EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 500,000 Max Cl/Cd: 70.62 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e837-il-500000.txt Download as CSV file: xf-e837-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E837 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8092 0.13571 0.13317 -0.0018 1.0000 0.0100
-17.500 -0.8439 0.12247 0.11975 -0.0097 1.0000 0.0097
-17.250 -0.8741 0.11135 0.10842 -0.0162 1.0000 0.0094
-17.000 -0.8945 0.10284 0.09974 -0.0212 1.0000 0.0094
-16.750 -0.9084 0.09604 0.09280 -0.0252 1.0000 0.0095
-16.500 -0.9319 0.08792 0.08446 -0.0293 1.0000 0.0094
-16.250 -0.9452 0.08199 0.07837 -0.0323 1.0000 0.0094
-16.000 -0.9610 0.07594 0.07212 -0.0348 1.0000 0.0094
-15.750 -0.9721 0.07093 0.06693 -0.0367 1.0000 0.0094
-15.500 -0.9801 0.06657 0.06241 -0.0382 1.0000 0.0096
-15.250 -0.9863 0.06260 0.05828 -0.0393 1.0000 0.0096
-15.000 -0.9913 0.05894 0.05446 -0.0400 1.0000 0.0096
-14.750 -0.9952 0.05551 0.05086 -0.0404 1.0000 0.0098
-14.500 -0.9968 0.05245 0.04764 -0.0405 1.0000 0.0098
-14.250 -0.9955 0.04980 0.04485 -0.0405 1.0000 0.0098
-14.000 -0.9936 0.04729 0.04219 -0.0403 1.0000 0.0101
-13.750 -0.9901 0.04499 0.03975 -0.0399 1.0000 0.0103
-13.500 -0.9852 0.04305 0.03768 -0.0397 1.0000 0.0105
-13.250 -0.9782 0.04112 0.03565 -0.0390 1.0000 0.0105
-13.000 -0.9748 0.03878 0.03319 -0.0379 1.0000 0.0110
-12.750 -0.9692 0.03690 0.03122 -0.0370 1.0000 0.0111
-12.500 -0.9637 0.03510 0.02939 -0.0361 1.0000 0.0115
-12.250 -0.9567 0.03348 0.02771 -0.0353 1.0000 0.0117
-12.000 -0.9487 0.03198 0.02617 -0.0345 1.0000 0.0121
-11.750 -0.9404 0.03054 0.02467 -0.0337 1.0000 0.0124
-11.500 -0.9321 0.02914 0.02321 -0.0327 1.0000 0.0130
-11.250 -0.9228 0.02783 0.02183 -0.0317 1.0000 0.0135
-11.000 -0.9107 0.02678 0.02071 -0.0309 1.0000 0.0141
-10.750 -0.9038 0.02536 0.01924 -0.0296 1.0000 0.0144
-10.500 -0.9053 0.02344 0.01727 -0.0275 1.0000 0.0155
-10.250 -0.8959 0.02233 0.01614 -0.0263 1.0000 0.0163
-10.000 -0.8856 0.02132 0.01510 -0.0249 1.0000 0.0176
-9.750 -0.8741 0.02043 0.01416 -0.0236 1.0000 0.0186
-9.500 -0.8653 0.01904 0.01272 -0.0226 0.9749 0.0201
-9.250 -0.8292 0.01787 0.01144 -0.0263 0.9255 0.0236
-9.000 -0.8198 0.01717 0.01056 -0.0240 0.8897 0.0260
-8.750 -0.8135 0.01651 0.00980 -0.0209 0.8686 0.0299
-8.500 -0.8062 0.01589 0.00911 -0.0178 0.8532 0.0358
-8.250 -0.7996 0.01528 0.00850 -0.0145 0.8406 0.0467
-8.000 -0.7901 0.01457 0.00786 -0.0118 0.8305 0.0681
-7.750 -0.7788 0.01386 0.00727 -0.0095 0.8218 0.0983
-7.500 -0.7652 0.01316 0.00673 -0.0076 0.8132 0.1328
-7.250 -0.7511 0.01248 0.00621 -0.0057 0.8062 0.1739
-7.000 -0.7357 0.01176 0.00570 -0.0041 0.7989 0.2205
-6.750 -0.7196 0.01109 0.00521 -0.0025 0.7927 0.2720
-6.500 -0.7029 0.01039 0.00476 -0.0010 0.7864 0.3277
-6.250 -0.6847 0.00980 0.00438 0.0004 0.7805 0.3826
-6.000 -0.6638 0.00940 0.00412 0.0013 0.7755 0.4291
-5.750 -0.6407 0.00911 0.00393 0.0020 0.7699 0.4683
-5.500 -0.6165 0.00894 0.00381 0.0026 0.7647 0.4999
-5.250 -0.5905 0.00887 0.00370 0.0028 0.7602 0.5205
-5.000 -0.5636 0.00880 0.00361 0.0029 0.7552 0.5359
-4.750 -0.5368 0.00876 0.00353 0.0030 0.7504 0.5500
-4.250 -0.4820 0.00871 0.00341 0.0031 0.7415 0.5710
-4.000 -0.4542 0.00871 0.00334 0.0030 0.7370 0.5806
-3.750 -0.4265 0.00870 0.00330 0.0030 0.7329 0.5886
-3.500 -0.3985 0.00872 0.00325 0.0029 0.7287 0.5969
-3.250 -0.3703 0.00869 0.00323 0.0027 0.7241 0.6034
-3.000 -0.3422 0.00871 0.00316 0.0026 0.7200 0.6104
-2.750 -0.3139 0.00871 0.00314 0.0025 0.7163 0.6161
-2.500 -0.2856 0.00872 0.00312 0.0023 0.7119 0.6228
-2.250 -0.2572 0.00870 0.00309 0.0021 0.7076 0.6285
-2.000 -0.2287 0.00871 0.00307 0.0019 0.7037 0.6338
-1.750 -0.2004 0.00875 0.00304 0.0017 0.7000 0.6395
-1.500 -0.1718 0.00871 0.00303 0.0015 0.6956 0.6442
-1.250 -0.1432 0.00871 0.00303 0.0012 0.6915 0.6490
-1.000 -0.1146 0.00874 0.00299 0.0010 0.6877 0.6542
-0.750 -0.0860 0.00873 0.00298 0.0008 0.6838 0.6585
-0.500 -0.0573 0.00871 0.00300 0.0005 0.6794 0.6626
-0.250 -0.0287 0.00872 0.00298 0.0003 0.6752 0.6672
0.000 0.0000 0.00874 0.00295 0.0000 0.6715 0.6715
0.250 0.0286 0.00872 0.00298 -0.0003 0.6672 0.6752
0.500 0.0573 0.00871 0.00300 -0.0005 0.6626 0.6794
0.750 0.0860 0.00873 0.00298 -0.0008 0.6585 0.6838
1.000 0.1146 0.00873 0.00299 -0.0010 0.6542 0.6877
1.250 0.1431 0.00871 0.00303 -0.0012 0.6490 0.6914
1.500 0.1717 0.00871 0.00303 -0.0015 0.6441 0.6956
1.750 0.2003 0.00875 0.00304 -0.0017 0.6395 0.7000
2.000 0.2287 0.00871 0.00307 -0.0019 0.6338 0.7038
2.250 0.2572 0.00870 0.00309 -0.0021 0.6285 0.7076
2.500 0.2856 0.00872 0.00312 -0.0023 0.6228 0.7119
2.750 0.3139 0.00871 0.00314 -0.0025 0.6161 0.7163
3.000 0.3422 0.00871 0.00316 -0.0026 0.6104 0.7200
3.250 0.3703 0.00869 0.00323 -0.0027 0.6034 0.7241
3.500 0.3985 0.00872 0.00325 -0.0029 0.5969 0.7287
3.750 0.4264 0.00870 0.00330 -0.0030 0.5887 0.7329
4.000 0.4542 0.00871 0.00334 -0.0030 0.5806 0.7370
4.250 0.4819 0.00871 0.00341 -0.0030 0.5711 0.7415
4.750 0.5367 0.00876 0.00353 -0.0030 0.5501 0.7504
5.000 0.5636 0.00880 0.00361 -0.0029 0.5359 0.7551
5.250 0.5904 0.00887 0.00370 -0.0028 0.5208 0.7602
5.500 0.6164 0.00894 0.00380 -0.0025 0.4996 0.7648
5.750 0.6407 0.00911 0.00393 -0.0020 0.4683 0.7699
6.000 0.6638 0.00940 0.00412 -0.0013 0.4293 0.7755
6.250 0.6846 0.00980 0.00438 -0.0003 0.3825 0.7805
6.500 0.7027 0.01040 0.00476 0.0010 0.3269 0.7865
6.750 0.7196 0.01109 0.00521 0.0025 0.2721 0.7927
7.000 0.7355 0.01176 0.00570 0.0041 0.2201 0.7989
7.250 0.7512 0.01247 0.00620 0.0057 0.1744 0.8061
7.500 0.7651 0.01316 0.00673 0.0076 0.1325 0.8132
7.750 0.7786 0.01387 0.00728 0.0095 0.0976 0.8217
8.000 0.7901 0.01457 0.00786 0.0118 0.0681 0.8304
8.250 0.7992 0.01530 0.00851 0.0146 0.0460 0.8407
8.500 0.8062 0.01589 0.00910 0.0178 0.0357 0.8533
8.750 0.8137 0.01650 0.00979 0.0208 0.0300 0.8687
9.000 0.8201 0.01715 0.01054 0.0239 0.0261 0.8897
9.250 0.8294 0.01786 0.01144 0.0263 0.0235 0.9256
9.500 0.8658 0.01901 0.01269 0.0225 0.0201 0.9747
9.750 0.8751 0.02039 0.01412 0.0235 0.0186 1.0000
10.000 0.8860 0.02131 0.01509 0.0249 0.0176 1.0000
10.250 0.8970 0.02227 0.01608 0.0261 0.0164 1.0000
10.500 0.9053 0.02346 0.01729 0.0275 0.0156 1.0000
10.750 0.9052 0.02528 0.01916 0.0294 0.0144 1.0000
11.000 0.9146 0.02650 0.02044 0.0305 0.0139 1.0000
11.250 0.9244 0.02773 0.02174 0.0316 0.0134 1.0000
11.500 0.9328 0.02911 0.02318 0.0326 0.0130 1.0000
11.750 0.9411 0.03053 0.02466 0.0336 0.0125 1.0000
12.000 0.9500 0.03191 0.02609 0.0344 0.0120 1.0000
12.250 0.9573 0.03348 0.02770 0.0352 0.0117 1.0000
12.500 0.9643 0.03510 0.02937 0.0361 0.0115 1.0000
12.750 0.9689 0.03699 0.03131 0.0369 0.0110 1.0000
13.000 0.9749 0.03887 0.03328 0.0379 0.0109 1.0000
13.250 0.9796 0.04112 0.03564 0.0390 0.0106 1.0000
13.500 0.9861 0.04297 0.03761 0.0394 0.0105 1.0000
13.750 0.9911 0.04499 0.03976 0.0398 0.0102 1.0000
14.000 0.9950 0.04730 0.04220 0.0403 0.0102 1.0000
14.250 0.9965 0.04976 0.04481 0.0403 0.0098 1.0000
14.500 0.9980 0.05242 0.04761 0.0405 0.0099 1.0000
14.750 0.9964 0.05551 0.05086 0.0404 0.0099 1.0000
15.000 0.9928 0.05887 0.05439 0.0399 0.0097 1.0000
15.250 0.9871 0.06262 0.05830 0.0392 0.0096 1.0000
15.500 0.9809 0.06658 0.06243 0.0381 0.0096 1.0000
15.750 0.9690 0.07154 0.06758 0.0365 0.0095 1.0000
16.000 0.9592 0.07638 0.07259 0.0346 0.0094 1.0000
16.250 0.9468 0.08189 0.07826 0.0321 0.0094 1.0000
16.500 0.9367 0.08728 0.08379 0.0294 0.0092 1.0000
16.750 0.9176 0.09454 0.09124 0.0256 0.0093 1.0000
17.000 0.8929 0.10335 0.10027 0.0208 0.0096 1.0000
17.250 0.8763 0.11113 0.10820 0.0162 0.0093 1.0000
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