E168 (12.45%) (e168-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 500,000 Max Cl/Cd: 73 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e168-il-500000.txt Download as CSV file: xf-e168-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.9294 0.15099 0.14833 0.0283 1.0000 0.0112
-18.000 -0.9578 0.13900 0.13617 0.0212 1.0000 0.0111
-17.750 -0.9805 0.12911 0.12612 0.0154 1.0000 0.0110
-17.500 -0.9978 0.12075 0.11761 0.0104 1.0000 0.0110
-17.250 -1.0127 0.11324 0.10997 0.0061 1.0000 0.0110
-17.000 -1.0270 0.10609 0.10269 0.0020 1.0000 0.0111
-16.750 -1.0395 0.09954 0.09600 -0.0016 1.0000 0.0111
-16.500 -1.0508 0.09338 0.08971 -0.0050 1.0000 0.0111
-16.250 -1.0611 0.08762 0.08382 -0.0080 1.0000 0.0112
-16.000 -1.0701 0.08220 0.07828 -0.0109 1.0000 0.0113
-15.750 -1.0795 0.07692 0.07288 -0.0136 1.0000 0.0114
-15.500 -1.0864 0.07219 0.06803 -0.0160 1.0000 0.0115
-15.250 -1.0939 0.06757 0.06328 -0.0182 1.0000 0.0117
-15.000 -1.1014 0.06312 0.05870 -0.0202 1.0000 0.0118
-14.750 -1.1060 0.05910 0.05456 -0.0221 1.0000 0.0120
-14.500 -1.1107 0.05534 0.05070 -0.0235 1.0000 0.0119
-14.250 -1.1128 0.05173 0.04695 -0.0252 1.0000 0.0122
-14.000 -1.1204 0.04783 0.04293 -0.0262 1.0000 0.0123
-13.750 -1.1287 0.04394 0.03894 -0.0272 1.0000 0.0125
-13.500 -1.1341 0.04042 0.03534 -0.0282 1.0000 0.0129
-13.250 -1.1368 0.03730 0.03214 -0.0290 1.0000 0.0132
-13.000 -1.1353 0.03479 0.02955 -0.0295 1.0000 0.0135
-12.750 -1.1318 0.03267 0.02736 -0.0297 1.0000 0.0140
-12.500 -1.1312 0.03048 0.02507 -0.0293 1.0000 0.0143
-12.250 -1.1281 0.02875 0.02324 -0.0285 1.0000 0.0149
-12.000 -1.1254 0.02721 0.02158 -0.0269 1.0000 0.0152
-11.750 -1.1171 0.02622 0.02049 -0.0253 1.0000 0.0157
-11.500 -1.1230 0.02453 0.01870 -0.0216 1.0000 0.0162
-11.250 -1.1205 0.02314 0.01727 -0.0188 1.0000 0.0170
-11.000 -1.1081 0.02220 0.01627 -0.0171 1.0000 0.0178
-10.750 -1.0938 0.02130 0.01530 -0.0156 1.0000 0.0188
-10.500 -1.0767 0.02056 0.01447 -0.0142 1.0000 0.0199
-10.250 -1.0641 0.01938 0.01321 -0.0124 1.0000 0.0212
-10.000 -1.0472 0.01853 0.01232 -0.0111 1.0000 0.0229
-9.750 -1.0270 0.01793 0.01166 -0.0100 1.0000 0.0248
-9.500 -1.0091 0.01707 0.01074 -0.0087 1.0000 0.0271
-9.250 -0.9894 0.01636 0.01003 -0.0076 1.0000 0.0302
-9.000 -0.9691 0.01568 0.00930 -0.0065 1.0000 0.0340
-8.750 -0.9484 0.01503 0.00864 -0.0054 1.0000 0.0396
-8.500 -0.9283 0.01432 0.00796 -0.0043 1.0000 0.0486
-8.250 -0.9073 0.01368 0.00737 -0.0033 1.0000 0.0605
-8.000 -0.8866 0.01303 0.00681 -0.0022 1.0000 0.0761
-7.750 -0.8652 0.01245 0.00632 -0.0012 1.0000 0.0939
-7.500 -0.8435 0.01192 0.00586 -0.0002 1.0000 0.1135
-7.250 -0.8215 0.01142 0.00547 0.0007 1.0000 0.1356
-7.000 -0.7991 0.01099 0.00513 0.0017 1.0000 0.1562
-6.750 -0.7760 0.01063 0.00484 0.0025 1.0000 0.1756
-6.500 -0.7525 0.01033 0.00457 0.0033 1.0000 0.1934
-6.250 -0.7288 0.01005 0.00433 0.0041 1.0000 0.2098
-6.000 -0.7053 0.00977 0.00412 0.0049 1.0000 0.2263
-5.750 -0.6817 0.00952 0.00393 0.0058 1.0000 0.2436
-5.500 -0.6580 0.00930 0.00374 0.0066 1.0000 0.2581
-5.250 -0.6342 0.00911 0.00357 0.0074 1.0000 0.2711
-5.000 -0.6106 0.00894 0.00342 0.0083 1.0000 0.2836
-4.500 -0.5390 0.00857 0.00314 0.0048 0.9909 0.3142
-4.250 -0.4983 0.00838 0.00300 0.0021 0.9814 0.3306
-4.000 -0.4604 0.00819 0.00285 0.0000 0.9651 0.3461
-3.750 -0.4182 0.00801 0.00270 -0.0029 0.9427 0.3620
-3.250 -0.3467 0.00783 0.00241 -0.0056 0.8685 0.3917
-3.000 -0.3208 0.00784 0.00230 -0.0049 0.8327 0.4047
-2.750 -0.2950 0.00785 0.00221 -0.0042 0.8013 0.4179
-2.500 -0.2691 0.00784 0.00213 -0.0036 0.7732 0.4310
-2.250 -0.2427 0.00782 0.00206 -0.0031 0.7478 0.4442
-2.000 -0.2163 0.00781 0.00199 -0.0026 0.7244 0.4575
-1.750 -0.1895 0.00779 0.00193 -0.0022 0.7022 0.4710
-1.500 -0.1627 0.00779 0.00187 -0.0019 0.6813 0.4848
-1.250 -0.1357 0.00778 0.00183 -0.0015 0.6618 0.4988
-1.000 -0.1086 0.00777 0.00179 -0.0012 0.6427 0.5131
-0.750 -0.0815 0.00776 0.00177 -0.0009 0.6245 0.5279
-0.500 -0.0543 0.00776 0.00175 -0.0006 0.6070 0.5428
-0.250 -0.0272 0.00776 0.00174 -0.0003 0.5903 0.5582
0.000 0.0000 0.00776 0.00173 0.0000 0.5739 0.5739
0.250 0.0271 0.00776 0.00174 0.0003 0.5582 0.5902
0.500 0.0543 0.00776 0.00175 0.0006 0.5428 0.6070
0.750 0.0815 0.00776 0.00177 0.0009 0.5279 0.6245
1.000 0.1086 0.00777 0.00179 0.0012 0.5131 0.6427
1.250 0.1357 0.00778 0.00183 0.0015 0.4988 0.6618
1.500 0.1627 0.00779 0.00187 0.0019 0.4849 0.6813
1.750 0.1895 0.00779 0.00193 0.0023 0.4709 0.7022
2.000 0.2163 0.00781 0.00199 0.0026 0.4576 0.7244
2.250 0.2427 0.00782 0.00206 0.0031 0.4442 0.7478
2.500 0.2690 0.00783 0.00213 0.0036 0.4310 0.7733
2.750 0.2949 0.00785 0.00221 0.0042 0.4180 0.8014
3.000 0.3208 0.00784 0.00230 0.0049 0.4046 0.8325
3.250 0.3466 0.00783 0.00240 0.0057 0.3916 0.8685
3.500 0.3763 0.00787 0.00254 0.0056 0.3779 0.9103
3.750 0.4183 0.00801 0.00270 0.0029 0.3620 0.9429
4.000 0.4603 0.00819 0.00285 0.0000 0.3460 0.9650
4.250 0.4983 0.00838 0.00300 -0.0021 0.3305 0.9815
4.500 0.5390 0.00858 0.00314 -0.0048 0.3141 0.9909
5.000 0.6106 0.00894 0.00342 -0.0083 0.2836 1.0000
5.250 0.6342 0.00911 0.00357 -0.0074 0.2710 1.0000
5.500 0.6580 0.00930 0.00374 -0.0066 0.2582 1.0000
5.750 0.6817 0.00952 0.00393 -0.0058 0.2434 1.0000
6.000 0.7053 0.00977 0.00412 -0.0049 0.2264 1.0000
6.250 0.7288 0.01005 0.00433 -0.0041 0.2099 1.0000
6.500 0.7525 0.01033 0.00458 -0.0033 0.1937 1.0000
6.750 0.7760 0.01063 0.00484 -0.0025 0.1755 1.0000
7.000 0.7991 0.01099 0.00513 -0.0017 0.1562 1.0000
7.250 0.8215 0.01142 0.00547 -0.0007 0.1355 1.0000
7.500 0.8435 0.01192 0.00586 0.0002 0.1135 1.0000
7.750 0.8652 0.01245 0.00632 0.0012 0.0937 1.0000
8.000 0.8865 0.01303 0.00681 0.0022 0.0760 1.0000
8.250 0.9073 0.01368 0.00737 0.0033 0.0606 1.0000
8.500 0.9282 0.01432 0.00796 0.0043 0.0485 1.0000
8.750 0.9484 0.01503 0.00864 0.0054 0.0395 1.0000
9.000 0.9689 0.01570 0.00931 0.0065 0.0339 1.0000
9.250 0.9892 0.01637 0.01003 0.0076 0.0302 1.0000
9.500 1.0091 0.01706 0.01074 0.0087 0.0272 1.0000
9.750 1.0270 0.01792 0.01165 0.0101 0.0249 1.0000
10.000 1.0471 0.01852 0.01232 0.0111 0.0230 1.0000
10.250 1.0642 0.01938 0.01321 0.0124 0.0212 1.0000
10.500 1.0769 0.02054 0.01445 0.0142 0.0198 1.0000
10.750 1.0936 0.02131 0.01531 0.0156 0.0189 1.0000
11.000 1.1084 0.02217 0.01623 0.0171 0.0178 1.0000
11.250 1.1204 0.02315 0.01727 0.0188 0.0170 1.0000
11.500 1.1223 0.02456 0.01874 0.0217 0.0162 1.0000
11.750 1.1196 0.02607 0.02034 0.0250 0.0156 1.0000
12.000 1.1228 0.02740 0.02178 0.0271 0.0154 1.0000
12.250 1.1278 0.02878 0.02327 0.0285 0.0149 1.0000
12.500 1.1296 0.03064 0.02524 0.0294 0.0144 1.0000
12.750 1.1338 0.03250 0.02718 0.0296 0.0139 1.0000
13.000 1.1359 0.03477 0.02953 0.0295 0.0135 1.0000
13.250 1.1374 0.03728 0.03211 0.0289 0.0131 1.0000
13.500 1.1349 0.04037 0.03529 0.0282 0.0129 1.0000
13.750 1.1321 0.04362 0.03863 0.0272 0.0127 1.0000
14.000 1.1219 0.04773 0.04283 0.0262 0.0123 1.0000
14.250 1.1145 0.05166 0.04688 0.0250 0.0121 1.0000
14.500 1.1121 0.05526 0.05062 0.0234 0.0119 1.0000
14.750 1.1076 0.05914 0.05462 0.0217 0.0118 1.0000
15.000 1.1019 0.06322 0.05882 0.0200 0.0117 1.0000
15.250 1.0956 0.06749 0.06320 0.0181 0.0116 1.0000
15.500 1.0877 0.07215 0.06799 0.0159 0.0115 1.0000
15.750 1.0811 0.07685 0.07280 0.0134 0.0114 1.0000
16.000 1.0715 0.08220 0.07828 0.0106 0.0112 1.0000
16.250 1.0630 0.08747 0.08367 0.0079 0.0112 1.0000
16.500 1.0530 0.09324 0.08956 0.0048 0.0111 1.0000
16.750 1.0429 0.09921 0.09565 0.0015 0.0109 1.0000
17.000 1.0303 0.10578 0.10236 -0.0022 0.0109 1.0000
17.250 1.0165 0.11281 0.10952 -0.0061 0.0108 1.0000
17.500 0.9994 0.12075 0.11761 -0.0107 0.0110 1.0000
17.750 0.9814 0.12920 0.12621 -0.0156 0.0111 1.0000
18.000 0.9571 0.13955 0.13673 -0.0217 0.0111 1.0000
18.250 0.9269 0.15206 0.14942 -0.0291 0.0113 1.0000
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