DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DSMA-523B AIRFOIL (dsma523b-il) Reynolds number: 500,000 Max Cl/Cd: 49.56 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dsma523b-il-500000.txt Download as CSV file: xf-dsma523b-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7695 0.08154 0.07853 -0.0458 1.0000 0.0304
-14.000 -0.7825 0.10797 0.10511 -0.0254 1.0000 0.0307
-13.750 -0.9417 0.06939 0.06600 -0.0514 1.0000 0.0295
-13.500 -0.9905 0.05995 0.05628 -0.0557 1.0000 0.0293
-13.250 -1.0285 0.05327 0.04932 -0.0568 1.0000 0.0292
-13.000 -1.0568 0.04853 0.04433 -0.0560 1.0000 0.0292
-12.750 -1.0819 0.04505 0.04066 -0.0535 1.0000 0.0293
-12.500 -1.0988 0.04179 0.03719 -0.0515 1.0000 0.0294
-12.250 -1.1010 0.03834 0.03347 -0.0518 1.0000 0.0296
-12.000 -1.0938 0.03538 0.03025 -0.0526 1.0000 0.0299
-11.750 -1.0799 0.03296 0.02758 -0.0537 1.0000 0.0302
-11.500 -1.0619 0.03111 0.02549 -0.0546 1.0000 0.0305
-11.250 -1.0443 0.02897 0.02315 -0.0550 1.0000 0.0309
-11.000 -1.0245 0.02744 0.02156 -0.0550 1.0000 0.0313
-10.750 -1.0020 0.02647 0.02054 -0.0554 1.0000 0.0317
-10.500 -0.9782 0.02564 0.01966 -0.0558 1.0000 0.0322
-10.250 -0.9538 0.02481 0.01877 -0.0562 1.0000 0.0327
-10.000 -0.9287 0.02399 0.01788 -0.0567 1.0000 0.0333
-9.750 -0.9032 0.02315 0.01695 -0.0571 1.0000 0.0340
-9.500 -0.8771 0.02235 0.01604 -0.0576 1.0000 0.0347
-9.250 -0.8506 0.02157 0.01517 -0.0581 1.0000 0.0353
-9.000 -0.8237 0.02078 0.01438 -0.0587 1.0000 0.0362
-8.750 -0.7958 0.02038 0.01399 -0.0594 1.0000 0.0370
-8.500 -0.7677 0.01999 0.01357 -0.0600 1.0000 0.0379
-8.250 -0.7394 0.01957 0.01310 -0.0607 1.0000 0.0391
-8.000 -0.7108 0.01911 0.01257 -0.0613 1.0000 0.0403
-7.750 -0.6821 0.01877 0.01226 -0.0621 1.0000 0.0414
-7.500 -0.6534 0.01859 0.01208 -0.0627 1.0000 0.0426
-7.250 -0.6245 0.01836 0.01180 -0.0633 1.0000 0.0443
-7.000 -0.5953 0.01804 0.01145 -0.0640 1.0000 0.0460
-6.750 -0.5664 0.01783 0.01126 -0.0646 1.0000 0.0474
-6.500 -0.5372 0.01762 0.01103 -0.0652 1.0000 0.0493
-6.250 -0.5080 0.01748 0.01081 -0.0658 1.0000 0.0511
-6.000 -0.4771 0.01694 0.01038 -0.0669 1.0000 0.0532
-5.750 -0.4472 0.01672 0.01016 -0.0677 1.0000 0.0556
-5.500 -0.4150 0.01633 0.00978 -0.0690 1.0000 0.0585
-5.250 -0.3819 0.01596 0.00946 -0.0706 1.0000 0.0616
-5.000 -0.3471 0.01557 0.00909 -0.0725 1.0000 0.0648
-4.750 -0.3099 0.01514 0.00872 -0.0751 1.0000 0.0685
-4.500 -0.2750 0.01489 0.00848 -0.0771 1.0000 0.0718
-4.250 -0.2394 0.01465 0.00830 -0.0791 1.0000 0.0755
-4.000 -0.2066 0.01455 0.00822 -0.0805 1.0000 0.0786
-3.750 -0.1736 0.01445 0.00820 -0.0819 1.0000 0.0842
-3.250 -0.1062 0.01428 0.00828 -0.0850 1.0000 0.1218
-3.000 -0.0675 0.01408 0.00833 -0.0878 1.0000 0.1725
-2.750 -0.0253 0.01383 0.00840 -0.0914 1.0000 0.2438
-2.500 0.0269 0.01338 0.00842 -0.0975 1.0000 0.3627
-2.250 0.0874 0.01285 0.00879 -0.1052 1.0000 0.5823
-2.000 0.1145 0.01309 0.00910 -0.1048 0.9993 0.6132
-1.750 0.1726 0.01290 0.00889 -0.1108 0.9940 0.6315
-1.500 0.2229 0.01259 0.00861 -0.1150 0.9873 0.6415
-1.250 0.2822 0.01198 0.00799 -0.1211 0.9799 0.6503
-1.000 0.3328 0.01148 0.00757 -0.1250 0.9729 0.6574
-0.750 0.3837 0.01104 0.00717 -0.1289 0.9662 0.6689
-0.500 0.3676 0.01122 0.00744 -0.1185 0.9336 0.6720
-0.250 0.4715 0.00990 0.00610 -0.1332 0.9073 0.6819
0.000 0.4941 0.01232 0.00634 -0.1317 0.4239 0.6861
0.250 0.5130 0.01331 0.00668 -0.1297 0.2667 0.6883
0.500 0.5334 0.01422 0.00705 -0.1279 0.1441 0.6905
0.750 0.5557 0.01481 0.00744 -0.1263 0.1030 0.6933
1.000 0.5802 0.01522 0.00779 -0.1251 0.0905 0.6966
1.250 0.6075 0.01562 0.00811 -0.1248 0.0815 0.7002
1.500 0.6389 0.01594 0.00838 -0.1256 0.0763 0.7044
1.750 0.6644 0.01624 0.00864 -0.1248 0.0711 0.7066
2.000 0.6889 0.01651 0.00895 -0.1237 0.0684 0.7085
2.250 0.7138 0.01676 0.00922 -0.1227 0.0654 0.7102
2.500 0.7390 0.01707 0.00951 -0.1218 0.0625 0.7121
2.750 0.7635 0.01763 0.01006 -0.1209 0.0598 0.7143
3.000 0.7902 0.01790 0.01036 -0.1203 0.0580 0.7177
3.250 0.8195 0.01816 0.01060 -0.1206 0.0557 0.7203
3.500 0.8493 0.01844 0.01084 -0.1210 0.0537 0.7217
3.750 0.8769 0.01922 0.01157 -0.1211 0.0515 0.7230
4.000 0.9066 0.01949 0.01185 -0.1214 0.0504 0.7236
4.250 0.9354 0.01977 0.01216 -0.1215 0.0489 0.7243
4.500 0.9632 0.02004 0.01244 -0.1215 0.0475 0.7249
4.750 0.9906 0.02034 0.01273 -0.1213 0.0461 0.7256
5.000 1.0161 0.02125 0.01360 -0.1209 0.0444 0.7261
5.250 1.0433 0.02161 0.01404 -0.1206 0.0434 0.7267
5.500 1.0703 0.02195 0.01443 -0.1204 0.0422 0.7273
5.750 1.0972 0.02228 0.01479 -0.1201 0.0409 0.7279
6.000 1.1236 0.02268 0.01520 -0.1197 0.0399 0.7286
6.250 1.1494 0.02319 0.01571 -0.1193 0.0390 0.7293
6.500 1.1737 0.02465 0.01720 -0.1187 0.0378 0.7302
6.750 1.1994 0.02513 0.01779 -0.1181 0.0373 0.7310
7.000 1.2250 0.02578 0.01856 -0.1175 0.0366 0.7317
7.250 1.2502 0.02652 0.01940 -0.1170 0.0359 0.7323
7.500 1.2750 0.02727 0.02022 -0.1164 0.0352 0.7329
7.750 1.2993 0.02803 0.02107 -0.1157 0.0346 0.7336
8.000 1.3233 0.02875 0.02186 -0.1150 0.0340 0.7342
8.250 1.3468 0.02947 0.02262 -0.1142 0.0335 0.7349
8.500 1.3694 0.03047 0.02367 -0.1134 0.0330 0.7356
8.750 1.3876 0.03308 0.02646 -0.1120 0.0323 0.7362
9.000 1.4075 0.03408 0.02765 -0.1106 0.0320 0.7369
9.250 1.4254 0.03545 0.02925 -0.1088 0.0317 0.7375
9.500 1.4411 0.03709 0.03115 -0.1068 0.0312 0.7382
9.750 1.4538 0.03907 0.03341 -0.1044 0.0308 0.7388
10.000 1.4632 0.04131 0.03592 -0.1015 0.0304 0.7395
10.250 1.4686 0.04385 0.03874 -0.0982 0.0300 0.7402
10.500 1.4710 0.04639 0.04156 -0.0946 0.0297 0.7410
10.750 1.4662 0.04944 0.04490 -0.0901 0.0295 0.7415
11.000 1.4597 0.05192 0.04759 -0.0854 0.0292 0.7419
11.250 1.4232 0.05633 0.05237 -0.0771 0.0292 0.7421
11.500 1.3822 0.06182 0.05823 -0.0702 0.0292 0.7422
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