EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 200,000 Max Cl/Cd: 58.74 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1590-il-200000-n5.txt Download as CSV file: xf-eh1590-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.5/9.0
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5013 0.08535 0.08222 -0.0008 1.0000 0.0138
-9.250 -0.5160 0.07660 0.07351 -0.0046 1.0000 0.0130
-8.750 -0.6017 0.07281 0.06959 -0.0126 1.0000 0.0126
-8.500 -0.6153 0.06731 0.06406 -0.0155 1.0000 0.0125
-8.250 -0.6261 0.06174 0.05840 -0.0170 1.0000 0.0123
-8.000 -0.6324 0.05602 0.05253 -0.0180 1.0000 0.0122
-7.750 -0.6364 0.05001 0.04628 -0.0181 1.0000 0.0121
-7.500 -0.6371 0.04420 0.04015 -0.0175 1.0000 0.0119
-7.250 -0.6342 0.03877 0.03429 -0.0162 1.0000 0.0118
-7.000 -0.6269 0.03399 0.02900 -0.0146 1.0000 0.0118
-6.750 -0.6148 0.03010 0.02458 -0.0130 1.0000 0.0119
-6.500 -0.5988 0.02697 0.02090 -0.0114 1.0000 0.0121
-6.250 -0.5797 0.02456 0.01805 -0.0101 1.0000 0.0124
-6.000 -0.5586 0.02268 0.01582 -0.0089 1.0000 0.0127
-5.750 -0.5387 0.02026 0.01310 -0.0076 1.0000 0.0134
-5.500 -0.5166 0.01908 0.01181 -0.0068 1.0000 0.0144
-5.250 -0.4936 0.01839 0.01104 -0.0060 1.0000 0.0160
-5.000 -0.4710 0.01740 0.00993 -0.0050 1.0000 0.0174
-4.750 -0.4492 0.01634 0.00874 -0.0037 1.0000 0.0183
-4.500 -0.4279 0.01546 0.00773 -0.0024 1.0000 0.0194
-4.250 -0.3960 0.01434 0.00654 -0.0035 0.9867 0.0219
-4.000 -0.3604 0.01364 0.00577 -0.0052 0.9685 0.0273
-3.750 -0.3258 0.01304 0.00515 -0.0067 0.9465 0.0394
-3.500 -0.2919 0.01247 0.00466 -0.0080 0.9222 0.0603
-3.250 -0.2603 0.01204 0.00423 -0.0088 0.8957 0.0864
-3.000 -0.2324 0.01167 0.00389 -0.0087 0.8678 0.1170
-2.750 -0.2070 0.01130 0.00359 -0.0081 0.8407 0.1579
-2.500 -0.1834 0.01088 0.00331 -0.0072 0.8150 0.2197
-2.250 -0.1617 0.01027 0.00303 -0.0061 0.7906 0.3285
-2.000 -0.1445 0.00932 0.00278 -0.0042 0.7684 0.5296
-1.750 -0.1265 0.00874 0.00277 -0.0016 0.7477 0.7017
-1.500 -0.1030 0.00863 0.00280 0.0001 0.7277 0.7850
-1.250 -0.0772 0.00865 0.00280 0.0012 0.7083 0.8344
-1.000 -0.0499 0.00874 0.00277 0.0020 0.6901 0.8679
-0.750 -0.0208 0.00885 0.00278 0.0023 0.6720 0.8980
-0.500 0.0125 0.00902 0.00285 0.0019 0.6543 0.9275
-0.250 0.0569 0.00927 0.00295 -0.0008 0.6364 0.9505
0.000 0.0967 0.00940 0.00292 -0.0031 0.6190 0.9599
0.250 0.1303 0.00946 0.00285 -0.0043 0.6027 0.9654
0.500 0.1633 0.00952 0.00279 -0.0054 0.5867 0.9706
0.750 0.1984 0.00957 0.00273 -0.0070 0.5711 0.9746
1.000 0.2312 0.00963 0.00269 -0.0082 0.5560 0.9798
1.250 0.2646 0.00969 0.00266 -0.0094 0.5412 0.9842
1.500 0.2989 0.00974 0.00265 -0.0110 0.5265 0.9882
1.750 0.3320 0.00981 0.00265 -0.0122 0.5122 0.9928
2.000 0.3658 0.00987 0.00265 -0.0136 0.4982 0.9968
2.250 0.3975 0.00994 0.00267 -0.0147 0.4843 1.0000
2.500 0.4206 0.01003 0.00274 -0.0139 0.4717 1.0000
2.750 0.4438 0.01013 0.00281 -0.0130 0.4593 1.0000
3.000 0.4670 0.01024 0.00291 -0.0122 0.4469 1.0000
3.250 0.4902 0.01036 0.00301 -0.0114 0.4348 1.0000
3.500 0.5134 0.01050 0.00314 -0.0106 0.4223 1.0000
3.750 0.5367 0.01065 0.00331 -0.0098 0.4100 1.0000
4.000 0.5601 0.01082 0.00347 -0.0090 0.3977 1.0000
4.250 0.5835 0.01100 0.00366 -0.0082 0.3849 1.0000
4.500 0.6069 0.01118 0.00386 -0.0074 0.3719 1.0000
4.750 0.6304 0.01138 0.00408 -0.0067 0.3583 1.0000
5.250 0.6775 0.01183 0.00461 -0.0051 0.3290 1.0000
5.500 0.7010 0.01207 0.00489 -0.0044 0.3127 1.0000
5.750 0.7243 0.01234 0.00520 -0.0036 0.2947 1.0000
6.000 0.7466 0.01271 0.00549 -0.0028 0.2632 1.0000
6.250 0.7668 0.01334 0.00589 -0.0018 0.2046 1.0000
6.500 0.7866 0.01413 0.00641 -0.0009 0.1486 1.0000
6.750 0.8044 0.01526 0.00718 0.0002 0.0841 1.0000
7.000 0.8215 0.01652 0.00816 0.0014 0.0372 1.0000
7.250 0.8408 0.01751 0.00915 0.0025 0.0243 1.0000
7.500 0.8597 0.01853 0.01026 0.0037 0.0191 1.0000
7.750 0.8800 0.01931 0.01118 0.0047 0.0163 1.0000
8.000 0.8985 0.02031 0.01237 0.0058 0.0146 1.0000
8.250 0.9139 0.02162 0.01381 0.0072 0.0133 1.0000
8.500 0.9259 0.02328 0.01561 0.0090 0.0125 1.0000
8.750 0.9417 0.02448 0.01695 0.0103 0.0119 1.0000
9.000 0.9572 0.02568 0.01829 0.0117 0.0110 1.0000
9.250 0.9723 0.02685 0.01958 0.0129 0.0100 1.0000
9.500 0.9858 0.02814 0.02097 0.0142 0.0092 1.0000
9.750 0.9969 0.02969 0.02265 0.0158 0.0088 1.0000
10.000 1.0060 0.03141 0.02450 0.0174 0.0085 1.0000
10.250 1.0118 0.03340 0.02662 0.0193 0.0082 1.0000
10.500 1.0144 0.03565 0.02907 0.0214 0.0079 1.0000
11.000 1.0128 0.04114 0.03497 0.0247 0.0077 1.0000
11.250 1.0110 0.04372 0.03777 0.0255 0.0076 1.0000
11.500 1.0070 0.04670 0.04097 0.0257 0.0076 1.0000
11.750 1.0005 0.05015 0.04465 0.0252 0.0075 1.0000
12.000 0.9918 0.05416 0.04889 0.0240 0.0075 1.0000
12.250 0.9829 0.05840 0.05333 0.0222 0.0074 1.0000
12.500 0.9724 0.06315 0.05827 0.0199 0.0074 1.0000
12.750 0.9593 0.06865 0.06396 0.0169 0.0075 1.0000
13.000 0.9470 0.07429 0.06977 0.0135 0.0075 1.0000
13.250 0.9325 0.08064 0.07628 0.0096 0.0075 1.0000
13.500 0.9173 0.08751 0.08331 0.0052 0.0075 1.0000
13.750 0.9007 0.09502 0.09096 0.0006 0.0076 1.0000
14.000 0.8854 0.10285 0.09890 -0.0043 0.0076 1.0000
14.250 0.8683 0.11166 0.10783 -0.0096 0.0077 1.0000
14.500 0.8509 0.12124 0.11751 -0.0153 0.0077 1.0000
14.750 0.8401 0.12990 0.12628 -0.0203 0.0078 1.0000
15.000 0.8099 0.14676 0.14319 -0.0286 0.0083 1.0000
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Polar data table (+)
Polar graphs
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