EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 100,000 Max Cl/Cd: 37.58 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh0009-il-100000.txt Download as CSV file: xf-eh0009-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6404 0.11534 0.11047 0.0106 1.0000 0.1209
-10.250 -0.6368 0.11140 0.10655 0.0096 1.0000 0.1253
-10.000 -0.6668 0.10662 0.10191 0.0017 1.0000 0.1300
-9.750 -0.6502 0.10184 0.09711 0.0039 1.0000 0.1331
-9.500 -0.6516 0.06832 0.06390 -0.0217 1.0000 0.0636
-9.250 -0.6634 0.06284 0.05840 -0.0232 1.0000 0.0623
-8.500 -0.7828 0.05459 0.04896 -0.0211 1.0000 0.0506
-8.250 -0.7814 0.04974 0.04384 -0.0201 1.0000 0.0491
-8.000 -0.7777 0.04543 0.03910 -0.0187 1.0000 0.0490
-7.750 -0.7706 0.04175 0.03486 -0.0170 1.0000 0.0504
-7.500 -0.7590 0.03821 0.03077 -0.0152 1.0000 0.0510
-7.250 -0.7437 0.03453 0.02658 -0.0135 1.0000 0.0510
-7.000 -0.7250 0.03145 0.02290 -0.0119 1.0000 0.0516
-6.750 -0.7041 0.02801 0.01912 -0.0106 1.0000 0.0536
-6.500 -0.6822 0.02591 0.01697 -0.0097 1.0000 0.0594
-6.250 -0.6596 0.02390 0.01477 -0.0085 1.0000 0.0673
-6.000 -0.6366 0.02214 0.01294 -0.0072 1.0000 0.0764
-5.750 -0.6167 0.02044 0.01137 -0.0059 1.0000 0.0934
-5.500 -0.5985 0.01868 0.00983 -0.0040 1.0000 0.1214
-5.250 -0.5831 0.01693 0.00859 -0.0021 1.0000 0.1897
-5.000 -0.5671 0.01561 0.00776 -0.0003 1.0000 0.2792
-4.750 -0.5502 0.01477 0.00728 0.0015 1.0000 0.3649
-4.500 -0.5323 0.01416 0.00695 0.0035 1.0000 0.4377
-4.250 -0.5135 0.01369 0.00666 0.0055 1.0000 0.5006
-4.000 -0.4943 0.01331 0.00645 0.0076 1.0000 0.5571
-3.750 -0.4751 0.01301 0.00628 0.0098 1.0000 0.6097
-3.500 -0.4557 0.01278 0.00617 0.0122 1.0000 0.6567
-3.250 -0.4366 0.01261 0.00605 0.0146 1.0000 0.7011
-3.000 -0.4178 0.01250 0.00600 0.0173 1.0000 0.7425
-2.750 -0.3993 0.01244 0.00599 0.0200 1.0000 0.7812
-2.500 -0.3810 0.01243 0.00599 0.0228 1.0000 0.8185
-2.250 -0.3601 0.01249 0.00605 0.0253 1.0000 0.8536
-2.000 -0.3333 0.01263 0.00611 0.0265 1.0000 0.8879
-1.750 -0.2905 0.01289 0.00626 0.0246 1.0000 0.9175
-1.500 -0.2349 0.01314 0.00636 0.0197 1.0000 0.9417
-1.250 -0.1638 0.01329 0.00632 0.0115 1.0000 0.9580
-1.000 -0.0956 0.01322 0.00614 0.0033 1.0000 0.9740
-0.750 -0.0299 0.01299 0.00582 -0.0046 1.0000 0.9895
-0.500 0.0181 0.01268 0.00548 -0.0098 1.0000 1.0000
-0.250 0.0136 0.01252 0.00536 -0.0057 1.0000 1.0000
0.000 0.0000 0.01247 0.00533 0.0000 1.0000 1.0000
0.250 -0.0136 0.01252 0.00536 0.0057 1.0000 1.0000
0.500 -0.0181 0.01268 0.00548 0.0098 1.0000 1.0000
0.750 0.0298 0.01299 0.00582 0.0046 0.9895 1.0000
1.000 0.0955 0.01322 0.00614 -0.0033 0.9740 1.0000
1.250 0.1636 0.01328 0.00632 -0.0114 0.9581 1.0000
1.500 0.2347 0.01314 0.00636 -0.0196 0.9418 1.0000
1.750 0.2904 0.01288 0.00625 -0.0245 0.9175 1.0000
2.000 0.3331 0.01262 0.00610 -0.0265 0.8879 1.0000
2.250 0.3599 0.01249 0.00605 -0.0253 0.8537 1.0000
2.500 0.3807 0.01243 0.00599 -0.0228 0.8185 1.0000
2.750 0.3991 0.01244 0.00599 -0.0200 0.7813 1.0000
3.000 0.4176 0.01250 0.00600 -0.0172 0.7426 1.0000
3.250 0.4363 0.01261 0.00604 -0.0146 0.7013 1.0000
3.500 0.4555 0.01278 0.00617 -0.0121 0.6568 1.0000
3.750 0.4748 0.01301 0.00627 -0.0098 0.6100 1.0000
4.000 0.4941 0.01331 0.00645 -0.0076 0.5573 1.0000
4.250 0.5132 0.01369 0.00666 -0.0055 0.5008 1.0000
4.500 0.5321 0.01416 0.00695 -0.0035 0.4378 1.0000
4.750 0.5500 0.01477 0.00728 -0.0015 0.3652 1.0000
5.000 0.5669 0.01561 0.00776 0.0003 0.2797 1.0000
5.250 0.5830 0.01694 0.00859 0.0022 0.1896 1.0000
5.500 0.5985 0.01868 0.00983 0.0040 0.1215 1.0000
5.750 0.6167 0.02044 0.01137 0.0059 0.0935 1.0000
6.000 0.6366 0.02214 0.01294 0.0072 0.0764 1.0000
6.250 0.6596 0.02389 0.01476 0.0085 0.0673 1.0000
6.500 0.6823 0.02592 0.01698 0.0097 0.0595 1.0000
6.750 0.7041 0.02805 0.01914 0.0106 0.0535 1.0000
7.000 0.7251 0.03146 0.02291 0.0119 0.0516 1.0000
7.250 0.7438 0.03452 0.02657 0.0135 0.0509 1.0000
7.500 0.7591 0.03821 0.03077 0.0152 0.0510 1.0000
7.750 0.7706 0.04171 0.03484 0.0170 0.0501 1.0000
8.000 0.7781 0.04546 0.03912 0.0186 0.0491 1.0000
8.250 0.7815 0.04977 0.04387 0.0201 0.0490 1.0000
8.500 0.7831 0.05462 0.04899 0.0211 0.0506 1.0000
8.750 0.7615 0.06175 0.05681 0.0217 0.0580 1.0000
9.000 0.7490 0.06741 0.06262 0.0214 0.0620 1.0000
9.250 0.5599 0.08630 0.08190 0.0016 0.1376 1.0000
9.500 0.5514 0.09214 0.08770 -0.0008 0.1388 1.0000
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Polar data table (+)
Polar graphs
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