EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 500,000 Max Cl/Cd: 60.03 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e836-il-500000.txt Download as CSV file: xf-e836-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E836 HYDROFOIL AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8227 0.04715 0.04377 -0.0430 1.0000 0.0115
-10.500 -0.8441 0.04348 0.03986 -0.0393 1.0000 0.0112
-10.250 -0.8639 0.03988 0.03599 -0.0345 1.0000 0.0107
-10.000 -0.8884 0.03398 0.02947 -0.0281 1.0000 0.0097
-9.750 -0.8882 0.03035 0.02541 -0.0246 1.0000 0.0093
-9.500 -0.8791 0.02797 0.02277 -0.0223 1.0000 0.0093
-9.250 -0.8680 0.02676 0.02145 -0.0202 1.0000 0.0096
-9.000 -0.8598 0.02562 0.02020 -0.0174 1.0000 0.0098
-8.750 -0.8343 0.02427 0.01872 -0.0181 0.9933 0.0104
-8.500 -0.8029 0.02270 0.01698 -0.0197 0.9871 0.0110
-8.250 -0.7710 0.02068 0.01478 -0.0212 0.9819 0.0111
-8.000 -0.7404 0.01911 0.01306 -0.0224 0.9738 0.0115
-7.750 -0.7099 0.01791 0.01174 -0.0236 0.9651 0.0123
-7.500 -0.6804 0.01706 0.01078 -0.0245 0.9555 0.0129
-7.250 -0.6687 0.01528 0.00882 -0.0222 0.9411 0.0145
-7.000 -0.6514 0.01466 0.00812 -0.0206 0.9297 0.0158
-6.750 -0.6330 0.01414 0.00752 -0.0190 0.9201 0.0179
-6.500 -0.6163 0.01349 0.00676 -0.0171 0.9120 0.0220
-6.250 -0.5969 0.01300 0.00622 -0.0157 0.9043 0.0268
-6.000 -0.5782 0.01244 0.00563 -0.0141 0.8978 0.0366
-5.750 -0.5618 0.01167 0.00508 -0.0124 0.8908 0.0783
-5.500 -0.5454 0.01095 0.00463 -0.0107 0.8853 0.1427
-5.250 -0.5284 0.01021 0.00423 -0.0092 0.8790 0.2171
-5.000 -0.5112 0.00952 0.00386 -0.0076 0.8737 0.2974
-4.750 -0.4949 0.00878 0.00351 -0.0059 0.8686 0.3917
-4.500 -0.4790 0.00806 0.00320 -0.0040 0.8630 0.4934
-4.250 -0.4594 0.00765 0.00305 -0.0025 0.8587 0.5698
-4.000 -0.4361 0.00748 0.00300 -0.0016 0.8543 0.6200
-3.750 -0.4113 0.00740 0.00298 -0.0010 0.8498 0.6535
-3.500 -0.3850 0.00740 0.00293 -0.0007 0.8458 0.6734
-3.250 -0.3585 0.00742 0.00292 -0.0004 0.8422 0.6900
-3.000 -0.3316 0.00743 0.00291 -0.0002 0.8378 0.7035
-2.750 -0.3044 0.00745 0.00289 -0.0001 0.8337 0.7138
-2.500 -0.2769 0.00748 0.00289 0.0000 0.8303 0.7230
-2.250 -0.2497 0.00752 0.00289 0.0001 0.8263 0.7327
-2.000 -0.2221 0.00755 0.00290 0.0001 0.8221 0.7405
-1.750 -0.1944 0.00757 0.00288 0.0001 0.8183 0.7474
-1.500 -0.1666 0.00762 0.00290 0.0002 0.8150 0.7546
-1.250 -0.1391 0.00763 0.00291 0.0002 0.8105 0.7613
-1.000 -0.1113 0.00766 0.00294 0.0001 0.8063 0.7676
-0.750 -0.0836 0.00768 0.00292 0.0001 0.8027 0.7738
-0.500 -0.0556 0.00770 0.00296 0.0001 0.7987 0.7788
-0.250 -0.0280 0.00772 0.00298 0.0000 0.7939 0.7848
0.000 0.0000 0.00771 0.00296 0.0000 0.7896 0.7896
0.250 0.0279 0.00772 0.00298 0.0000 0.7848 0.7939
0.500 0.0555 0.00770 0.00296 -0.0001 0.7788 0.7987
0.750 0.0835 0.00768 0.00292 -0.0001 0.7738 0.8027
1.000 0.1112 0.00766 0.00294 -0.0001 0.7675 0.8063
1.250 0.1390 0.00763 0.00291 -0.0001 0.7614 0.8105
1.500 0.1666 0.00762 0.00290 -0.0002 0.7546 0.8150
1.750 0.1943 0.00756 0.00288 -0.0001 0.7474 0.8183
2.000 0.2220 0.00755 0.00290 -0.0001 0.7405 0.8220
2.250 0.2496 0.00752 0.00288 -0.0001 0.7326 0.8263
2.500 0.2768 0.00748 0.00289 0.0000 0.7230 0.8303
2.750 0.3042 0.00745 0.00289 0.0001 0.7138 0.8337
3.000 0.3315 0.00743 0.00291 0.0002 0.7034 0.8378
3.250 0.3584 0.00742 0.00293 0.0004 0.6901 0.8422
3.500 0.3849 0.00740 0.00293 0.0007 0.6734 0.8458
3.750 0.4112 0.00740 0.00298 0.0010 0.6539 0.8497
4.000 0.4360 0.00748 0.00300 0.0017 0.6203 0.8543
4.250 0.4592 0.00765 0.00305 0.0025 0.5699 0.8587
4.500 0.4787 0.00806 0.00320 0.0041 0.4924 0.8631
4.750 0.4950 0.00875 0.00350 0.0059 0.3949 0.8686
5.000 0.5110 0.00951 0.00386 0.0077 0.2984 0.8737
5.250 0.5282 0.01020 0.00423 0.0092 0.2186 0.8790
5.500 0.5452 0.01093 0.00462 0.0107 0.1441 0.8853
5.750 0.5612 0.01168 0.00508 0.0125 0.0777 0.8909
6.000 0.5777 0.01243 0.00563 0.0142 0.0366 0.8979
6.250 0.5964 0.01299 0.00621 0.0158 0.0267 0.9043
6.500 0.6156 0.01350 0.00677 0.0172 0.0218 0.9122
6.750 0.6313 0.01422 0.00761 0.0193 0.0184 0.9204
7.000 0.6508 0.01464 0.00810 0.0207 0.0157 0.9298
7.250 0.6679 0.01528 0.00883 0.0224 0.0145 0.9414
7.500 0.6798 0.01707 0.01078 0.0247 0.0128 0.9558
7.750 0.7098 0.01784 0.01167 0.0237 0.0121 0.9652
8.000 0.7400 0.01913 0.01309 0.0225 0.0116 0.9739
8.250 0.7707 0.02068 0.01478 0.0212 0.0112 0.9820
8.500 0.8026 0.02267 0.01695 0.0198 0.0110 0.9872
8.750 0.8337 0.02444 0.01891 0.0183 0.0105 0.9933
9.000 0.8604 0.02592 0.02053 0.0173 0.0099 1.0000
9.250 0.8672 0.02608 0.02069 0.0202 0.0094 1.0000
9.500 0.8785 0.02801 0.02281 0.0224 0.0093 1.0000
9.750 0.8881 0.02989 0.02488 0.0246 0.0091 1.0000
10.000 0.8950 0.03190 0.02709 0.0270 0.0090 1.0000
10.250 0.8922 0.03527 0.03086 0.0308 0.0093 1.0000
10.500 0.8425 0.04359 0.03999 0.0395 0.0111 1.0000
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Polar data table (+)
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