0.9884 0.0621
-4.250 -0.1499 0.01261 0.00727 -0.0979 0.9880 0.0635
-4.000 -0.1142 0.01242 0.00710 -0.0999 0.9878 0.0654
-3.750 -0.0795 0.01229 0.00700 -0.1015 0.9876 0.0670
-3.500 -0.0452 0.01220 0.00693 -0.1030 0.9873 0.0686
-3.250 -0.0087 0.01210 0.00685 -0.1050 0.9868 0.0700
-3.000 0.0444 0.01172 0.00650 -0.1103 0.9856 0.0722
-2.750 0.0903 0.01114 0.00598 -0.1140 0.9808 0.0759
-2.500 0.1401 0.01059 0.00560 -0.1188 0.9795 0.1067
-2.250 0.1934 0.00996 0.00513 -0.1243 0.9783 0.1363
-2.000 0.2386 0.00942 0.00477 -0.1281 0.9747 0.1803
-1.750 0.3293 0.00789 0.00370 -0.1426 0.9727 0.3078
-1.500 0.3949 0.00668 0.00301 -0.1516 0.9607 0.4785
-1.250 0.4285 0.00585 0.00241 -0.1525 0.9176 0.5980
-1.000 0.4346 0.00744 0.00278 -0.1471 0.6062 0.6149
-0.750 0.4545 0.00871 0.00312 -0.1455 0.3781 0.6278
-0.500 0.4794 0.00940 0.00341 -0.1447 0.2701 0.6387
-0.250 0.5052 0.01005 0.00368 -0.1441 0.1853 0.6490
0.000 0.5297 0.01069 0.00406 -0.1431 0.1117 0.6555
0.250 0.5563 0.01108 0.00434 -0.1425 0.0897 0.6603
0.500 0.5837 0.01140 0.00460 -0.1421 0.0795 0.6646
0.750 0.6114 0.01173 0.00485 -0.1418 0.0710 0.6673
1.000 0.6391 0.01187 0.00501 -0.1415 0.0672 0.6702
1.250 0.6661 0.01212 0.00523 -0.1410 0.0626 0.6722
1.500 0.6929 0.01240 0.00551 -0.1404 0.0592 0.6745
1.750 0.7198 0.01265 0.00576 -0.1399 0.0565 0.6775
2.000 0.7472 0.01291 0.00598 -0.1395 0.0535 0.6797
2.250 0.7751 0.01316 0.00621 -0.1393 0.0510 0.6810
2.500 0.8033 0.01333 0.00637 -0.1392 0.0493 0.6824
2.750 0.8311 0.01354 0.00656 -0.1389 0.0474 0.6838
3.000 0.8583 0.01386 0.00685 -0.1385 0.0454 0.6850
3.250 0.8860 0.01413 0.00712 -0.1383 0.0438 0.6862
3.500 0.9142 0.01423 0.00723 -0.1382 0.0427 0.6883
3.750 0.9414 0.01442 0.00743 -0.1379 0.0415 0.6898
4.000 0.9685 0.01465 0.00766 -0.1375 0.0403 0.6908
4.250 0.9957 0.01495 0.00794 -0.1372 0.0389 0.6914
4.500 1.0222 0.01536 0.00836 -0.1367 0.0377 0.6920
4.750 1.0496 0.01555 0.00858 -0.1364 0.0370 0.6927
5.000 1.0768 0.01579 0.00883 -0.1361 0.0361 0.6935
5.250 1.1040 0.01603 0.00908 -0.1358 0.0352 0.6941
5.500 1.1311 0.01628 0.00932 -0.1355 0.0343 0.6946
5.750 1.1575 0.01662 0.00965 -0.1350 0.0334 0.6952
6.000 1.1823 0.01725 0.01031 -0.1343 0.0322 0.6958
6.250 1.2091 0.01749 0.01057 -0.1339 0.0318 0.6964
6.500 1.2356 0.01778 0.01089 -0.1334 0.0312 0.6970
6.750 1.2618 0.01810 0.01125 -0.1329 0.0306 0.6976
7.000 1.2877 0.01844 0.01160 -0.1324 0.0300 0.6982
7.250 1.3135 0.01876 0.01194 -0.1318 0.0294 0.6988
7.500 1.3390 0.01913 0.01231 -0.1312 0.0288 0.6994
7.750 1.3633 0.01965 0.01285 -0.1304 0.0282 0.7000
8.000 1.3846 0.02066 0.01392 -0.1290 0.0274 0.7005
8.250 1.4097 0.02100 0.01431 -0.1283 0.0272 0.7011
8.500 1.4340 0.02144 0.01480 -0.1275 0.0269 0.7016
8.750 1.4581 0.02189 0.01531 -0.1266 0.0266 0.7022
9.000 1.4815 0.02239 0.01586 -0.1256 0.0262 0.7028
9.250 1.5045 0.02292 0.01645 -0.1245 0.0259 0.7033
9.500 1.5274 0.02342 0.01700 -0.1235 0.0255 0.7038
9.750 1.5498 0.02393 0.01755 -0.1224 0.0251 0.7041
10.000 1.5719 0.02444 0.01810 -0.1212 0.0248 0.7044
10.250 1.5934 0.02498 0.01869 -0.1199 0.0245 0.7047
10.500 1.6148 0.02552 0.01927 -0.1187 0.0242 0.7056
10.750 1.6343 0.02622 0.02001 -0.1171 0.0238 0.7064
11.000 1.6462 0.02786 0.02179 -0.1143 0.0231 0.7071
11.250 1.6654 0.02843 0.02244 -0.1127 0.0230 0.7078
11.500 1.6837 0.02901 0.02311 -0.1109 0.0228 0.7084
11.750 1.7002 0.02971 0.02389 -0.1088 0.0226 0.7090
12.000 1.7159 0.03039 0.02466 -0.1066 0.0223 0.7096
12.250 1.7289 0.03124 0.02562 -0.1039 0.0221 0.7102
12.500 1.7407 0.03213 0.02661 -0.1011 0.0219 0.7108
12.750 1.7508 0.03307 0.02766 -0.0981 0.0217 0.7114
13.000 1.7565 0.03404 0.02872 -0.0942 0.0215 0.7121
13.250 1.7619 0.03511 0.02990 -0.0905 0.0213 0.7127
13.500 1.7672 0.03631 0.03120 -0.0870 0.0212 0.7133
13.750 1.7730 0.03748 0.03247 -0.0836 0.0210 0.7141
14.000 1.7773 0.03881 0.03389 -0.0803 0.0208 0.7149
14.250 1.7795 0.04034 0.03552 -0.0768 0.0207 0.7157
14.500 1.7803 0.04201 0.03730 -0.0735 0.0206 0.7163
14.750 1.7815 0.04370 0.03909 -0.0704 0.0204 0.7169
15.000 1.7781 0.04589 0.04141 -0.0672 0.0204 0.7175
15.250 1.7754 0.04811 0.04374 -0.0644 0.0202 0.7180
15.500 1.7671 0.05104 0.04680 -0.0618 0.0202 0.7185
15.750 1.7581 0.05426 0.05015 -0.0597 0.0201 0.7190
16.000 1.7451 0.05822 0.05426 -0.0584 0.0200 0.7194
16.250 1.7289 0.06308 0.05928 -0.0582 0.0199 0.7198
16.500 1.7077 0.06943 0.06582 -0.0597 0.0199 0.7202
16.750 1.6808 0.07787 0.07447 -0.0638 0.0199 0.7204
17.000 1.6440 0.08990 0.08677 -0.0717 0.0199 0.7205
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