EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 500,000 Max Cl/Cd: 113.72 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e817-il-500000.txt Download as CSV file: xf-e817-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 817 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4681 0.13042 0.12814 -0.0386 1.0000 0.0132
-12.250 -0.4724 0.12769 0.12545 -0.0378 1.0000 0.0135
-12.000 -0.4791 0.12495 0.12274 -0.0366 1.0000 0.0136
-8.500 -0.4835 0.03032 0.02621 -0.1181 0.9580 0.0092
-8.250 -0.4661 0.02290 0.01796 -0.1196 0.9565 0.0062
-8.000 -0.4500 0.02135 0.01618 -0.1181 0.9522 0.0058
-7.750 -0.4275 0.02002 0.01469 -0.1180 0.9493 0.0056
-7.500 -0.4014 0.01857 0.01309 -0.1186 0.9475 0.0055
-7.250 -0.3737 0.01718 0.01156 -0.1195 0.9461 0.0054
-7.000 -0.3463 0.01543 0.00961 -0.1207 0.9447 0.0055
-6.750 -0.3167 0.01412 0.00809 -0.1221 0.9436 0.0059
-6.500 -0.2944 0.01325 0.00705 -0.1216 0.9406 0.0069
-6.250 -0.2714 0.01274 0.00642 -0.1211 0.9375 0.0089
-6.000 -0.2444 0.01162 0.00547 -0.1218 0.9355 0.0616
-5.750 -0.2164 0.01045 0.00482 -0.1233 0.9340 0.1736
-5.500 -0.1864 0.00979 0.00457 -0.1247 0.9328 0.2760
-5.250 -0.1552 0.00960 0.00441 -0.1257 0.9318 0.3057
-5.000 -0.1239 0.00947 0.00426 -0.1267 0.9309 0.3240
-4.750 -0.0925 0.00936 0.00413 -0.1276 0.9301 0.3390
-4.500 -0.0693 0.00938 0.00414 -0.1269 0.9274 0.3525
-4.250 -0.0446 0.00937 0.00411 -0.1265 0.9249 0.3683
-4.000 -0.0164 0.00933 0.00407 -0.1268 0.9230 0.3853
-3.750 0.0130 0.00926 0.00401 -0.1274 0.9215 0.3992
-3.500 0.0429 0.00920 0.00394 -0.1280 0.9203 0.4107
-3.250 0.0733 0.00913 0.00388 -0.1287 0.9192 0.4220
-3.000 0.1042 0.00906 0.00379 -0.1295 0.9182 0.4335
-2.750 0.1351 0.00901 0.00374 -0.1303 0.9173 0.4455
-2.500 0.1620 0.00905 0.00379 -0.1303 0.9154 0.4571
-2.250 0.1845 0.00913 0.00391 -0.1295 0.9122 0.4679
-2.000 0.2118 0.00913 0.00395 -0.1295 0.9101 0.4796
-1.750 0.2411 0.00910 0.00395 -0.1300 0.9084 0.4917
-1.500 0.2714 0.00906 0.00394 -0.1306 0.9069 0.5035
-1.250 0.3024 0.00901 0.00392 -0.1314 0.9056 0.5160
-1.000 0.3337 0.00896 0.00391 -0.1322 0.9044 0.5286
-0.750 0.3629 0.00897 0.00397 -0.1326 0.9027 0.5408
-0.500 0.3848 0.00908 0.00414 -0.1315 0.8988 0.5526
-0.250 0.4129 0.00908 0.00418 -0.1317 0.8962 0.5652
0.000 0.4440 0.00899 0.00416 -0.1324 0.8940 0.5780
0.250 0.4766 0.00886 0.00411 -0.1333 0.8920 0.5907
0.500 0.5080 0.00877 0.00409 -0.1340 0.8896 0.6035
0.750 0.5315 0.00877 0.00417 -0.1331 0.8841 0.6158
1.000 0.5633 0.00859 0.00406 -0.1337 0.8802 0.6288
1.250 0.5963 0.00839 0.00392 -0.1345 0.8764 0.6420
1.500 0.6216 0.00825 0.00390 -0.1337 0.8688 0.6549
1.750 0.6528 0.00800 0.00370 -0.1340 0.8619 0.6682
2.000 0.6824 0.00769 0.00343 -0.1338 0.8508 0.6816
2.250 0.7081 0.00749 0.00331 -0.1330 0.8387 0.6948
2.500 0.7338 0.00733 0.00322 -0.1322 0.8254 0.7083
2.750 0.7590 0.00724 0.00323 -0.1314 0.8127 0.7219
3.000 0.7844 0.00716 0.00328 -0.1306 0.7974 0.7359
3.250 0.8063 0.00709 0.00327 -0.1290 0.7636 0.7502
3.500 0.8195 0.00747 0.00320 -0.1254 0.6515 0.7645
3.750 0.8136 0.00898 0.00381 -0.1185 0.4696 0.7795
4.000 0.8121 0.01061 0.00453 -0.1132 0.2804 0.7953
4.250 0.8197 0.01196 0.00519 -0.1098 0.1349 0.8124
4.500 0.8354 0.01276 0.00571 -0.1077 0.0685 0.8316
4.750 0.8490 0.01378 0.00648 -0.1050 0.0149 0.8525
5.000 0.8662 0.01437 0.00721 -0.1026 0.0104 0.8775
5.250 0.8785 0.01495 0.00799 -0.0991 0.0092 0.9139
5.500 0.8920 0.01567 0.00888 -0.0961 0.0088 1.0000
5.750 0.9106 0.01685 0.01021 -0.0944 0.0085 1.0000
6.000 0.9307 0.01855 0.01204 -0.0930 0.0081 1.0000
6.250 0.9559 0.02023 0.01384 -0.0926 0.0073 1.0000
6.500 0.9802 0.02073 0.01440 -0.0921 0.0067 1.0000
6.750 1.0072 0.02236 0.01618 -0.0919 0.0064 1.0000
7.000 1.0344 0.02423 0.01822 -0.0917 0.0061 1.0000
7.250 1.0601 0.02636 0.02058 -0.0911 0.0057 1.0000
7.500 1.0832 0.02957 0.02414 -0.0899 0.0056 1.0000
7.750 1.0984 0.03426 0.02933 -0.0873 0.0060 1.0000
10.000 1.0399 0.07147 0.06908 -0.0517 0.0095 1.0000
10.250 1.0196 0.07586 0.07362 -0.0499 0.0095 1.0000
10.500 0.9974 0.08103 0.07893 -0.0494 0.0096 1.0000
10.750 0.9732 0.08728 0.08533 -0.0505 0.0097 1.0000
11.000 0.9468 0.09535 0.09353 -0.0542 0.0099 1.0000
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Polar data table (+)
Polar graphs
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