E169 (14.4%) (e169-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.59 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e169-il-1000000-n5.txt Download as CSV file: xf-e169-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E169 (14.4%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -1.1885 0.10139 0.09771 -0.0015 1.0000 0.0058
-18.500 -1.2008 0.09566 0.09189 -0.0043 1.0000 0.0058
-18.250 -1.2145 0.08979 0.08592 -0.0072 1.0000 0.0058
-18.000 -1.2252 0.08454 0.08057 -0.0096 1.0000 0.0059
-17.750 -1.2357 0.07944 0.07537 -0.0119 1.0000 0.0061
-17.500 -1.2469 0.07434 0.07018 -0.0142 1.0000 0.0060
-17.250 -1.2580 0.06938 0.06512 -0.0164 1.0000 0.0061
-17.000 -1.2689 0.06456 0.06020 -0.0184 1.0000 0.0061
-16.750 -1.2794 0.05996 0.05551 -0.0203 1.0000 0.0063
-16.500 -1.2902 0.05551 0.05097 -0.0220 1.0000 0.0064
-16.250 -1.2991 0.05137 0.04674 -0.0235 1.0000 0.0066
-16.000 -1.3071 0.04741 0.04270 -0.0248 1.0000 0.0068
-15.750 -1.3121 0.04386 0.03906 -0.0260 1.0000 0.0069
-15.500 -1.3155 0.04055 0.03568 -0.0270 1.0000 0.0072
-15.250 -1.3172 0.03749 0.03254 -0.0279 1.0000 0.0074
-15.000 -1.3165 0.03479 0.02975 -0.0285 1.0000 0.0076
-14.750 -1.3153 0.03221 0.02710 -0.0291 1.0000 0.0078
-14.500 -1.3119 0.02999 0.02480 -0.0293 1.0000 0.0081
-14.250 -1.3078 0.02797 0.02271 -0.0293 1.0000 0.0082
-14.000 -1.3032 0.02619 0.02085 -0.0290 1.0000 0.0086
-13.750 -1.2996 0.02453 0.01912 -0.0282 1.0000 0.0090
-13.500 -1.2952 0.02315 0.01768 -0.0269 1.0000 0.0093
-13.250 -1.2892 0.02206 0.01654 -0.0252 1.0000 0.0097
-13.000 -1.2820 0.02117 0.01560 -0.0232 1.0000 0.0101
-12.750 -1.2736 0.02043 0.01481 -0.0209 1.0000 0.0105
-12.500 -1.2640 0.01981 0.01414 -0.0184 1.0000 0.0109
-12.250 -1.2519 0.01918 0.01347 -0.0164 1.0000 0.0114
-12.000 -1.2373 0.01852 0.01278 -0.0148 1.0000 0.0121
-11.750 -1.2206 0.01794 0.01216 -0.0134 1.0000 0.0127
-11.500 -1.2024 0.01741 0.01160 -0.0121 1.0000 0.0134
-11.250 -1.1829 0.01693 0.01108 -0.0110 1.0000 0.0140
-11.000 -1.1636 0.01641 0.01054 -0.0099 1.0000 0.0149
-10.750 -1.1438 0.01590 0.01002 -0.0088 1.0000 0.0160
-10.500 -1.1230 0.01545 0.00954 -0.0078 1.0000 0.0172
-10.250 -1.1020 0.01500 0.00907 -0.0069 1.0000 0.0187
-10.000 -1.0809 0.01454 0.00861 -0.0059 1.0000 0.0206
-9.750 -1.0591 0.01413 0.00819 -0.0050 1.0000 0.0229
-9.500 -1.0378 0.01367 0.00775 -0.0040 1.0000 0.0263
-9.250 -1.0161 0.01324 0.00734 -0.0031 1.0000 0.0303
-9.000 -0.9943 0.01282 0.00693 -0.0021 1.0000 0.0355
-8.750 -0.9728 0.01239 0.00654 -0.0011 1.0000 0.0422
-8.500 -0.9464 0.01194 0.00614 -0.0011 0.9968 0.0502
-8.250 -0.9138 0.01148 0.00573 -0.0024 0.9851 0.0602
-8.000 -0.8694 0.01100 0.00528 -0.0062 0.9422 0.0723
-7.750 -0.8407 0.01078 0.00491 -0.0064 0.8632 0.0834
-7.500 -0.8182 0.01056 0.00459 -0.0054 0.8195 0.0951
-7.250 -0.7946 0.01031 0.00429 -0.0046 0.7866 0.1091
-7.000 -0.7703 0.01005 0.00400 -0.0040 0.7588 0.1244
-6.750 -0.7452 0.00982 0.00374 -0.0035 0.7350 0.1384
-6.500 -0.7204 0.00952 0.00347 -0.0030 0.7134 0.1578
-6.250 -0.6951 0.00925 0.00323 -0.0026 0.6929 0.1783
-6.000 -0.6689 0.00906 0.00303 -0.0023 0.6746 0.1933
-5.750 -0.6424 0.00889 0.00285 -0.0020 0.6582 0.2054
-5.500 -0.6154 0.00876 0.00269 -0.0018 0.6415 0.2154
-5.000 -0.5612 0.00850 0.00239 -0.0014 0.6113 0.2393
-4.750 -0.5340 0.00837 0.00226 -0.0012 0.5974 0.2509
-4.500 -0.5067 0.00826 0.00213 -0.0011 0.5837 0.2627
-4.250 -0.4791 0.00816 0.00202 -0.0010 0.5711 0.2729
-4.000 -0.4513 0.00809 0.00192 -0.0008 0.5591 0.2837
-3.500 -0.3958 0.00792 0.00174 -0.0006 0.5353 0.3041
-3.250 -0.3677 0.00787 0.00167 -0.0006 0.5246 0.3126
-3.000 -0.3398 0.00782 0.00159 -0.0005 0.5136 0.3212
-2.750 -0.3115 0.00779 0.00153 -0.0004 0.5032 0.3288
-2.500 -0.2834 0.00774 0.00148 -0.0004 0.4934 0.3363
-2.250 -0.2552 0.00772 0.00143 -0.0003 0.4835 0.3439
-2.000 -0.2269 0.00767 0.00138 -0.0003 0.4742 0.3514
-1.750 -0.1986 0.00766 0.00134 -0.0002 0.4650 0.3583
-1.500 -0.1703 0.00763 0.00131 -0.0002 0.4557 0.3656
-1.250 -0.1419 0.00762 0.00128 -0.0001 0.4476 0.3727
-1.000 -0.1136 0.00761 0.00125 -0.0001 0.4391 0.3798
-0.750 -0.0852 0.00759 0.00124 -0.0001 0.4314 0.3871
-0.500 -0.0568 0.00759 0.00122 -0.0001 0.4233 0.3937
-0.250 -0.0284 0.00758 0.00122 0.0000 0.4160 0.4015
0.000 0.0000 0.00759 0.00121 0.0000 0.4082 0.4083
0.250 0.0284 0.00758 0.00122 0.0000 0.4015 0.4161
0.500 0.0568 0.00759 0.00122 0.0001 0.3937 0.4233
0.750 0.0852 0.00759 0.00124 0.0001 0.3871 0.4314
1.000 0.1136 0.00761 0.00125 0.0001 0.3798 0.4390
1.250 0.1419 0.00762 0.00128 0.0002 0.3727 0.4476
1.500 0.1703 0.00763 0.00131 0.0002 0.3656 0.4557
1.750 0.1986 0.00766 0.00134 0.0002 0.3583 0.4651
2.000 0.2269 0.00767 0.00138 0.0003 0.3514 0.4739
2.250 0.2551 0.00772 0.00143 0.0003 0.3439 0.4834
2.500 0.2834 0.00774 0.00148 0.0004 0.3364 0.4937
2.750 0.3115 0.00779 0.00153 0.0004 0.3289 0.5032
3.000 0.3398 0.00782 0.00159 0.0005 0.3210 0.5137
3.250 0.3677 0.00787 0.00167 0.0006 0.3127 0.5246
3.500 0.3958 0.00792 0.00174 0.0006 0.3043 0.5352
4.000 0.4513 0.00809 0.00192 0.0008 0.2839 0.5590
4.250 0.4790 0.00816 0.00202 0.0010 0.2730 0.5710
4.500 0.5066 0.00826 0.00213 0.0011 0.2626 0.5837
4.750 0.5340 0.00837 0.00226 0.0013 0.2508 0.5974
5.000 0.5612 0.00850 0.00239 0.0014 0.2393 0.6113
5.500 0.6154 0.00876 0.00269 0.0018 0.2152 0.6416
5.750 0.6423 0.00889 0.00285 0.0020 0.2053 0.6582
6.000 0.6689 0.00906 0.00303 0.0023 0.1934 0.6746
6.250 0.6950 0.00924 0.00323 0.0026 0.1794 0.6931
6.500 0.7203 0.00951 0.00347 0.0031 0.1578 0.7139
6.750 0.7451 0.00981 0.00374 0.0035 0.1385 0.7351
7.000 0.7702 0.01005 0.00400 0.0040 0.1244 0.7585
7.250 0.7945 0.01031 0.00429 0.0046 0.1093 0.7858
7.500 0.8180 0.01057 0.00460 0.0054 0.0947 0.8195
7.750 0.8406 0.01079 0.00491 0.0064 0.0833 0.8629
8.000 0.8698 0.01100 0.00529 0.0061 0.0721 0.9433
8.250 0.9137 0.01148 0.00573 0.0024 0.0602 0.9851
8.500 0.9463 0.01194 0.00614 0.0011 0.0504 0.9967
8.750 0.9728 0.01239 0.00654 0.0011 0.0423 1.0000
9.000 0.9944 0.01282 0.00693 0.0021 0.0356 1.0000
9.250 1.0161 0.01324 0.00734 0.0031 0.0303 1.0000
9.500 1.0377 0.01367 0.00775 0.0040 0.0262 1.0000
9.750 1.0591 0.01412 0.00818 0.0050 0.0231 1.0000
10.000 1.0809 0.01453 0.00860 0.0059 0.0209 1.0000
10.250 1.1018 0.01500 0.00907 0.0069 0.0187 1.0000
10.500 1.1229 0.01545 0.00954 0.0079 0.0172 1.0000
10.750 1.1437 0.01589 0.01001 0.0088 0.0161 1.0000
11.000 1.1634 0.01641 0.01053 0.0099 0.0149 1.0000
11.250 1.1828 0.01692 0.01108 0.0111 0.0140 1.0000
11.500 1.2022 0.01741 0.01160 0.0122 0.0134 1.0000
11.750 1.2204 0.01793 0.01215 0.0134 0.0127 1.0000
12.000 1.2371 0.01852 0.01277 0.0148 0.0120 1.0000
12.250 1.2518 0.01917 0.01346 0.0164 0.0114 1.0000
12.500 1.2638 0.01981 0.01413 0.0185 0.0109 1.0000
12.750 1.2736 0.02042 0.01480 0.0209 0.0105 1.0000
13.000 1.2818 0.02116 0.01559 0.0232 0.0102 1.0000
13.250 1.2892 0.02205 0.01653 0.0252 0.0098 1.0000
13.500 1.2951 0.02315 0.01767 0.0269 0.0092 1.0000
13.750 1.2997 0.02451 0.01910 0.0282 0.0088 1.0000
14.000 1.3030 0.02620 0.02086 0.0290 0.0084 1.0000
14.250 1.3079 0.02796 0.02269 0.0293 0.0082 1.0000
14.500 1.3125 0.02993 0.02474 0.0293 0.0080 1.0000
14.750 1.3156 0.03219 0.02707 0.0290 0.0077 1.0000
15.000 1.3176 0.03467 0.02963 0.0285 0.0075 1.0000
15.250 1.3176 0.03747 0.03251 0.0278 0.0072 1.0000
15.500 1.3160 0.04051 0.03563 0.0270 0.0069 1.0000
15.750 1.3123 0.04386 0.03906 0.0259 0.0068 1.0000
16.000 1.3072 0.04744 0.04273 0.0248 0.0068 1.0000
16.250 1.3003 0.05127 0.04663 0.0234 0.0065 1.0000
16.500 1.2915 0.05540 0.05086 0.0219 0.0064 1.0000
16.750 1.2826 0.05959 0.05515 0.0203 0.0064 1.0000
17.000 1.2695 0.06453 0.06018 0.0183 0.0061 1.0000
17.250 1.2584 0.06938 0.06512 0.0163 0.0061 1.0000
17.500 1.2493 0.07406 0.06989 0.0142 0.0061 1.0000
17.750 1.2374 0.07926 0.07519 0.0119 0.0060 1.0000
18.000 1.2249 0.08467 0.08070 0.0094 0.0060 1.0000
18.250 1.2130 0.09011 0.08625 0.0069 0.0060 1.0000
18.500 1.2033 0.09533 0.09156 0.0044 0.0059 1.0000
18.750 1.1908 0.10110 0.09742 0.0015 0.0058 1.0000
19.000 1.1773 0.10719 0.10361 -0.0015 0.0057 1.0000
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Polar data table (+)
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