E168 (12.45%) (e168-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.58 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e168-il-1000000-n5.txt Download as CSV file: xf-e168-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E168 (12.45%)
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
------ -------- --------- --------- -------- -------- --------
-18.500 -1.1393 0.11158 0.10847 0.0065 1.0000 0.0041
-18.250 -1.1585 0.10404 0.10081 0.0024 1.0000 0.0040
-18.000 -1.1799 0.09636 0.09301 -0.0017 1.0000 0.0040
-17.750 -1.1988 0.08929 0.08583 -0.0054 1.0000 0.0041
-17.500 -1.2179 0.08239 0.07882 -0.0089 1.0000 0.0041
-17.250 -1.2342 0.07614 0.07246 -0.0121 1.0000 0.0041
-17.000 -1.2514 0.06997 0.06618 -0.0152 1.0000 0.0041
-16.750 -1.2702 0.06380 0.05988 -0.0182 1.0000 0.0041
-16.500 -1.2861 0.05823 0.05420 -0.0208 1.0000 0.0042
-16.250 -1.2970 0.05345 0.04930 -0.0230 1.0000 0.0042
-16.000 -1.3112 0.04829 0.04402 -0.0253 1.0000 0.0042
-15.750 -1.3168 0.04441 0.04005 -0.0270 1.0000 0.0043
-15.500 -1.3229 0.04055 0.03606 -0.0286 1.0000 0.0044
-15.250 -1.3270 0.03709 0.03249 -0.0299 1.0000 0.0045
-15.000 -1.3278 0.03418 0.02949 -0.0307 1.0000 0.0045
-14.750 -1.3266 0.03170 0.02691 -0.0312 1.0000 0.0046
-14.500 -1.3260 0.02937 0.02449 -0.0312 1.0000 0.0047
-14.250 -1.3231 0.02753 0.02256 -0.0307 1.0000 0.0048
-14.000 -1.3211 0.02586 0.02080 -0.0297 1.0000 0.0049
-13.750 -1.3164 0.02461 0.01947 -0.0281 1.0000 0.0050
-13.500 -1.3121 0.02349 0.01827 -0.0260 1.0000 0.0051
-13.250 -1.3086 0.02246 0.01717 -0.0233 1.0000 0.0053
-13.000 -1.3019 0.02164 0.01629 -0.0206 1.0000 0.0056
-12.750 -1.2896 0.02089 0.01549 -0.0187 1.0000 0.0059
-12.500 -1.2747 0.02019 0.01474 -0.0172 1.0000 0.0062
-12.250 -1.2583 0.01952 0.01402 -0.0159 1.0000 0.0066
-12.000 -1.2405 0.01891 0.01336 -0.0147 1.0000 0.0069
-11.750 -1.2216 0.01835 0.01274 -0.0136 1.0000 0.0073
-11.500 -1.2030 0.01772 0.01208 -0.0124 1.0000 0.0079
-11.250 -1.1832 0.01716 0.01149 -0.0114 1.0000 0.0085
-11.000 -1.1625 0.01665 0.01095 -0.0104 1.0000 0.0092
-10.750 -1.1411 0.01619 0.01044 -0.0096 1.0000 0.0098
-10.500 -1.1194 0.01572 0.00994 -0.0087 1.0000 0.0105
-10.250 -1.0981 0.01522 0.00942 -0.0078 1.0000 0.0114
-10.000 -1.0759 0.01478 0.00896 -0.0070 1.0000 0.0124
-9.750 -1.0532 0.01439 0.00853 -0.0062 1.0000 0.0131
-9.500 -1.0304 0.01400 0.00811 -0.0054 1.0000 0.0139
-9.250 -1.0079 0.01356 0.00766 -0.0046 1.0000 0.0152
-9.000 -0.9850 0.01318 0.00726 -0.0038 1.0000 0.0165
-8.750 -0.9617 0.01284 0.00690 -0.0030 1.0000 0.0177
-8.500 -0.9390 0.01244 0.00651 -0.0021 1.0000 0.0203
-8.250 -0.9159 0.01209 0.00616 -0.0013 1.0000 0.0229
-8.000 -0.8933 0.01169 0.00578 -0.0004 1.0000 0.0278
-7.750 -0.8707 0.01130 0.00543 0.0005 1.0000 0.0344
-7.500 -0.8477 0.01093 0.00509 0.0014 1.0000 0.0415
-7.250 -0.8194 0.01058 0.00477 0.0012 0.9981 0.0495
-7.000 -0.7863 0.01022 0.00446 -0.0001 0.9925 0.0588
-6.750 -0.7535 0.00983 0.00413 -0.0014 0.9840 0.0718
-6.500 -0.7187 0.00943 0.00381 -0.0030 0.9639 0.0872
-6.250 -0.6756 0.00909 0.00346 -0.0064 0.9112 0.1051
-6.000 -0.6515 0.00896 0.00321 -0.0055 0.8570 0.1197
-5.750 -0.6274 0.00881 0.00299 -0.0046 0.8178 0.1361
-5.500 -0.6029 0.00857 0.00276 -0.0040 0.7867 0.1600
-5.250 -0.5776 0.00839 0.00257 -0.0035 0.7590 0.1796
-5.000 -0.5513 0.00827 0.00240 -0.0031 0.7342 0.1931
-4.750 -0.5246 0.00817 0.00226 -0.0028 0.7118 0.2037
-4.500 -0.4979 0.00806 0.00212 -0.0025 0.6902 0.2166
-4.250 -0.4710 0.00796 0.00199 -0.0023 0.6698 0.2294
-4.000 -0.4440 0.00786 0.00187 -0.0020 0.6508 0.2426
-3.750 -0.4167 0.00778 0.00176 -0.0018 0.6324 0.2544
-3.500 -0.3893 0.00771 0.00166 -0.0017 0.6148 0.2657
-3.250 -0.3618 0.00764 0.00157 -0.0015 0.5980 0.2774
-3.000 -0.3343 0.00757 0.00148 -0.0013 0.5822 0.2892
-2.750 -0.3067 0.00752 0.00141 -0.0012 0.5667 0.3000
-2.500 -0.2790 0.00747 0.00134 -0.0010 0.5519 0.3111
-2.250 -0.2512 0.00743 0.00127 -0.0009 0.5372 0.3222
-2.000 -0.2235 0.00738 0.00122 -0.0008 0.5233 0.3333
-1.750 -0.1956 0.00735 0.00117 -0.0007 0.5095 0.3438
-1.500 -0.1677 0.00732 0.00113 -0.0006 0.4961 0.3552
-1.250 -0.1398 0.00730 0.00110 -0.0005 0.4832 0.3658
-1.000 -0.1119 0.00728 0.00107 -0.0004 0.4704 0.3772
-0.500 -0.0559 0.00726 0.00103 -0.0002 0.4457 0.3988
-0.250 -0.0280 0.00725 0.00102 -0.0001 0.4337 0.4109
0.000 0.0000 0.00725 0.00102 0.0000 0.4223 0.4223
0.250 0.0279 0.00725 0.00102 0.0001 0.4110 0.4338
0.500 0.0559 0.00726 0.00103 0.0002 0.3990 0.4456
1.000 0.1119 0.00728 0.00107 0.0004 0.3772 0.4705
1.250 0.1397 0.00730 0.00110 0.0005 0.3658 0.4831
1.500 0.1677 0.00732 0.00113 0.0006 0.3551 0.4964
1.750 0.1956 0.00735 0.00117 0.0007 0.3438 0.5095
2.000 0.2234 0.00738 0.00122 0.0008 0.3334 0.5231
2.250 0.2511 0.00743 0.00127 0.0009 0.3220 0.5372
2.500 0.2789 0.00747 0.00134 0.0011 0.3111 0.5518
2.750 0.3067 0.00751 0.00141 0.0012 0.3002 0.5666
3.000 0.3343 0.00757 0.00148 0.0013 0.2891 0.5822
3.250 0.3618 0.00764 0.00157 0.0015 0.2774 0.5980
3.500 0.3892 0.00771 0.00166 0.0017 0.2659 0.6147
3.750 0.4166 0.00778 0.00176 0.0018 0.2542 0.6323
4.000 0.4439 0.00786 0.00187 0.0020 0.2424 0.6505
4.250 0.4709 0.00796 0.00199 0.0023 0.2295 0.6700
4.500 0.4978 0.00806 0.00212 0.0025 0.2166 0.6901
4.750 0.5245 0.00817 0.00226 0.0028 0.2038 0.7119
5.000 0.5512 0.00826 0.00240 0.0031 0.1932 0.7344
5.250 0.5775 0.00838 0.00257 0.0035 0.1802 0.7591
5.500 0.6029 0.00856 0.00276 0.0040 0.1603 0.7868
5.750 0.6273 0.00880 0.00299 0.0047 0.1363 0.8180
6.000 0.6514 0.00896 0.00321 0.0055 0.1198 0.8569
6.250 0.6755 0.00909 0.00346 0.0064 0.1052 0.9110
6.500 0.7188 0.00943 0.00381 0.0030 0.0873 0.9642
6.750 0.7533 0.00983 0.00413 0.0014 0.0717 0.9838
7.250 0.8193 0.01058 0.00477 -0.0011 0.0495 0.9980
7.500 0.8479 0.01093 0.00509 -0.0014 0.0418 1.0000
7.750 0.8707 0.01131 0.00543 -0.0005 0.0340 1.0000
8.000 0.8934 0.01169 0.00578 0.0004 0.0277 1.0000
8.250 0.9159 0.01209 0.00616 0.0013 0.0229 1.0000
8.500 0.9391 0.01243 0.00650 0.0021 0.0204 1.0000
8.750 0.9617 0.01284 0.00690 0.0030 0.0177 1.0000
9.000 0.9850 0.01318 0.00726 0.0038 0.0165 1.0000
9.250 1.0079 0.01356 0.00766 0.0046 0.0152 1.0000
9.500 1.0303 0.01400 0.00811 0.0055 0.0139 1.0000
9.750 1.0531 0.01438 0.00853 0.0062 0.0132 1.0000
10.000 1.0758 0.01478 0.00895 0.0070 0.0124 1.0000
10.250 1.0979 0.01522 0.00942 0.0078 0.0114 1.0000
10.500 1.1192 0.01573 0.00995 0.0088 0.0104 1.0000
10.750 1.1409 0.01620 0.01045 0.0096 0.0098 1.0000
11.000 1.1624 0.01665 0.01095 0.0105 0.0092 1.0000
11.250 1.1830 0.01715 0.01149 0.0114 0.0085 1.0000
11.500 1.2028 0.01771 0.01208 0.0124 0.0079 1.0000
11.750 1.2214 0.01834 0.01274 0.0136 0.0073 1.0000
12.000 1.2402 0.01891 0.01336 0.0147 0.0069 1.0000
12.250 1.2581 0.01951 0.01402 0.0159 0.0066 1.0000
12.500 1.2745 0.02017 0.01473 0.0173 0.0063 1.0000
12.750 1.2894 0.02089 0.01549 0.0188 0.0059 1.0000
13.000 1.3016 0.02164 0.01630 0.0207 0.0056 1.0000
13.250 1.3083 0.02246 0.01717 0.0233 0.0054 1.0000
13.500 1.3127 0.02345 0.01823 0.0260 0.0051 1.0000
13.750 1.3162 0.02462 0.01948 0.0281 0.0050 1.0000
14.000 1.3204 0.02591 0.02085 0.0297 0.0049 1.0000
14.250 1.3234 0.02751 0.02253 0.0307 0.0048 1.0000
14.500 1.3260 0.02938 0.02450 0.0312 0.0047 1.0000
14.750 1.3265 0.03171 0.02693 0.0311 0.0047 1.0000
15.000 1.3267 0.03432 0.02964 0.0306 0.0045 1.0000
15.250 1.3261 0.03722 0.03263 0.0298 0.0044 1.0000
15.500 1.3223 0.04067 0.03620 0.0285 0.0044 1.0000
15.750 1.3173 0.04438 0.04001 0.0270 0.0043 1.0000
16.000 1.3084 0.04874 0.04448 0.0250 0.0043 1.0000
16.250 1.2988 0.05325 0.04910 0.0230 0.0042 1.0000
16.500 1.2878 0.05806 0.05401 0.0208 0.0041 1.0000
16.750 1.2741 0.06331 0.05938 0.0183 0.0041 1.0000
17.000 1.2540 0.06967 0.06587 0.0152 0.0042 1.0000
17.250 1.2373 0.07574 0.07205 0.0122 0.0042 1.0000
17.500 1.2171 0.08262 0.07906 0.0087 0.0041 1.0000
17.750 1.1990 0.08936 0.08591 0.0052 0.0041 1.0000
18.000 1.1783 0.09675 0.09341 0.0013 0.0041 1.0000
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