SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 50,000 Max Cl/Cd: 31.27 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7084-il-50000.txt Download as CSV file: xf-sd7084-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD7084 (9.6%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3984 0.09801 0.09132 -0.0142 1.0000 0.2779
-8.000 -0.3994 0.09528 0.08867 -0.0138 1.0000 0.2904
-7.750 -0.3964 0.09244 0.08589 -0.0129 1.0000 0.3050
-7.500 -0.3894 0.08947 0.08297 -0.0116 1.0000 0.3223
-7.250 -0.3918 0.08726 0.08085 -0.0100 1.0000 0.3417
-7.000 -0.4025 0.08562 0.07935 -0.0081 1.0000 0.3583
-6.750 -0.3844 0.08162 0.07534 -0.0062 1.0000 0.3785
-6.500 -0.3832 0.07913 0.07292 -0.0038 1.0000 0.3976
-6.250 -0.4098 0.07870 0.07270 0.0005 1.0000 0.4169
-5.250 -0.4525 0.05064 0.04350 -0.0322 1.0000 0.1564
-5.000 -0.4385 0.04586 0.03818 -0.0322 1.0000 0.1420
-4.750 -0.4229 0.04220 0.03432 -0.0313 1.0000 0.1363
-4.500 -0.4042 0.03842 0.02965 -0.0306 1.0000 0.1278
-4.250 -0.3848 0.03550 0.02637 -0.0295 1.0000 0.1259
-4.000 -0.3637 0.03294 0.02337 -0.0285 1.0000 0.1252
-3.750 -0.3413 0.03092 0.02073 -0.0273 1.0000 0.1284
-3.500 -0.3200 0.02902 0.01881 -0.0263 1.0000 0.1359
-3.250 -0.2958 0.02738 0.01674 -0.0252 1.0000 0.1418
-3.000 -0.2719 0.02576 0.01509 -0.0241 1.0000 0.1511
-2.750 -0.2478 0.02446 0.01374 -0.0231 1.0000 0.1735
-2.500 -0.2228 0.02304 0.01244 -0.0221 1.0000 0.2136
-2.250 -0.1486 0.01831 0.01118 -0.0249 1.0000 1.0000
-2.000 -0.1368 0.01829 0.01067 -0.0231 1.0000 1.0000
-1.750 -0.1225 0.01838 0.01035 -0.0216 1.0000 1.0000
-1.500 -0.1069 0.01853 0.01014 -0.0203 1.0000 1.0000
-1.250 -0.0906 0.01874 0.01001 -0.0192 1.0000 1.0000
-1.000 -0.0739 0.01900 0.01000 -0.0181 1.0000 1.0000
-0.750 -0.0571 0.01932 0.01007 -0.0172 1.0000 1.0000
-0.500 -0.0403 0.01969 0.01022 -0.0164 1.0000 1.0000
-0.250 -0.0235 0.02011 0.01042 -0.0157 1.0000 1.0000
0.000 -0.0069 0.02059 0.01073 -0.0150 1.0000 1.0000
0.250 0.0094 0.02113 0.01112 -0.0144 1.0000 1.0000
0.500 0.0255 0.02174 0.01159 -0.0140 1.0000 1.0000
0.750 0.0413 0.02241 0.01215 -0.0136 1.0000 1.0000
1.000 0.0994 0.02389 0.01346 -0.0211 0.9820 1.0000
1.250 0.1569 0.02515 0.01462 -0.0282 0.9599 1.0000
1.500 0.2103 0.02618 0.01558 -0.0340 0.9374 1.0000
1.750 0.2677 0.02706 0.01644 -0.0402 0.9155 1.0000
2.000 0.3119 0.02765 0.01703 -0.0436 0.8916 1.0000
2.250 0.3641 0.02807 0.01749 -0.0480 0.8692 1.0000
2.500 0.4122 0.02829 0.01776 -0.0513 0.8461 1.0000
2.750 0.4576 0.02836 0.01792 -0.0539 0.8228 1.0000
3.000 0.5143 0.02794 0.01763 -0.0575 0.8021 1.0000
3.250 0.5517 0.02776 0.01756 -0.0580 0.7781 1.0000
3.500 0.6033 0.02691 0.01683 -0.0596 0.7582 1.0000
3.750 0.6347 0.02672 0.01671 -0.0588 0.7332 1.0000
4.000 0.6688 0.02637 0.01644 -0.0580 0.7089 1.0000
4.250 0.7067 0.02581 0.01596 -0.0573 0.6857 1.0000
4.500 0.7356 0.02574 0.01593 -0.0559 0.6599 1.0000
4.750 0.7617 0.02592 0.01614 -0.0543 0.6335 1.0000
5.000 0.7876 0.02619 0.01647 -0.0528 0.6077 1.0000
5.250 0.8142 0.02651 0.01678 -0.0513 0.5832 1.0000
5.500 0.8402 0.02691 0.01717 -0.0499 0.5589 1.0000
5.750 0.8615 0.02771 0.01803 -0.0484 0.5346 1.0000
6.000 0.8861 0.02834 0.01872 -0.0470 0.5121 1.0000
6.250 0.9081 0.02920 0.01965 -0.0456 0.4898 1.0000
6.500 0.9309 0.03007 0.02057 -0.0442 0.4687 1.0000
6.750 0.9518 0.03106 0.02167 -0.0428 0.4475 1.0000
7.000 0.9758 0.03194 0.02257 -0.0415 0.4276 1.0000
7.250 0.9934 0.03322 0.02408 -0.0398 0.4069 1.0000
7.500 1.0172 0.03413 0.02502 -0.0385 0.3870 1.0000
7.750 1.0339 0.03550 0.02659 -0.0368 0.3667 1.0000
8.000 1.0549 0.03653 0.02770 -0.0352 0.3456 1.0000
8.250 1.0721 0.03784 0.02916 -0.0333 0.3244 1.0000
8.500 1.0960 0.03846 0.02973 -0.0318 0.3000 1.0000
8.750 1.1078 0.03975 0.03125 -0.0293 0.2756 1.0000
9.000 1.1231 0.04053 0.03203 -0.0269 0.2473 1.0000
9.250 1.1392 0.04092 0.03217 -0.0244 0.2147 1.0000
9.500 1.1439 0.04213 0.03343 -0.0211 0.1842 1.0000
9.750 1.1481 0.04358 0.03481 -0.0178 0.1557 1.0000
10.000 1.1551 0.04536 0.03636 -0.0151 0.1320 1.0000
10.250 1.1569 0.04797 0.03915 -0.0123 0.1168 1.0000
10.500 1.1631 0.05087 0.04211 -0.0101 0.1052 1.0000
10.750 1.1618 0.05395 0.04557 -0.0075 0.0979 1.0000
11.000 1.1629 0.05755 0.04932 -0.0055 0.0925 1.0000
11.250 1.1492 0.06148 0.05367 -0.0027 0.0912 1.0000
11.500 1.1312 0.06542 0.05793 -0.0001 0.0907 1.0000
11.750 1.1086 0.06982 0.06259 0.0015 0.0906 1.0000
12.000 1.0844 0.07476 0.06776 0.0017 0.0911 1.0000
12.250 1.0586 0.08050 0.07368 0.0005 0.0920 1.0000
12.500 1.0339 0.08697 0.08023 -0.0020 0.0929 1.0000
12.750 1.0114 0.09409 0.08743 -0.0053 0.0938 1.0000
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Polar data table (+)
Polar graphs
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