SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 200,000 Max Cl/Cd: 47.51 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8020-il-200000.txt Download as CSV file: xf-sd8020-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8482 0.06783 0.06382 -0.0344 1.0000 0.0277
-12.000 -0.8787 0.06108 0.05681 -0.0389 1.0000 0.0273
-11.750 -0.8983 0.05700 0.05250 -0.0401 1.0000 0.0270
-11.500 -0.9155 0.05368 0.04897 -0.0395 1.0000 0.0269
-11.250 -0.9322 0.05069 0.04577 -0.0373 1.0000 0.0268
-11.000 -0.9481 0.04779 0.04264 -0.0339 1.0000 0.0268
-10.750 -0.9575 0.04457 0.03913 -0.0310 1.0000 0.0269
-10.500 -0.9641 0.04083 0.03506 -0.0282 1.0000 0.0271
-10.250 -0.9640 0.03734 0.03127 -0.0258 1.0000 0.0275
-10.000 -0.9564 0.03484 0.02858 -0.0238 1.0000 0.0283
-9.750 -0.9446 0.03325 0.02687 -0.0220 1.0000 0.0296
-9.500 -0.9315 0.03177 0.02519 -0.0202 1.0000 0.0312
-9.250 -0.9181 0.03010 0.02325 -0.0183 1.0000 0.0329
-9.000 -0.9029 0.02849 0.02134 -0.0163 1.0000 0.0342
-8.750 -0.8880 0.02584 0.01845 -0.0145 1.0000 0.0358
-8.500 -0.8710 0.02450 0.01711 -0.0131 1.0000 0.0383
-8.250 -0.8527 0.02354 0.01603 -0.0115 1.0000 0.0415
-8.000 -0.8334 0.02258 0.01488 -0.0099 1.0000 0.0441
-7.750 -0.8177 0.02076 0.01308 -0.0080 1.0000 0.0479
-7.500 -0.7988 0.02000 0.01225 -0.0064 1.0000 0.0533
-7.250 -0.7824 0.01879 0.01104 -0.0045 1.0000 0.0595
-7.000 -0.7638 0.01796 0.01013 -0.0027 1.0000 0.0682
-6.750 -0.7460 0.01712 0.00931 -0.0009 1.0000 0.0806
-6.500 -0.7284 0.01629 0.00854 0.0008 1.0000 0.0952
-6.250 -0.7098 0.01561 0.00790 0.0024 1.0000 0.1104
-6.000 -0.6905 0.01503 0.00737 0.0039 1.0000 0.1270
-5.750 -0.6705 0.01453 0.00689 0.0053 1.0000 0.1467
-5.500 -0.6514 0.01396 0.00645 0.0068 1.0000 0.1688
-5.250 -0.6319 0.01346 0.00604 0.0083 1.0000 0.1947
-5.000 -0.6124 0.01296 0.00565 0.0098 1.0000 0.2234
-4.750 -0.5930 0.01249 0.00531 0.0113 1.0000 0.2549
-4.500 -0.5734 0.01207 0.00502 0.0127 1.0000 0.2901
-4.250 -0.5540 0.01167 0.00477 0.0142 1.0000 0.3265
-4.000 -0.5345 0.01132 0.00454 0.0158 1.0000 0.3658
-3.750 -0.5153 0.01098 0.00438 0.0173 1.0000 0.4065
-3.500 -0.4960 0.01069 0.00425 0.0189 1.0000 0.4483
-3.250 -0.4770 0.01043 0.00416 0.0206 1.0000 0.4913
-3.000 -0.4582 0.01020 0.00410 0.0223 1.0000 0.5353
-2.750 -0.4396 0.01001 0.00408 0.0241 1.0000 0.5794
-2.500 -0.4214 0.00985 0.00410 0.0259 1.0000 0.6232
-2.250 -0.4035 0.00973 0.00415 0.0278 1.0000 0.6665
-2.000 -0.3858 0.00965 0.00422 0.0298 1.0000 0.7091
-1.750 -0.3441 0.00968 0.00442 0.0271 0.9928 0.7574
-1.500 -0.3016 0.00970 0.00457 0.0244 0.9850 0.8011
-1.250 -0.2599 0.00971 0.00467 0.0220 0.9768 0.8403
-1.000 -0.2116 0.00978 0.00482 0.0183 0.9708 0.8736
-0.750 -0.1647 0.00987 0.00493 0.0149 0.9629 0.9008
-0.500 -0.1086 0.00999 0.00506 0.0097 0.9579 0.9193
-0.250 -0.0559 0.01007 0.00513 0.0052 0.9502 0.9333
0.000 0.0001 0.01009 0.00514 0.0000 0.9436 0.9436
0.250 0.0560 0.01007 0.00513 -0.0052 0.9333 0.9502
0.500 0.1087 0.00999 0.00506 -0.0097 0.9192 0.9579
0.750 0.1649 0.00986 0.00492 -0.0150 0.9005 0.9629
1.000 0.2117 0.00978 0.00482 -0.0183 0.8736 0.9709
1.250 0.2601 0.00970 0.00467 -0.0220 0.8402 0.9768
1.500 0.3018 0.00970 0.00457 -0.0244 0.8012 0.9850
1.750 0.3442 0.00968 0.00442 -0.0271 0.7575 0.9929
2.000 0.3858 0.00965 0.00422 -0.0298 0.7092 1.0000
2.250 0.4035 0.00973 0.00415 -0.0278 0.6669 1.0000
2.500 0.4214 0.00985 0.00410 -0.0259 0.6239 1.0000
2.750 0.4397 0.01001 0.00408 -0.0241 0.5800 1.0000
3.000 0.4582 0.01020 0.00410 -0.0223 0.5358 1.0000
3.250 0.4770 0.01043 0.00416 -0.0206 0.4920 1.0000
3.500 0.4960 0.01069 0.00425 -0.0189 0.4485 1.0000
3.750 0.5152 0.01098 0.00438 -0.0173 0.4063 1.0000
4.000 0.5344 0.01132 0.00454 -0.0157 0.3658 1.0000
4.250 0.5540 0.01167 0.00477 -0.0142 0.3265 1.0000
4.500 0.5734 0.01207 0.00502 -0.0127 0.2900 1.0000
4.750 0.5930 0.01249 0.00531 -0.0113 0.2548 1.0000
5.000 0.6124 0.01296 0.00565 -0.0098 0.2233 1.0000
5.250 0.6319 0.01345 0.00603 -0.0083 0.1947 1.0000
5.500 0.6514 0.01396 0.00645 -0.0068 0.1685 1.0000
5.750 0.6706 0.01452 0.00689 -0.0053 0.1466 1.0000
6.000 0.6904 0.01504 0.00738 -0.0039 0.1269 1.0000
6.250 0.7097 0.01562 0.00790 -0.0024 0.1101 1.0000
6.500 0.7283 0.01631 0.00855 -0.0008 0.0951 1.0000
6.750 0.7460 0.01713 0.00932 0.0010 0.0807 1.0000
7.000 0.7639 0.01795 0.01013 0.0027 0.0683 1.0000
7.250 0.7824 0.01879 0.01104 0.0045 0.0595 1.0000
7.500 0.7988 0.02003 0.01228 0.0064 0.0533 1.0000
7.750 0.8178 0.02078 0.01309 0.0080 0.0481 1.0000
8.000 0.8334 0.02262 0.01491 0.0099 0.0442 1.0000
8.250 0.8528 0.02355 0.01604 0.0115 0.0416 1.0000
8.500 0.8710 0.02448 0.01708 0.0130 0.0384 1.0000
8.750 0.8882 0.02582 0.01843 0.0145 0.0359 1.0000
9.000 0.9029 0.02854 0.02138 0.0163 0.0343 1.0000
9.250 0.9182 0.03010 0.02324 0.0182 0.0330 1.0000
9.500 0.9316 0.03178 0.02521 0.0202 0.0313 1.0000
9.750 0.9447 0.03321 0.02682 0.0220 0.0295 1.0000
10.000 0.9564 0.03482 0.02856 0.0238 0.0283 1.0000
10.250 0.9640 0.03736 0.03128 0.0258 0.0275 1.0000
10.500 0.9635 0.04098 0.03520 0.0282 0.0270 1.0000
10.750 0.9566 0.04474 0.03931 0.0310 0.0268 1.0000
11.000 0.9473 0.04792 0.04277 0.0339 0.0268 1.0000
11.250 0.9283 0.05120 0.04630 0.0374 0.0267 1.0000
11.500 0.9139 0.05395 0.04925 0.0394 0.0268 1.0000
11.750 0.8951 0.05752 0.05302 0.0399 0.0269 1.0000
12.000 0.8779 0.06135 0.05706 0.0388 0.0271 1.0000
12.250 0.8524 0.06729 0.06324 0.0349 0.0275 1.0000
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Polar data table (+)
Polar graphs
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