EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 200,000 Max Cl/Cd: 43.29 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh0009-il-200000-n5.txt Download as CSV file: xf-eh0009-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8386 0.05455 0.05048 -0.0248 1.0000 0.0068
-10.500 -0.8558 0.05009 0.04582 -0.0262 1.0000 0.0068
-10.250 -0.8707 0.04662 0.04214 -0.0255 1.0000 0.0068
-10.000 -0.8903 0.04287 0.03812 -0.0229 1.0000 0.0070
-9.750 -0.8953 0.03959 0.03453 -0.0210 1.0000 0.0071
-9.500 -0.8916 0.03719 0.03192 -0.0196 1.0000 0.0075
-9.250 -0.8830 0.03511 0.02956 -0.0182 1.0000 0.0078
-9.000 -0.8667 0.03456 0.02893 -0.0175 1.0000 0.0088
-8.750 -0.8546 0.03236 0.02642 -0.0161 1.0000 0.0094
-8.500 -0.8412 0.02998 0.02369 -0.0147 1.0000 0.0100
-8.250 -0.8257 0.02764 0.02100 -0.0132 1.0000 0.0104
-8.000 -0.8081 0.02566 0.01873 -0.0119 1.0000 0.0109
-7.750 -0.7887 0.02408 0.01689 -0.0107 1.0000 0.0115
-7.500 -0.7723 0.02189 0.01452 -0.0092 1.0000 0.0124
-7.250 -0.7528 0.02072 0.01327 -0.0082 1.0000 0.0139
-7.000 -0.7313 0.01990 0.01236 -0.0074 1.0000 0.0160
-6.750 -0.7108 0.01883 0.01114 -0.0062 1.0000 0.0176
-6.500 -0.6898 0.01789 0.01001 -0.0050 1.0000 0.0190
-6.250 -0.6712 0.01664 0.00867 -0.0036 1.0000 0.0220
-6.000 -0.6494 0.01595 0.00790 -0.0026 1.0000 0.0265
-5.750 -0.6281 0.01520 0.00711 -0.0016 1.0000 0.0332
-5.500 -0.6064 0.01453 0.00642 -0.0005 1.0000 0.0434
-5.250 -0.5852 0.01386 0.00583 0.0005 1.0000 0.0647
-5.000 -0.5641 0.01323 0.00532 0.0016 1.0000 0.0929
-4.750 -0.5431 0.01262 0.00486 0.0026 1.0000 0.1320
-4.500 -0.5217 0.01210 0.00448 0.0036 1.0000 0.1716
-4.250 -0.5007 0.01158 0.00416 0.0046 1.0000 0.2191
-4.000 -0.4800 0.01108 0.00388 0.0057 1.0000 0.2732
-3.750 -0.4588 0.01069 0.00365 0.0067 1.0000 0.3200
-3.500 -0.4376 0.01035 0.00345 0.0078 1.0000 0.3627
-3.250 -0.4166 0.01005 0.00325 0.0090 1.0000 0.4051
-3.000 -0.3821 0.00975 0.00311 0.0073 0.9937 0.4560
-2.750 -0.3476 0.00948 0.00299 0.0058 0.9861 0.5025
-2.500 -0.3123 0.00925 0.00290 0.0041 0.9788 0.5468
-2.250 -0.2775 0.00905 0.00279 0.0026 0.9707 0.5877
-2.000 -0.2443 0.00887 0.00273 0.0016 0.9610 0.6250
-1.750 -0.2106 0.00871 0.00268 0.0005 0.9512 0.6612
-1.500 -0.1768 0.00857 0.00264 -0.0005 0.9408 0.6948
-1.250 -0.1452 0.00846 0.00259 -0.0010 0.9283 0.7243
-1.000 -0.1140 0.00837 0.00256 -0.0013 0.9147 0.7517
-0.750 -0.0838 0.00830 0.00254 -0.0014 0.8997 0.7774
-0.500 -0.0555 0.00824 0.00253 -0.0011 0.8825 0.8017
-0.250 -0.0276 0.00821 0.00252 -0.0006 0.8641 0.8239
0.000 0.0000 0.00820 0.00251 0.0000 0.8450 0.8450
0.250 0.0275 0.00821 0.00252 0.0006 0.8239 0.8641
0.500 0.0554 0.00824 0.00253 0.0011 0.8018 0.8825
0.750 0.0838 0.00830 0.00254 0.0014 0.7775 0.8997
1.000 0.1140 0.00837 0.00256 0.0014 0.7517 0.9147
1.250 0.1451 0.00846 0.00259 0.0010 0.7242 0.9283
1.500 0.1767 0.00857 0.00264 0.0005 0.6946 0.9409
1.750 0.2106 0.00871 0.00268 -0.0005 0.6614 0.9513
2.000 0.2443 0.00887 0.00272 -0.0016 0.6251 0.9611
2.250 0.2775 0.00905 0.00279 -0.0026 0.5878 0.9707
2.500 0.3123 0.00925 0.00290 -0.0041 0.5472 0.9790
2.750 0.3476 0.00948 0.00299 -0.0058 0.5025 0.9863
3.000 0.3822 0.00975 0.00311 -0.0073 0.4558 0.9938
3.250 0.4163 0.01004 0.00325 -0.0089 0.4056 1.0000
3.500 0.4374 0.01035 0.00344 -0.0078 0.3631 1.0000
3.750 0.4585 0.01069 0.00364 -0.0067 0.3198 1.0000
4.000 0.4797 0.01108 0.00388 -0.0056 0.2735 1.0000
4.250 0.5005 0.01157 0.00415 -0.0045 0.2199 1.0000
4.500 0.5215 0.01210 0.00448 -0.0035 0.1718 1.0000
4.750 0.5428 0.01262 0.00485 -0.0025 0.1319 1.0000
5.000 0.5638 0.01323 0.00532 -0.0015 0.0929 1.0000
5.250 0.5850 0.01386 0.00583 -0.0005 0.0647 1.0000
5.500 0.6063 0.01453 0.00642 0.0005 0.0436 1.0000
5.750 0.6280 0.01520 0.00711 0.0016 0.0332 1.0000
6.000 0.6493 0.01594 0.00789 0.0026 0.0265 1.0000
6.250 0.6711 0.01664 0.00866 0.0036 0.0220 1.0000
6.500 0.6898 0.01789 0.01000 0.0050 0.0189 1.0000
6.750 0.7108 0.01883 0.01114 0.0062 0.0176 1.0000
7.000 0.7314 0.01991 0.01237 0.0074 0.0160 1.0000
7.250 0.7530 0.02071 0.01326 0.0082 0.0138 1.0000
7.500 0.7726 0.02189 0.01452 0.0092 0.0124 1.0000
7.750 0.7890 0.02407 0.01689 0.0107 0.0114 1.0000
8.000 0.8084 0.02566 0.01873 0.0118 0.0109 1.0000
8.250 0.8261 0.02766 0.02102 0.0132 0.0104 1.0000
8.500 0.8415 0.03002 0.02373 0.0146 0.0100 1.0000
8.750 0.8549 0.03244 0.02651 0.0161 0.0095 1.0000
9.000 0.8683 0.03428 0.02861 0.0173 0.0087 1.0000
9.250 0.8805 0.03590 0.03045 0.0184 0.0080 1.0000
9.500 0.8899 0.03775 0.03255 0.0197 0.0076 1.0000
9.750 0.8956 0.03965 0.03459 0.0209 0.0071 1.0000
10.000 0.8858 0.04346 0.03874 0.0229 0.0069 1.0000
10.500 0.8565 0.05016 0.04591 0.0260 0.0068 1.0000
11.000 0.8253 0.05973 0.05586 0.0212 0.0069 1.0000
11.250 0.8123 0.06603 0.06233 0.0161 0.0070 1.0000
11.500 0.7922 0.07537 0.07183 0.0085 0.0070 1.0000
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Polar data table (+)
Polar graphs
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