E168 (12.45%) (e168-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: E168 (12.45%) (e168-il) Reynolds number: 50,000 Max Cl/Cd: 22.61 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e168-il-50000.txt Download as CSV file: xf-e168-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8344 0.07618 0.06930 -0.0201 1.0000 0.1375
-10.750 -0.8628 0.06955 0.06263 -0.0227 1.0000 0.1363
-10.500 -0.8927 0.06409 0.05705 -0.0229 1.0000 0.1353
-10.250 -0.9179 0.05880 0.05152 -0.0225 1.0000 0.1352
-10.000 -0.9382 0.05376 0.04604 -0.0214 1.0000 0.1367
-9.750 -0.9254 0.05102 0.04330 -0.0202 1.0000 0.1445
-9.500 -0.9332 0.04691 0.03866 -0.0185 1.0000 0.1508
-9.250 -0.9199 0.04468 0.03641 -0.0171 1.0000 0.1636
-9.000 -0.9091 0.04241 0.03401 -0.0155 1.0000 0.1784
-8.750 -0.8958 0.04051 0.03207 -0.0138 1.0000 0.1962
-8.500 -0.8758 0.03975 0.03147 -0.0120 1.0000 0.2190
-8.250 -0.8585 0.03880 0.03057 -0.0101 1.0000 0.2430
-8.000 -0.8459 0.03739 0.02894 -0.0081 1.0000 0.2677
-7.750 -0.8199 0.03757 0.02936 -0.0061 1.0000 0.2938
-7.500 -0.7976 0.03730 0.02915 -0.0041 1.0000 0.3183
-7.250 -0.7830 0.03613 0.02778 -0.0023 1.0000 0.3424
-7.000 -0.7543 0.03658 0.02837 -0.0001 1.0000 0.3642
-6.750 -0.7369 0.03560 0.02725 0.0016 1.0000 0.3858
-6.500 -0.7149 0.03511 0.02673 0.0035 1.0000 0.4057
-6.250 -0.6915 0.03477 0.02638 0.0053 1.0000 0.4244
-6.000 -0.6713 0.03399 0.02552 0.0070 1.0000 0.4429
-5.750 -0.6529 0.03296 0.02435 0.0085 1.0000 0.4614
-5.500 -0.6351 0.03185 0.02310 0.0099 1.0000 0.4794
-5.250 -0.6132 0.03122 0.02246 0.0116 1.0000 0.4959
-5.000 -0.5921 0.03050 0.02170 0.0132 1.0000 0.5122
-4.750 -0.5715 0.02977 0.02092 0.0148 1.0000 0.5285
-4.500 -0.5514 0.02900 0.02012 0.0164 1.0000 0.5448
-4.250 -0.5317 0.02826 0.01935 0.0180 1.0000 0.5613
-4.000 -0.5124 0.02752 0.01859 0.0197 1.0000 0.5779
-3.750 -0.4936 0.02680 0.01785 0.0214 1.0000 0.5948
-3.500 -0.4754 0.02609 0.01712 0.0231 1.0000 0.6120
-3.250 -0.4582 0.02539 0.01642 0.0248 1.0000 0.6300
-3.000 -0.4424 0.02468 0.01569 0.0266 1.0000 0.6485
-2.750 -0.4263 0.02418 0.01525 0.0288 1.0000 0.6658
-2.500 -0.4119 0.02371 0.01483 0.0311 1.0000 0.6834
-2.250 -0.3995 0.02328 0.01445 0.0335 1.0000 0.7022
-2.000 -0.3889 0.02286 0.01406 0.0358 1.0000 0.7222
-1.750 -0.3783 0.02252 0.01373 0.0380 1.0000 0.7429
-1.500 -0.3664 0.02231 0.01358 0.0401 1.0000 0.7642
-1.250 -0.3564 0.02210 0.01340 0.0420 1.0000 0.7885
-1.000 -0.3448 0.02200 0.01336 0.0439 1.0000 0.8137
-0.750 -0.3308 0.02195 0.01337 0.0453 1.0000 0.8424
-0.500 -0.2581 0.02271 0.01415 0.0365 0.9791 0.8787
-0.250 -0.1466 0.02369 0.01511 0.0213 0.9567 0.9106
0.000 0.0001 0.02421 0.01560 0.0000 0.9338 0.9338
0.250 0.1461 0.02369 0.01511 -0.0213 0.9106 0.9566
0.500 0.2578 0.02271 0.01416 -0.0365 0.8785 0.9789
0.750 0.3308 0.02195 0.01337 -0.0453 0.8422 1.0000
1.000 0.3448 0.02200 0.01336 -0.0439 0.8137 1.0000
1.250 0.3564 0.02210 0.01340 -0.0420 0.7886 1.0000
1.500 0.3663 0.02231 0.01358 -0.0401 0.7643 1.0000
1.750 0.3783 0.02251 0.01373 -0.0380 0.7429 1.0000
2.000 0.3888 0.02286 0.01406 -0.0358 0.7221 1.0000
2.250 0.3995 0.02328 0.01445 -0.0335 0.7021 1.0000
2.500 0.4119 0.02371 0.01483 -0.0310 0.6834 1.0000
2.750 0.4263 0.02418 0.01525 -0.0288 0.6657 1.0000
3.000 0.4424 0.02467 0.01570 -0.0266 0.6485 1.0000
3.250 0.4582 0.02539 0.01642 -0.0248 0.6300 1.0000
3.500 0.4754 0.02609 0.01713 -0.0231 0.6121 1.0000
3.750 0.4936 0.02680 0.01784 -0.0214 0.5948 1.0000
4.000 0.5124 0.02752 0.01857 -0.0197 0.5779 1.0000
4.250 0.5317 0.02826 0.01935 -0.0180 0.5613 1.0000
4.500 0.5514 0.02900 0.02011 -0.0164 0.5448 1.0000
4.750 0.5716 0.02976 0.02091 -0.0148 0.5285 1.0000
5.000 0.5921 0.03049 0.02169 -0.0132 0.5122 1.0000
5.250 0.6132 0.03122 0.02245 -0.0116 0.4959 1.0000
5.500 0.6350 0.03185 0.02311 -0.0099 0.4794 1.0000
5.750 0.6529 0.03297 0.02436 -0.0085 0.4614 1.0000
6.250 0.6915 0.03476 0.02637 -0.0053 0.4244 1.0000
6.500 0.7149 0.03512 0.02674 -0.0035 0.4057 1.0000
6.750 0.7368 0.03560 0.02725 -0.0016 0.3858 1.0000
7.000 0.7543 0.03658 0.02837 0.0001 0.3642 1.0000
7.250 0.7830 0.03613 0.02778 0.0023 0.3423 1.0000
7.500 0.7976 0.03729 0.02914 0.0041 0.3183 1.0000
7.750 0.8198 0.03756 0.02936 0.0061 0.2938 1.0000
8.000 0.8457 0.03740 0.02895 0.0081 0.2676 1.0000
8.250 0.8585 0.03880 0.03057 0.0101 0.2429 1.0000
8.500 0.8758 0.03975 0.03148 0.0120 0.2190 1.0000
8.750 0.8960 0.04048 0.03202 0.0138 0.1961 1.0000
9.000 0.9089 0.04243 0.03403 0.0155 0.1783 1.0000
9.250 0.9197 0.04469 0.03642 0.0171 0.1635 1.0000
9.500 0.9333 0.04692 0.03865 0.0185 0.1509 1.0000
9.750 0.9253 0.05105 0.04333 0.0202 0.1447 1.0000
10.000 0.9384 0.05375 0.04603 0.0213 0.1367 1.0000
10.250 0.9182 0.05878 0.05150 0.0225 0.1352 1.0000
10.500 0.8926 0.06413 0.05709 0.0229 0.1353 1.0000
10.750 0.8631 0.06958 0.06265 0.0226 0.1363 1.0000
11.000 0.8351 0.07617 0.06929 0.0201 0.1375 1.0000
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Polar data table (+)
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