E178 (8.69%) (e178-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 500,000 Max Cl/Cd: 105.01 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e178-il-500000.txt Download as CSV file: xf-e178-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4638 0.08851 0.08646 -0.0137 1.0000 0.0155
-8.500 -0.4608 0.08513 0.08311 -0.0151 1.0000 0.0158
-8.250 -0.4584 0.08177 0.07978 -0.0167 1.0000 0.0161
-8.000 -0.4578 0.07819 0.07624 -0.0187 1.0000 0.0162
-7.750 -0.4602 0.07445 0.07254 -0.0211 1.0000 0.0164
-7.500 -0.4569 0.07035 0.06846 -0.0251 1.0000 0.0167
-7.250 -0.4508 0.06543 0.06355 -0.0303 1.0000 0.0169
-7.000 -0.4419 0.06028 0.05837 -0.0352 1.0000 0.0172
-6.500 -0.4046 0.04833 0.04600 -0.0466 0.9017 0.0187
-6.250 -0.3937 0.04340 0.04077 -0.0477 0.8751 0.0195
-6.000 -0.3700 0.04019 0.03714 -0.0477 0.8554 0.0225
-5.000 -0.3053 0.01982 0.01469 -0.0463 0.8017 0.0193
-4.750 -0.2803 0.01795 0.01244 -0.0456 0.7909 0.0202
-4.500 -0.2547 0.01589 0.01000 -0.0449 0.7809 0.0204
-4.250 -0.2285 0.01459 0.00844 -0.0444 0.7717 0.0211
-4.000 -0.2019 0.01363 0.00728 -0.0439 0.7628 0.0218
-3.750 -0.1747 0.01307 0.00659 -0.0436 0.7540 0.0230
-3.500 -0.1497 0.01158 0.00489 -0.0430 0.7465 0.0242
-3.250 -0.1232 0.01085 0.00406 -0.0426 0.7383 0.0258
-3.000 -0.0963 0.01041 0.00353 -0.0423 0.7312 0.0273
-2.750 -0.0689 0.01006 0.00312 -0.0421 0.7237 0.0293
-2.500 -0.0415 0.00981 0.00275 -0.0419 0.7170 0.0321
-2.250 -0.0139 0.00943 0.00233 -0.0417 0.7101 0.0401
-2.000 0.0125 0.00886 0.00204 -0.0416 0.7040 0.1210
-1.750 0.0394 0.00846 0.00190 -0.0415 0.6972 0.2034
-1.500 0.0656 0.00805 0.00180 -0.0414 0.6916 0.3133
-1.250 0.0910 0.00745 0.00174 -0.0413 0.6850 0.4755
-1.000 0.1153 0.00694 0.00170 -0.0406 0.6793 0.6305
-0.750 0.1359 0.00634 0.00172 -0.0388 0.6736 0.8125
-0.500 0.1889 0.00608 0.00170 -0.0434 0.6676 0.9831
-0.250 0.2341 0.00611 0.00161 -0.0472 0.6620 1.0000
0.000 0.2603 0.00614 0.00158 -0.0469 0.6559 1.0000
0.250 0.2864 0.00622 0.00156 -0.0465 0.6506 1.0000
0.500 0.3129 0.00626 0.00156 -0.0462 0.6445 1.0000
0.750 0.3393 0.00632 0.00155 -0.0458 0.6389 1.0000
1.000 0.3658 0.00639 0.00157 -0.0455 0.6334 1.0000
1.250 0.3925 0.00644 0.00160 -0.0452 0.6273 1.0000
1.500 0.4190 0.00653 0.00162 -0.0449 0.6216 1.0000
1.750 0.4458 0.00657 0.00165 -0.0447 0.6139 1.0000
2.000 0.4725 0.00665 0.00167 -0.0444 0.6073 1.0000
2.250 0.4995 0.00669 0.00172 -0.0442 0.5997 1.0000
2.500 0.5263 0.00678 0.00177 -0.0439 0.5926 1.0000
2.750 0.5534 0.00682 0.00182 -0.0437 0.5842 1.0000
3.000 0.5804 0.00690 0.00189 -0.0435 0.5761 1.0000
3.250 0.6073 0.00698 0.00194 -0.0433 0.5674 1.0000
3.500 0.6345 0.00703 0.00204 -0.0431 0.5580 1.0000
3.750 0.6615 0.00712 0.00213 -0.0430 0.5488 1.0000
4.000 0.6884 0.00721 0.00221 -0.0428 0.5384 1.0000
4.250 0.7154 0.00730 0.00231 -0.0426 0.5261 1.0000
4.500 0.7423 0.00740 0.00244 -0.0424 0.5127 1.0000
4.750 0.7690 0.00753 0.00257 -0.0422 0.4978 1.0000
5.000 0.7958 0.00765 0.00272 -0.0420 0.4812 1.0000
5.250 0.8222 0.00783 0.00288 -0.0418 0.4586 1.0000
5.500 0.8480 0.00808 0.00309 -0.0415 0.4285 1.0000
5.750 0.8722 0.00854 0.00335 -0.0410 0.3720 1.0000
6.000 0.8926 0.00957 0.00388 -0.0403 0.2715 1.0000
6.250 0.9131 0.01060 0.00450 -0.0397 0.1921 1.0000
6.500 0.9344 0.01149 0.00509 -0.0391 0.1332 1.0000
6.750 0.9559 0.01231 0.00568 -0.0386 0.0901 1.0000
7.000 0.9772 0.01314 0.00633 -0.0379 0.0539 1.0000
7.250 0.9944 0.01454 0.00746 -0.0366 0.0156 1.0000
7.500 1.0152 0.01543 0.00847 -0.0356 0.0124 1.0000
7.750 1.0361 0.01623 0.00937 -0.0346 0.0113 1.0000
8.000 1.0557 0.01712 0.01034 -0.0336 0.0103 1.0000
8.250 1.0723 0.01828 0.01159 -0.0322 0.0093 1.0000
8.500 1.0834 0.02002 0.01346 -0.0302 0.0086 1.0000
8.750 1.0994 0.02115 0.01473 -0.0287 0.0084 1.0000
9.000 1.1155 0.02225 0.01594 -0.0273 0.0081 1.0000
9.250 1.1295 0.02360 0.01742 -0.0256 0.0079 1.0000
9.500 1.1432 0.02500 0.01894 -0.0240 0.0076 1.0000
9.750 1.1559 0.02659 0.02068 -0.0222 0.0073 1.0000
10.000 1.1669 0.02848 0.02274 -0.0203 0.0073 1.0000
10.250 1.1762 0.03049 0.02493 -0.0182 0.0071 1.0000
10.500 1.1832 0.03299 0.02766 -0.0160 0.0072 1.0000
10.750 1.1864 0.03576 0.03069 -0.0138 0.0073 1.0000
11.000 1.1841 0.03900 0.03422 -0.0114 0.0075 1.0000
11.250 1.1761 0.04266 0.03817 -0.0093 0.0077 1.0000
11.500 1.1644 0.04657 0.04234 -0.0077 0.0080 1.0000
11.750 1.1485 0.05110 0.04711 -0.0069 0.0082 1.0000
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Polar data table (+)
Polar graphs
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