SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 50,000 Max Cl/Cd: 26.14 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8020-il-50000.txt Download as CSV file: xf-sd8020-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD8020-010-88
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7449 0.07990 0.07297 -0.0233 1.0000 0.1347
-9.500 -0.7581 0.07484 0.06785 -0.0234 1.0000 0.1330
-9.250 -0.7728 0.06967 0.06260 -0.0234 1.0000 0.1320
-9.000 -0.7877 0.06454 0.05731 -0.0230 1.0000 0.1311
-8.750 -0.8002 0.05954 0.05204 -0.0219 1.0000 0.1307
-8.500 -0.8084 0.05476 0.04689 -0.0203 1.0000 0.1309
-8.250 -0.8125 0.05018 0.04180 -0.0183 1.0000 0.1319
-8.000 -0.8128 0.04595 0.03691 -0.0158 1.0000 0.1338
-7.750 -0.7955 0.04343 0.03448 -0.0145 1.0000 0.1435
-7.500 -0.7855 0.04026 0.03094 -0.0124 1.0000 0.1519
-7.250 -0.7744 0.03745 0.02759 -0.0100 1.0000 0.1625
-7.000 -0.7568 0.03525 0.02537 -0.0084 1.0000 0.1784
-6.750 -0.7386 0.03341 0.02352 -0.0067 1.0000 0.1973
-6.500 -0.7220 0.03150 0.02138 -0.0046 1.0000 0.2184
-6.250 -0.7029 0.02992 0.01991 -0.0029 1.0000 0.2423
-6.000 -0.6841 0.02837 0.01836 -0.0011 1.0000 0.2686
-5.750 -0.6650 0.02695 0.01698 0.0008 1.0000 0.2978
-5.500 -0.6463 0.02572 0.01583 0.0028 1.0000 0.3317
-5.250 -0.6275 0.02454 0.01474 0.0049 1.0000 0.3690
-5.000 -0.6091 0.02351 0.01386 0.0072 1.0000 0.4114
-4.750 -0.5907 0.02263 0.01322 0.0097 1.0000 0.4575
-4.500 -0.5723 0.02189 0.01270 0.0124 1.0000 0.5067
-4.250 -0.5546 0.02126 0.01224 0.0154 1.0000 0.5590
-4.000 -0.5359 0.02083 0.01203 0.0187 1.0000 0.6115
-3.750 -0.5171 0.02054 0.01190 0.0221 1.0000 0.6643
-3.500 -0.4967 0.02044 0.01190 0.0257 1.0000 0.7163
-3.250 -0.4730 0.02051 0.01198 0.0290 1.0000 0.7671
-3.000 -0.4354 0.02094 0.01234 0.0302 1.0000 0.8169
-2.750 -0.3721 0.02171 0.01284 0.0267 1.0000 0.8658
-2.500 -0.2653 0.02249 0.01312 0.0143 1.0000 0.9098
-2.250 -0.1644 0.02225 0.01248 0.0008 1.0000 0.9488
-2.000 -0.0706 0.02126 0.01119 -0.0130 1.0000 0.9852
-1.750 -0.0228 0.02021 0.01001 -0.0193 1.0000 1.0000
-1.500 -0.0162 0.01962 0.00943 -0.0176 1.0000 1.0000
-1.250 -0.0105 0.01913 0.00895 -0.0156 1.0000 1.0000
-1.000 -0.0058 0.01874 0.00857 -0.0132 1.0000 1.0000
-0.750 -0.0021 0.01842 0.00828 -0.0104 1.0000 1.0000
-0.500 0.0001 0.01820 0.00807 -0.0073 1.0000 1.0000
-0.250 0.0007 0.01806 0.00795 -0.0038 1.0000 1.0000
0.000 0.0000 0.01801 0.00791 0.0000 1.0000 1.0000
0.250 -0.0007 0.01805 0.00795 0.0038 1.0000 1.0000
0.500 -0.0001 0.01819 0.00807 0.0073 1.0000 1.0000
0.750 0.0021 0.01842 0.00827 0.0104 1.0000 1.0000
1.000 0.0058 0.01873 0.00857 0.0132 1.0000 1.0000
1.250 0.0106 0.01913 0.00895 0.0156 1.0000 1.0000
1.500 0.0163 0.01962 0.00942 0.0176 1.0000 1.0000
1.750 0.0229 0.02020 0.01001 0.0193 1.0000 1.0000
2.000 0.0707 0.02126 0.01120 0.0130 0.9852 1.0000
2.250 0.1641 0.02225 0.01247 -0.0007 0.9490 1.0000
2.500 0.2653 0.02248 0.01311 -0.0143 0.9099 1.0000
2.750 0.3722 0.02170 0.01283 -0.0267 0.8659 1.0000
3.000 0.4353 0.02094 0.01234 -0.0302 0.8170 1.0000
3.250 0.4729 0.02051 0.01198 -0.0290 0.7672 1.0000
3.500 0.4967 0.02044 0.01190 -0.0257 0.7163 1.0000
3.750 0.5171 0.02054 0.01190 -0.0221 0.6643 1.0000
4.000 0.5359 0.02083 0.01203 -0.0187 0.6115 1.0000
4.250 0.5546 0.02126 0.01224 -0.0154 0.5590 1.0000
4.500 0.5723 0.02189 0.01270 -0.0124 0.5067 1.0000
4.750 0.5907 0.02264 0.01322 -0.0097 0.4573 1.0000
5.000 0.6091 0.02351 0.01386 -0.0072 0.4114 1.0000
5.250 0.6274 0.02454 0.01474 -0.0049 0.3690 1.0000
5.500 0.6462 0.02571 0.01579 -0.0028 0.3314 1.0000
5.750 0.6650 0.02695 0.01697 -0.0008 0.2976 1.0000
6.000 0.6841 0.02836 0.01834 0.0011 0.2682 1.0000
6.250 0.7028 0.02992 0.01990 0.0029 0.2420 1.0000
6.500 0.7218 0.03150 0.02139 0.0047 0.2180 1.0000
6.750 0.7386 0.03342 0.02353 0.0067 0.1971 1.0000
7.000 0.7569 0.03526 0.02538 0.0084 0.1783 1.0000
7.250 0.7744 0.03747 0.02762 0.0100 0.1625 1.0000
7.500 0.7855 0.04027 0.03095 0.0124 0.1518 1.0000
7.750 0.7957 0.04346 0.03450 0.0145 0.1438 1.0000
8.000 0.8132 0.04596 0.03690 0.0158 0.1339 1.0000
8.250 0.8128 0.05018 0.04179 0.0183 0.1320 1.0000
8.500 0.8087 0.05475 0.04687 0.0203 0.1310 1.0000
8.750 0.8002 0.05956 0.05206 0.0219 0.1307 1.0000
9.000 0.7882 0.06455 0.05731 0.0229 0.1312 1.0000
9.250 0.7743 0.06965 0.06258 0.0234 0.1322 1.0000
9.500 0.7604 0.07479 0.06780 0.0234 0.1331 1.0000
9.750 0.7479 0.07986 0.07289 0.0233 0.1339 1.0000
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Polar data table (+)
Polar graphs
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