EPPLER 864 STRUT AIRFOIL (e864-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 864 STRUT AIRFOIL (e864-il) Reynolds number: 500,000 Max Cl/Cd: 33.05 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e864-il-500000-n5.txt Download as CSV file: xf-e864-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 864 STRUT AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.9451 0.10241 0.09651 -0.0100 0.5983 0.2435
-18.250 -0.9455 0.09947 0.09352 -0.0107 0.5904 0.2476
-18.000 -0.9517 0.09592 0.08987 -0.0112 0.5833 0.2520
-17.750 -0.9334 0.09501 0.08895 -0.0121 0.5749 0.2544
-17.500 -0.9234 0.09322 0.08715 -0.0127 0.5681 0.2576
-17.250 -0.9361 0.08907 0.08290 -0.0131 0.5630 0.2628
-17.000 -0.9279 0.08710 0.08088 -0.0137 0.5558 0.2660
-16.750 -0.9125 0.08588 0.07966 -0.0145 0.5492 0.2686
-16.500 -0.9148 0.08286 0.07660 -0.0149 0.5446 0.2729
-16.250 -0.9285 0.07872 0.07236 -0.0150 0.5405 0.2779
-16.000 -0.9101 0.07784 0.07148 -0.0157 0.5340 0.2803
-15.750 -0.9029 0.07583 0.06944 -0.0162 0.5287 0.2837
-15.500 -0.9188 0.07156 0.06508 -0.0162 0.5257 0.2890
-15.250 -0.9163 0.06913 0.06263 -0.0165 0.5225 0.2925
-15.000 -0.9049 0.06759 0.06110 -0.0169 0.5185 0.2955
-14.750 -0.9066 0.06481 0.05827 -0.0171 0.5150 0.2996
-14.500 -0.9278 0.06023 0.05358 -0.0167 0.5126 0.3047
-14.250 -0.9130 0.05905 0.05240 -0.0172 0.5084 0.3073
-14.000 -0.9140 0.05643 0.04974 -0.0173 0.5050 0.3112
-13.750 -0.9322 0.05229 0.04549 -0.0168 0.5026 0.3162
-13.500 -0.9310 0.04994 0.04311 -0.0168 0.5004 0.3194
-13.250 -0.9226 0.04823 0.04141 -0.0170 0.4978 0.3223
-13.000 -0.9269 0.04545 0.03859 -0.0168 0.4954 0.3262
-12.750 -0.9385 0.04210 0.03512 -0.0162 0.4931 0.3302
-12.500 -0.9329 0.04025 0.03323 -0.0162 0.4902 0.3329
-12.250 -0.9258 0.03857 0.03153 -0.0162 0.4872 0.3356
-12.000 -0.9190 0.03688 0.02979 -0.0161 0.4841 0.3384
-11.750 -0.9169 0.03486 0.02768 -0.0159 0.4813 0.3414
-11.500 -0.9150 0.03284 0.02557 -0.0155 0.4793 0.3443
-11.250 -0.9052 0.03148 0.02417 -0.0154 0.4775 0.3465
-11.000 -0.8924 0.03039 0.02308 -0.0153 0.4756 0.3486
-10.750 -0.8799 0.02929 0.02197 -0.0152 0.4734 0.3507
-10.500 -0.8685 0.02815 0.02079 -0.0150 0.4713 0.3530
-10.250 -0.8563 0.02709 0.01967 -0.0148 0.4692 0.3552
-10.000 -0.8444 0.02604 0.01855 -0.0145 0.4672 0.3573
-9.750 -0.8312 0.02512 0.01754 -0.0142 0.4651 0.3592
-9.500 -0.8163 0.02434 0.01670 -0.0139 0.4630 0.3609
-9.250 -0.7982 0.02377 0.01612 -0.0138 0.4609 0.3626
-9.000 -0.7809 0.02319 0.01552 -0.0136 0.4589 0.3642
-8.750 -0.7635 0.02260 0.01492 -0.0134 0.4576 0.3659
-8.500 -0.7458 0.02206 0.01436 -0.0131 0.4561 0.3677
-8.250 -0.7284 0.02153 0.01379 -0.0127 0.4545 0.3694
-8.000 -0.7098 0.02106 0.01329 -0.0124 0.4527 0.3709
-7.750 -0.6917 0.02061 0.01279 -0.0120 0.4509 0.3725
-7.500 -0.6731 0.02020 0.01232 -0.0116 0.4493 0.3740
-7.250 -0.6548 0.01982 0.01187 -0.0111 0.4477 0.3752
-7.000 -0.6332 0.01952 0.01157 -0.0109 0.4461 0.3766
-6.750 -0.6121 0.01924 0.01128 -0.0106 0.4446 0.3779
-6.500 -0.5916 0.01898 0.01100 -0.0103 0.4430 0.3792
-6.250 -0.5709 0.01875 0.01075 -0.0098 0.4414 0.3806
-6.000 -0.5504 0.01855 0.01052 -0.0093 0.4398 0.3820
-5.750 -0.5299 0.01834 0.01029 -0.0088 0.4386 0.3834
-5.500 -0.5086 0.01813 0.01007 -0.0084 0.4376 0.3848
-5.250 -0.4874 0.01794 0.00986 -0.0079 0.4366 0.3860
-5.000 -0.4662 0.01776 0.00965 -0.0073 0.4353 0.3872
-4.750 -0.4457 0.01760 0.00948 -0.0066 0.4339 0.3884
-4.500 -0.4270 0.01749 0.00933 -0.0055 0.4326 0.3896
-4.250 -0.4094 0.01742 0.00922 -0.0041 0.4313 0.3906
-4.000 -0.3914 0.01734 0.00912 -0.0028 0.4300 0.3917
-3.750 -0.3710 0.01725 0.00903 -0.0019 0.4288 0.3930
-3.500 -0.3491 0.01717 0.00896 -0.0013 0.4275 0.3942
-3.250 -0.3264 0.01711 0.00889 -0.0008 0.4263 0.3953
-3.000 -0.3032 0.01707 0.00884 -0.0004 0.4251 0.3965
-2.750 -0.2797 0.01704 0.00879 -0.0001 0.4238 0.3977
-2.500 -0.2559 0.01702 0.00876 0.0002 0.4224 0.3990
-2.250 -0.2317 0.01703 0.00874 0.0004 0.4208 0.4003
-2.000 -0.2066 0.01701 0.00871 0.0005 0.4196 0.4015
-1.750 -0.1810 0.01697 0.00867 0.0005 0.4188 0.4027
-1.500 -0.1552 0.01694 0.00864 0.0005 0.4178 0.4038
-1.250 -0.1293 0.01692 0.00862 0.0004 0.4168 0.4049
-1.000 -0.1033 0.01691 0.00860 0.0003 0.4158 0.4060
-0.750 -0.0772 0.01691 0.00858 0.0003 0.4146 0.4070
-0.500 -0.0510 0.01691 0.00856 0.0002 0.4134 0.4079
-0.250 -0.0249 0.01686 0.00853 0.0000 0.4121 0.4091
0.000 0.0009 0.01681 0.00850 0.0000 0.4107 0.4104
0.250 0.0266 0.01679 0.00849 0.0000 0.4095 0.4116
0.500 0.0523 0.01679 0.00850 -0.0001 0.4084 0.4128
0.750 0.0779 0.01680 0.00851 -0.0001 0.4072 0.4141
1.000 0.1033 0.01682 0.00853 0.0000 0.4058 0.4154
1.250 0.1284 0.01686 0.00855 0.0000 0.4042 0.4168
1.500 0.1538 0.01693 0.00860 0.0000 0.4024 0.4180
1.750 0.1791 0.01693 0.00863 0.0001 0.4013 0.4192
2.000 0.2041 0.01693 0.00866 0.0002 0.3999 0.4203
2.250 0.2290 0.01695 0.00869 0.0003 0.3984 0.4215
2.500 0.2536 0.01698 0.00873 0.0005 0.3970 0.4226
2.750 0.2778 0.01702 0.00878 0.0007 0.3956 0.4237
3.000 0.3015 0.01707 0.00883 0.0010 0.3942 0.4248
3.250 0.3246 0.01713 0.00888 0.0015 0.3929 0.4257
3.500 0.3462 0.01717 0.00892 0.0021 0.3915 0.4269
3.750 0.3641 0.01718 0.00895 0.0035 0.3901 0.4283
4.000 0.3807 0.01722 0.00900 0.0051 0.3889 0.4297
4.250 0.3988 0.01730 0.00909 0.0063 0.3877 0.4309
4.500 0.4183 0.01742 0.00922 0.0073 0.3864 0.4322
4.750 0.4390 0.01755 0.00939 0.0080 0.3853 0.4335
5.000 0.4600 0.01771 0.00959 0.0086 0.3842 0.4348
5.250 0.4809 0.01788 0.00981 0.0092 0.3829 0.4362
5.500 0.5021 0.01807 0.01003 0.0096 0.3814 0.4376
5.750 0.5232 0.01828 0.01028 0.0101 0.3799 0.4391
6.000 0.5441 0.01852 0.01053 0.0105 0.3785 0.4406
6.250 0.5652 0.01877 0.01080 0.0109 0.3771 0.4421
6.500 0.5856 0.01905 0.01109 0.0113 0.3757 0.4433
6.750 0.6057 0.01935 0.01139 0.0117 0.3742 0.4444
7.000 0.6257 0.01967 0.01170 0.0121 0.3726 0.4453
7.250 0.6447 0.02001 0.01205 0.0126 0.3710 0.4471
7.500 0.6643 0.02037 0.01246 0.0129 0.3695 0.4489
7.750 0.6831 0.02079 0.01295 0.0132 0.3679 0.4506
8.000 0.7013 0.02126 0.01348 0.0135 0.3660 0.4522
8.250 0.7192 0.02176 0.01404 0.0138 0.3639 0.4540
8.500 0.7362 0.02233 0.01465 0.0142 0.3618 0.4557
8.750 0.7534 0.02293 0.01526 0.0144 0.3598 0.4575
9.000 0.7692 0.02362 0.01597 0.0147 0.3579 0.4592
9.250 0.7852 0.02432 0.01667 0.0149 0.3558 0.4611
9.500 0.7999 0.02517 0.01756 0.0152 0.3539 0.4629
9.750 0.8150 0.02604 0.01849 0.0153 0.3517 0.4645
10.250 0.8399 0.02815 0.02071 0.0157 0.3467 0.4684
10.500 0.8502 0.02938 0.02197 0.0159 0.3441 0.4706
10.750 0.8612 0.03058 0.02319 0.0161 0.3417 0.4729
11.000 0.8710 0.03195 0.02462 0.0162 0.3395 0.4751
11.250 0.8786 0.03354 0.02630 0.0164 0.3370 0.4774
11.500 0.8849 0.03525 0.02807 0.0165 0.3341 0.4796
11.750 0.8883 0.03720 0.03006 0.0167 0.3311 0.4817
12.000 0.8947 0.03893 0.03179 0.0168 0.3281 0.4839
12.250 0.8940 0.04131 0.03423 0.0171 0.3246 0.4857
12.500 0.8886 0.04416 0.03714 0.0175 0.3202 0.4872
12.750 0.8885 0.04653 0.03956 0.0176 0.3163 0.4897
13.000 0.8905 0.04874 0.04178 0.0176 0.3131 0.4927
13.250 0.8848 0.05175 0.04489 0.0178 0.3093 0.4954
13.500 0.8764 0.05500 0.04821 0.0181 0.3046 0.4981
13.750 0.8787 0.05729 0.05050 0.0180 0.3005 0.5013
14.000 0.8709 0.06059 0.05386 0.0181 0.2961 0.5041
14.250 0.8619 0.06404 0.05736 0.0182 0.2909 0.5067
14.500 0.8675 0.06612 0.05942 0.0179 0.2870 0.5095
14.750 0.8643 0.06908 0.06245 0.0178 0.2829 0.5125
15.000 0.8577 0.07241 0.06584 0.0176 0.2778 0.5159
15.250 0.8653 0.07435 0.06779 0.0172 0.2740 0.5201
15.500 0.8606 0.07758 0.07108 0.0170 0.2694 0.5237
15.750 0.8597 0.08043 0.07397 0.0166 0.2644 0.5275
16.000 0.8683 0.08231 0.07583 0.0161 0.2605 0.5317
16.500 0.8653 0.08828 0.08189 0.0152 0.2502 0.5398
16.750 0.8723 0.09038 0.08401 0.0146 0.2460 0.5455
17.000 0.8690 0.09360 0.08728 0.0141 0.2403 0.5504
17.250 0.8736 0.09596 0.08962 0.0135 0.2352 0.5557
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