SA7038 (sa7038-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 50,000 Max Cl/Cd: 39.67 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7038-il-50000-n5.txt Download as CSV file: xf-sa7038-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3585 0.09563 0.08881 -0.0341 1.0000 0.0591
-8.000 -0.3626 0.09222 0.08552 -0.0348 1.0000 0.0554
-7.750 -0.3781 0.08872 0.08215 -0.0369 1.0000 0.0503
-7.500 -0.3793 0.08599 0.07951 -0.0359 1.0000 0.0493
-7.250 -0.3828 0.08292 0.07654 -0.0361 1.0000 0.0486
-7.000 -0.3868 0.07971 0.07341 -0.0368 1.0000 0.0480
-6.750 -0.3903 0.07632 0.07009 -0.0376 1.0000 0.0473
-6.500 -0.3929 0.07276 0.06656 -0.0387 1.0000 0.0470
-6.250 -0.3937 0.06903 0.06284 -0.0398 1.0000 0.0462
-6.000 -0.3926 0.06509 0.05885 -0.0411 1.0000 0.0461
-5.750 -0.3888 0.06104 0.05471 -0.0424 1.0000 0.0458
-5.500 -0.3821 0.05692 0.05043 -0.0437 1.0000 0.0458
-5.250 -0.3721 0.05285 0.04614 -0.0450 1.0000 0.0456
-5.000 -0.3588 0.04877 0.04176 -0.0463 1.0000 0.0452
-4.750 -0.3423 0.04477 0.03736 -0.0474 1.0000 0.0447
-4.500 -0.3230 0.04112 0.03326 -0.0483 1.0000 0.0442
-4.250 -0.3017 0.03788 0.02953 -0.0488 1.0000 0.0441
-4.000 -0.2789 0.03507 0.02622 -0.0490 1.0000 0.0444
-3.750 -0.2554 0.03273 0.02338 -0.0489 1.0000 0.0449
-3.500 -0.2302 0.03069 0.02089 -0.0489 0.9995 0.0459
-3.250 -0.1920 0.02876 0.01848 -0.0509 0.9938 0.0477
-3.000 -0.1550 0.02731 0.01662 -0.0526 0.9873 0.0520
-2.750 -0.1186 0.02617 0.01538 -0.0545 0.9807 0.0594
-2.500 -0.0821 0.02506 0.01402 -0.0560 0.9735 0.0669
-2.250 -0.0446 0.02409 0.01297 -0.0580 0.9661 0.0877
-2.000 -0.0061 0.02263 0.01211 -0.0608 0.9591 0.1905
-1.750 0.0253 0.02102 0.01191 -0.0621 0.9516 0.4776
-1.500 0.0482 0.02008 0.01195 -0.0593 0.9436 0.7661
-1.250 0.0954 0.01980 0.01144 -0.0626 0.9335 1.0000
-1.000 0.1330 0.02000 0.01120 -0.0647 0.9233 1.0000
-0.750 0.1745 0.02018 0.01098 -0.0675 0.9143 1.0000
-0.500 0.2083 0.02034 0.01084 -0.0688 0.9023 1.0000
-0.250 0.2427 0.02049 0.01074 -0.0702 0.8905 1.0000
0.000 0.2780 0.02062 0.01064 -0.0716 0.8791 1.0000
0.250 0.3139 0.02072 0.01055 -0.0730 0.8680 1.0000
0.500 0.3514 0.02075 0.01042 -0.0746 0.8576 1.0000
0.750 0.3823 0.02083 0.01036 -0.0750 0.8446 1.0000
1.000 0.4133 0.02090 0.01032 -0.0753 0.8314 1.0000
1.250 0.4443 0.02094 0.01027 -0.0756 0.8180 1.0000
1.500 0.4751 0.02096 0.01023 -0.0757 0.8043 1.0000
1.750 0.5056 0.02096 0.01018 -0.0758 0.7903 1.0000
2.000 0.5359 0.02096 0.01013 -0.0757 0.7759 1.0000
2.250 0.5659 0.02095 0.01011 -0.0756 0.7612 1.0000
2.500 0.5958 0.02094 0.01006 -0.0753 0.7461 1.0000
2.750 0.6256 0.02093 0.01002 -0.0750 0.7307 1.0000
3.000 0.6521 0.02103 0.01012 -0.0743 0.7127 1.0000
3.250 0.6797 0.02110 0.01022 -0.0737 0.6948 1.0000
3.500 0.7080 0.02115 0.01025 -0.0732 0.6770 1.0000
3.750 0.7361 0.02122 0.01030 -0.0726 0.6587 1.0000
4.000 0.7613 0.02143 0.01053 -0.0717 0.6380 1.0000
4.250 0.7883 0.02158 0.01071 -0.0709 0.6184 1.0000
4.500 0.8132 0.02185 0.01099 -0.0700 0.5972 1.0000
4.750 0.8387 0.02210 0.01124 -0.0691 0.5763 1.0000
5.000 0.8629 0.02244 0.01159 -0.0682 0.5545 1.0000
5.250 0.8876 0.02278 0.01198 -0.0672 0.5329 1.0000
5.500 0.9106 0.02321 0.01244 -0.0662 0.5102 1.0000
5.750 0.9345 0.02362 0.01284 -0.0652 0.4885 1.0000
6.000 0.9563 0.02414 0.01342 -0.0640 0.4652 1.0000
6.250 0.9787 0.02467 0.01396 -0.0629 0.4431 1.0000
6.500 1.0002 0.02526 0.01464 -0.0618 0.4207 1.0000
6.750 1.0213 0.02589 0.01532 -0.0606 0.3984 1.0000
7.000 1.0420 0.02656 0.01602 -0.0594 0.3768 1.0000
7.250 1.0615 0.02731 0.01684 -0.0582 0.3547 1.0000
7.500 1.0808 0.02807 0.01768 -0.0569 0.3337 1.0000
7.750 1.0992 0.02893 0.01863 -0.0555 0.3128 1.0000
8.000 1.1170 0.02982 0.01958 -0.0541 0.2928 1.0000
8.250 1.1343 0.03079 0.02061 -0.0527 0.2737 1.0000
8.500 1.1501 0.03184 0.02177 -0.0512 0.2542 1.0000
8.750 1.1654 0.03294 0.02293 -0.0497 0.2364 1.0000
9.000 1.1791 0.03410 0.02419 -0.0480 0.2189 1.0000
9.250 1.1915 0.03539 0.02562 -0.0463 0.2018 1.0000
9.500 1.2018 0.03673 0.02707 -0.0444 0.1852 1.0000
9.750 1.2112 0.03818 0.02861 -0.0425 0.1702 1.0000
10.000 1.2183 0.03970 0.03023 -0.0404 0.1566 1.0000
10.250 1.2246 0.04137 0.03201 -0.0383 0.1443 1.0000
10.500 1.2289 0.04316 0.03390 -0.0362 0.1328 1.0000
10.750 1.2323 0.04507 0.03586 -0.0342 0.1228 1.0000
11.000 1.2361 0.04719 0.03812 -0.0325 0.1134 1.0000
11.250 1.2375 0.04960 0.04074 -0.0309 0.1047 1.0000
11.500 1.2378 0.05196 0.04319 -0.0295 0.0974 1.0000
11.750 1.2376 0.05482 0.04634 -0.0283 0.0904 1.0000
12.000 1.2385 0.05757 0.04913 -0.0273 0.0849 1.0000
12.250 1.2329 0.06111 0.05301 -0.0267 0.0794 1.0000
12.500 1.2306 0.06406 0.05594 -0.0264 0.0745 1.0000
12.750 1.2229 0.06841 0.06063 -0.0265 0.0709 1.0000
13.000 1.2134 0.07313 0.06565 -0.0271 0.0678 1.0000
13.250 1.2048 0.07763 0.07032 -0.0281 0.0649 1.0000
13.500 1.2008 0.08143 0.07408 -0.0288 0.0613 1.0000
13.750 1.1821 0.08813 0.08112 -0.0316 0.0602 1.0000
14.000 1.1623 0.09549 0.08876 -0.0351 0.0595 1.0000
14.250 1.1411 0.10369 0.09719 -0.0395 0.0595 1.0000
14.500 1.1170 0.11315 0.10685 -0.0449 0.0600 1.0000
14.750 1.0922 0.12363 0.11745 -0.0511 0.0608 1.0000
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Polar data table (+)
Polar graphs
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