EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.08 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e836-il-1000000.txt Download as CSV file: xf-e836-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7576 0.08894 0.08721 -0.0264 1.0000 0.0046
-13.750 -0.7811 0.07843 0.07657 -0.0336 1.0000 0.0044
-13.500 -0.8115 0.06851 0.06647 -0.0400 1.0000 0.0043
-13.250 -0.8353 0.06143 0.05923 -0.0437 1.0000 0.0043
-13.000 -0.8599 0.05523 0.05284 -0.0459 1.0000 0.0043
-12.750 -0.8935 0.04861 0.04598 -0.0467 1.0000 0.0042
-12.500 -0.9173 0.04373 0.04086 -0.0460 1.0000 0.0041
-12.250 -0.9259 0.04091 0.03788 -0.0449 1.0000 0.0043
-12.000 -0.9388 0.03767 0.03443 -0.0430 1.0000 0.0043
-11.750 -0.9595 0.03348 0.02990 -0.0397 1.0000 0.0042
-11.500 -0.9580 0.03189 0.02817 -0.0377 1.0000 0.0044
-11.250 -0.9539 0.03060 0.02676 -0.0357 1.0000 0.0046
-11.000 -0.9560 0.02826 0.02418 -0.0327 1.0000 0.0046
-10.750 -0.9513 0.02670 0.02246 -0.0302 1.0000 0.0047
-10.500 -0.9424 0.02580 0.02146 -0.0279 1.0000 0.0050
-10.250 -0.9342 0.02463 0.02015 -0.0254 1.0000 0.0051
-10.000 -0.9248 0.02361 0.01901 -0.0229 1.0000 0.0052
-9.750 -0.9143 0.02256 0.01785 -0.0204 1.0000 0.0052
-9.500 -0.8984 0.02147 0.01664 -0.0190 0.9969 0.0053
-9.250 -0.8691 0.01944 0.01441 -0.0208 0.9788 0.0054
-9.000 -0.8417 0.01736 0.01214 -0.0221 0.9590 0.0056
-8.750 -0.8249 0.01608 0.01066 -0.0209 0.9327 0.0059
-8.500 -0.8094 0.01548 0.00993 -0.0189 0.9151 0.0062
-8.250 -0.7923 0.01493 0.00929 -0.0173 0.9028 0.0064
-8.000 -0.7728 0.01451 0.00880 -0.0161 0.8935 0.0068
-7.750 -0.7541 0.01401 0.00820 -0.0146 0.8852 0.0073
-7.500 -0.7346 0.01347 0.00758 -0.0133 0.8778 0.0078
-7.000 -0.6958 0.01233 0.00623 -0.0107 0.8651 0.0092
-6.750 -0.6748 0.01188 0.00572 -0.0096 0.8596 0.0106
-6.500 -0.6513 0.01158 0.00539 -0.0090 0.8547 0.0123
-6.250 -0.6297 0.01109 0.00484 -0.0080 0.8495 0.0157
-6.000 -0.6062 0.01080 0.00450 -0.0074 0.8449 0.0188
-5.750 -0.5831 0.01043 0.00414 -0.0067 0.8405 0.0261
-5.500 -0.5609 0.00997 0.00378 -0.0059 0.8360 0.0482
-5.250 -0.5395 0.00949 0.00345 -0.0050 0.8316 0.0850
-5.000 -0.5181 0.00898 0.00314 -0.0042 0.8275 0.1327
-4.750 -0.4972 0.00841 0.00284 -0.0033 0.8233 0.1961
-4.500 -0.4759 0.00787 0.00256 -0.0024 0.8192 0.2618
-4.250 -0.4546 0.00736 0.00230 -0.0015 0.8153 0.3319
-4.000 -0.4342 0.00673 0.00202 -0.0005 0.8114 0.4231
-3.750 -0.4134 0.00616 0.00179 0.0005 0.8074 0.5113
-3.500 -0.3895 0.00586 0.00166 0.0011 0.8037 0.5690
-3.250 -0.3643 0.00568 0.00159 0.0015 0.8002 0.6114
-3.000 -0.3376 0.00557 0.00154 0.0017 0.7966 0.6387
-2.750 -0.3102 0.00551 0.00149 0.0017 0.7929 0.6587
-2.500 -0.2825 0.00548 0.00145 0.0016 0.7894 0.6724
-2.250 -0.2546 0.00546 0.00142 0.0015 0.7860 0.6827
-2.000 -0.2264 0.00543 0.00139 0.0014 0.7822 0.6923
-1.750 -0.1981 0.00543 0.00137 0.0012 0.7785 0.7022
-1.500 -0.1701 0.00541 0.00136 0.0011 0.7749 0.7101
-1.250 -0.1416 0.00543 0.00133 0.0009 0.7713 0.7171
-1.000 -0.1133 0.00541 0.00133 0.0007 0.7673 0.7236
-0.750 -0.0848 0.00542 0.00132 0.0005 0.7631 0.7306
-0.250 -0.0283 0.00542 0.00132 0.0002 0.7533 0.7427
0.000 0.0000 0.00540 0.00131 0.0000 0.7479 0.7479
0.250 0.0282 0.00542 0.00132 -0.0001 0.7427 0.7533
0.750 0.0847 0.00542 0.00132 -0.0005 0.7306 0.7631
1.000 0.1132 0.00541 0.00133 -0.0007 0.7236 0.7672
1.250 0.1415 0.00543 0.00133 -0.0008 0.7171 0.7713
1.500 0.1700 0.00541 0.00136 -0.0011 0.7101 0.7749
1.750 0.1980 0.00543 0.00137 -0.0012 0.7023 0.7785
2.000 0.2263 0.00543 0.00139 -0.0013 0.6923 0.7822
2.250 0.2545 0.00546 0.00142 -0.0015 0.6827 0.7860
2.500 0.2824 0.00548 0.00145 -0.0016 0.6724 0.7894
2.750 0.3101 0.00551 0.00149 -0.0016 0.6586 0.7929
3.000 0.3374 0.00557 0.00154 -0.0016 0.6387 0.7966
3.250 0.3641 0.00568 0.00159 -0.0015 0.6114 0.8002
3.500 0.3894 0.00586 0.00166 -0.0011 0.5688 0.8037
3.750 0.4132 0.00616 0.00179 -0.0005 0.5114 0.8074
4.000 0.4341 0.00672 0.00202 0.0005 0.4239 0.8114
4.250 0.4543 0.00737 0.00230 0.0016 0.3306 0.8153
4.500 0.4756 0.00787 0.00256 0.0025 0.2606 0.8192
4.750 0.4968 0.00842 0.00284 0.0034 0.1944 0.8233
5.000 0.5174 0.00901 0.00315 0.0043 0.1299 0.8276
5.250 0.5391 0.00949 0.00345 0.0051 0.0850 0.8317
5.500 0.5606 0.00996 0.00378 0.0060 0.0487 0.8360
5.750 0.5827 0.01043 0.00414 0.0068 0.0259 0.8405
6.000 0.6058 0.01080 0.00451 0.0075 0.0188 0.8449
6.250 0.6291 0.01110 0.00484 0.0081 0.0155 0.8495
6.500 0.6509 0.01157 0.00538 0.0091 0.0123 0.8547
6.750 0.6740 0.01190 0.00575 0.0098 0.0108 0.8596
7.000 0.6947 0.01238 0.00628 0.0109 0.0090 0.8652
7.500 0.7342 0.01345 0.00757 0.0134 0.0077 0.8779
7.750 0.7537 0.01399 0.00818 0.0147 0.0072 0.8854
8.000 0.7723 0.01450 0.00879 0.0162 0.0069 0.8936
8.250 0.7919 0.01491 0.00927 0.0174 0.0065 0.9030
8.500 0.8089 0.01546 0.00992 0.0191 0.0062 0.9154
8.750 0.8243 0.01607 0.01064 0.0210 0.0059 0.9333
9.000 0.8411 0.01742 0.01220 0.0223 0.0056 0.9596
9.250 0.8693 0.01937 0.01434 0.0207 0.0054 0.9793
9.500 0.8984 0.02143 0.01660 0.0191 0.0053 0.9974
9.750 0.9147 0.02220 0.01746 0.0205 0.0052 1.0000
10.000 0.9257 0.02298 0.01834 0.0229 0.0051 1.0000
10.250 0.9345 0.02432 0.01981 0.0254 0.0050 1.0000
10.500 0.9430 0.02551 0.02115 0.0279 0.0049 1.0000
10.750 0.9448 0.02778 0.02364 0.0309 0.0050 1.0000
11.000 0.9519 0.02881 0.02479 0.0332 0.0048 1.0000
11.250 0.9604 0.02956 0.02562 0.0351 0.0044 1.0000
11.500 0.9565 0.03202 0.02831 0.0379 0.0044 1.0000
11.750 0.9442 0.03528 0.03185 0.0410 0.0045 1.0000
12.000 0.9419 0.03725 0.03399 0.0429 0.0043 1.0000
12.250 0.9258 0.04089 0.03786 0.0450 0.0044 1.0000
12.500 0.9109 0.04448 0.04166 0.0463 0.0043 1.0000
12.750 0.8923 0.04872 0.04610 0.0468 0.0042 1.0000
13.000 0.8561 0.05572 0.05336 0.0459 0.0044 1.0000
13.250 0.8357 0.06133 0.05912 0.0438 0.0044 1.0000
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Polar data table (+)
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