SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 50,000 Max Cl/Cd: 29.32 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7003-il-50000.txt Download as CSV file: xf-sd7003-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD7003-085-88
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 -0.4952 0.10034 0.09346 0.0092 1.0000 0.2808
-8.000 -0.4923 0.09715 0.09033 0.0092 1.0000 0.2943
-7.750 -0.4895 0.09396 0.08720 0.0093 1.0000 0.3084
-7.250 -0.4816 0.08744 0.08077 0.0101 1.0000 0.3379
-7.000 -0.4743 0.08438 0.07776 0.0113 1.0000 0.3600
-6.750 -0.4777 0.08177 0.07525 0.0124 1.0000 0.3804
-6.500 -0.4618 0.07787 0.07134 0.0137 1.0000 0.3992
-6.250 -0.4576 0.07472 0.06825 0.0147 1.0000 0.4155
-6.000 -0.5038 0.04834 0.04068 -0.0336 1.0000 0.1408
-5.750 -0.4874 0.04356 0.03541 -0.0346 1.0000 0.1412
-5.500 -0.4683 0.03918 0.03025 -0.0353 1.0000 0.1432
-5.250 -0.4472 0.03586 0.02688 -0.0348 1.0000 0.1481
-5.000 -0.4242 0.03291 0.02321 -0.0346 1.0000 0.1575
-4.750 -0.4011 0.03035 0.02057 -0.0338 1.0000 0.1674
-4.500 -0.3774 0.02822 0.01818 -0.0331 1.0000 0.1828
-4.250 -0.3528 0.02623 0.01592 -0.0323 1.0000 0.1996
-4.000 -0.3287 0.02449 0.01415 -0.0314 1.0000 0.2201
-3.750 -0.3046 0.02301 0.01264 -0.0304 1.0000 0.2477
-3.500 -0.2806 0.02155 0.01130 -0.0293 1.0000 0.2809
-3.250 -0.2573 0.02020 0.01014 -0.0280 1.0000 0.3342
-3.000 -0.2359 0.01867 0.00919 -0.0263 1.0000 0.4229
-2.750 -0.2221 0.01715 0.00877 -0.0222 1.0000 0.5774
-2.500 -0.2185 0.01642 0.00883 -0.0145 1.0000 0.7412
-2.250 -0.1949 0.01612 0.00869 -0.0088 1.0000 0.9125
-2.000 -0.0848 0.01570 0.00744 -0.0246 1.0000 1.0000
-1.750 -0.0821 0.01541 0.00698 -0.0218 1.0000 1.0000
-1.500 -0.0722 0.01529 0.00666 -0.0198 1.0000 1.0000
-1.250 -0.0572 0.01527 0.00644 -0.0185 1.0000 1.0000
-1.000 -0.0401 0.01533 0.00631 -0.0175 1.0000 1.0000
-0.750 -0.0222 0.01545 0.00627 -0.0166 1.0000 1.0000
-0.500 -0.0040 0.01564 0.00629 -0.0159 1.0000 1.0000
-0.250 0.0139 0.01589 0.00642 -0.0152 1.0000 1.0000
0.000 0.0315 0.01621 0.00663 -0.0147 1.0000 1.0000
0.250 0.0487 0.01661 0.00695 -0.0142 1.0000 1.0000
0.500 0.0652 0.01711 0.00735 -0.0139 1.0000 1.0000
0.750 0.0812 0.01769 0.00788 -0.0138 1.0000 1.0000
1.000 0.0965 0.01838 0.00852 -0.0139 1.0000 1.0000
1.250 0.1671 0.01954 0.00968 -0.0237 0.9728 1.0000
1.500 0.2442 0.02031 0.01051 -0.0338 0.9415 1.0000
1.750 0.3133 0.02063 0.01095 -0.0414 0.9080 1.0000
2.000 0.3804 0.02063 0.01109 -0.0477 0.8753 1.0000
2.250 0.4344 0.02049 0.01107 -0.0507 0.8420 1.0000
2.500 0.4767 0.02037 0.01100 -0.0512 0.8088 1.0000
2.750 0.5058 0.02051 0.01114 -0.0497 0.7731 1.0000
3.000 0.5329 0.02067 0.01130 -0.0477 0.7387 1.0000
3.250 0.5585 0.02086 0.01143 -0.0454 0.7052 1.0000
3.500 0.5814 0.02125 0.01178 -0.0431 0.6697 1.0000
3.750 0.6048 0.02164 0.01210 -0.0409 0.6353 1.0000
4.000 0.6284 0.02205 0.01244 -0.0388 0.6022 1.0000
4.250 0.6514 0.02260 0.01292 -0.0369 0.5682 1.0000
4.500 0.6745 0.02322 0.01349 -0.0352 0.5346 1.0000
4.750 0.6979 0.02388 0.01407 -0.0335 0.5026 1.0000
5.000 0.7213 0.02460 0.01474 -0.0319 0.4714 1.0000
5.250 0.7447 0.02542 0.01551 -0.0305 0.4415 1.0000
5.500 0.7680 0.02633 0.01638 -0.0292 0.4126 1.0000
5.750 0.7910 0.02734 0.01741 -0.0279 0.3850 1.0000
6.000 0.8141 0.02847 0.01857 -0.0268 0.3592 1.0000
6.250 0.8379 0.02951 0.01950 -0.0256 0.3353 1.0000
6.500 0.8595 0.03099 0.02117 -0.0246 0.3118 1.0000
6.750 0.8824 0.03229 0.02245 -0.0234 0.2903 1.0000
7.000 0.9030 0.03408 0.02451 -0.0224 0.2701 1.0000
7.250 0.9254 0.03549 0.02590 -0.0213 0.2505 1.0000
7.500 0.9467 0.03745 0.02794 -0.0203 0.2337 1.0000
7.750 0.9634 0.03974 0.03058 -0.0192 0.2166 1.0000
8.000 0.9808 0.04233 0.03342 -0.0181 0.2025 1.0000
8.250 0.9960 0.04487 0.03620 -0.0170 0.1879 1.0000
8.500 1.0125 0.04763 0.03915 -0.0159 0.1757 1.0000
8.750 1.0285 0.05015 0.04176 -0.0148 0.1628 1.0000
9.000 1.0200 0.05590 0.04830 -0.0140 0.1585 1.0000
9.250 1.0360 0.05852 0.05091 -0.0129 0.1481 1.0000
9.500 1.0184 0.06484 0.05775 -0.0129 0.1470 1.0000
9.750 0.9971 0.07137 0.06457 -0.0137 0.1471 1.0000
10.000 0.9750 0.07792 0.07126 -0.0151 0.1480 1.0000
10.250 0.9540 0.08433 0.07770 -0.0168 0.1489 1.0000
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Polar data table (+)
Polar graphs
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