EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 100,000 Max Cl/Cd: 26.37 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e473-il-100000.txt Download as CSV file: xf-e473-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 473 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5471 0.09832 0.09187 -0.0028 1.0000 0.2680
-10.000 -0.5329 0.09545 0.08897 -0.0025 1.0000 0.2694
-9.750 -0.9708 0.04412 0.03699 -0.0132 1.0000 0.2499
-9.500 -0.9149 0.04588 0.03905 -0.0145 1.0000 0.2537
-9.250 -0.8860 0.04615 0.03938 -0.0136 1.0000 0.2582
-9.000 -0.9128 0.04215 0.03502 -0.0092 1.0000 0.2638
-8.750 -0.9152 0.03972 0.03237 -0.0062 1.0000 0.2685
-8.500 -0.8815 0.04010 0.03291 -0.0060 1.0000 0.2725
-8.250 -0.8718 0.03878 0.03147 -0.0038 1.0000 0.2778
-8.000 -0.8830 0.03591 0.02814 0.0003 1.0000 0.2838
-7.750 -0.8545 0.03561 0.02802 0.0007 1.0000 0.2874
-7.500 -0.8334 0.03509 0.02751 0.0020 1.0000 0.2921
-7.250 -0.8279 0.03343 0.02557 0.0047 1.0000 0.2981
-7.000 -0.8149 0.03210 0.02412 0.0067 1.0000 0.3027
-6.750 -0.7915 0.03165 0.02376 0.0077 1.0000 0.3067
-6.500 -0.7752 0.03079 0.02281 0.0095 1.0000 0.3120
-6.250 -0.7678 0.02938 0.02105 0.0122 1.0000 0.3179
-6.000 -0.7449 0.02869 0.02050 0.0132 1.0000 0.3217
-5.750 -0.7245 0.02813 0.01996 0.0145 1.0000 0.3262
-5.500 -0.7095 0.02726 0.01894 0.0164 1.0000 0.3319
-5.250 -0.6942 0.02633 0.01788 0.0183 1.0000 0.3367
-5.000 -0.6736 0.02577 0.01740 0.0195 1.0000 0.3408
-4.750 -0.6552 0.02520 0.01682 0.0211 1.0000 0.3455
-4.500 -0.6405 0.02453 0.01597 0.0230 1.0000 0.3512
-4.250 -0.6228 0.02391 0.01540 0.0245 1.0000 0.3555
-4.000 -0.6051 0.02351 0.01505 0.0260 1.0000 0.3599
-3.750 -0.5898 0.02309 0.01461 0.0277 1.0000 0.3647
-3.500 -0.5570 0.02267 0.01406 0.0259 0.9935 0.3712
-3.250 -0.4939 0.02223 0.01377 0.0190 0.9745 0.3789
-3.000 -0.4360 0.02158 0.01297 0.0132 0.9514 0.3876
-2.750 -0.3788 0.02081 0.01240 0.0082 0.9253 0.3951
-2.500 -0.3217 0.02008 0.01156 0.0033 0.8908 0.4047
-2.250 -0.2600 0.01932 0.01085 -0.0022 0.8348 0.4128
-2.000 -0.2133 0.01905 0.01018 -0.0048 0.7561 0.4224
-1.750 -0.1811 0.01897 0.00985 -0.0048 0.6880 0.4295
-1.500 -0.1548 0.01901 0.00956 -0.0040 0.6386 0.4375
-1.250 -0.1293 0.01898 0.00932 -0.0032 0.6005 0.4450
-1.000 -0.1038 0.01900 0.00919 -0.0024 0.5706 0.4538
-0.750 -0.0779 0.01900 0.00904 -0.0018 0.5483 0.4632
-0.500 -0.0522 0.01901 0.00897 -0.0011 0.5287 0.4739
-0.250 -0.0258 0.01899 0.00890 -0.0006 0.5122 0.4842
0.000 0.0000 0.01897 0.00886 0.0000 0.4971 0.4972
0.250 0.0258 0.01899 0.00890 0.0006 0.4842 0.5121
0.500 0.0522 0.01901 0.00897 0.0011 0.4739 0.5286
0.750 0.0779 0.01900 0.00904 0.0018 0.4633 0.5483
1.000 0.1038 0.01900 0.00919 0.0024 0.4539 0.5706
1.250 0.1293 0.01898 0.00932 0.0032 0.4449 0.6004
1.500 0.1548 0.01901 0.00956 0.0040 0.4375 0.6384
1.750 0.1811 0.01897 0.00986 0.0048 0.4295 0.6880
2.000 0.2133 0.01905 0.01018 0.0048 0.4225 0.7560
2.250 0.2600 0.01932 0.01085 0.0022 0.4128 0.8347
2.500 0.3218 0.02008 0.01156 -0.0033 0.4047 0.8908
2.750 0.3787 0.02080 0.01239 -0.0081 0.3950 0.9253
3.000 0.4360 0.02158 0.01297 -0.0132 0.3876 0.9515
3.250 0.4941 0.02223 0.01377 -0.0191 0.3789 0.9747
3.500 0.5570 0.02266 0.01406 -0.0259 0.3712 0.9936
3.750 0.5897 0.02309 0.01461 -0.0277 0.3647 1.0000
4.000 0.6050 0.02351 0.01505 -0.0260 0.3599 1.0000
4.250 0.6227 0.02391 0.01539 -0.0245 0.3555 1.0000
4.500 0.6404 0.02453 0.01597 -0.0230 0.3512 1.0000
4.750 0.6551 0.02520 0.01683 -0.0210 0.3456 1.0000
5.000 0.6735 0.02577 0.01740 -0.0195 0.3408 1.0000
5.250 0.6941 0.02632 0.01787 -0.0182 0.3367 1.0000
5.500 0.7094 0.02726 0.01894 -0.0164 0.3318 1.0000
5.750 0.7245 0.02812 0.01995 -0.0145 0.3262 1.0000
6.000 0.7449 0.02869 0.02050 -0.0132 0.3217 1.0000
6.250 0.7677 0.02938 0.02105 -0.0122 0.3179 1.0000
6.500 0.7751 0.03079 0.02282 -0.0095 0.3121 1.0000
6.750 0.7914 0.03165 0.02376 -0.0077 0.3067 1.0000
7.000 0.8149 0.03209 0.02411 -0.0067 0.3026 1.0000
7.250 0.8277 0.03343 0.02558 -0.0047 0.2980 1.0000
7.500 0.8334 0.03509 0.02751 -0.0020 0.2921 1.0000
7.750 0.8544 0.03562 0.02802 -0.0007 0.2875 1.0000
8.000 0.8830 0.03591 0.02814 -0.0003 0.2838 1.0000
8.250 0.8718 0.03879 0.03148 0.0038 0.2778 1.0000
8.500 0.8814 0.04011 0.03292 0.0060 0.2725 1.0000
8.750 0.9151 0.03972 0.03237 0.0062 0.2685 1.0000
9.000 0.9129 0.04215 0.03502 0.0092 0.2639 1.0000
9.250 0.8857 0.04620 0.03943 0.0136 0.2582 1.0000
9.500 0.9149 0.04589 0.03906 0.0145 0.2537 1.0000
9.750 0.9708 0.04413 0.03700 0.0132 0.2499 1.0000
10.000 0.5452 0.09208 0.08557 0.0043 0.2553 1.0000
10.250 0.5530 0.09504 0.08854 0.0042 0.2531 1.0000
10.500 0.5571 0.09875 0.09227 0.0037 0.2521 1.0000
10.750 0.5652 0.10231 0.09586 0.0035 0.2512 1.0000
11.000 0.5791 0.10574 0.09932 0.0037 0.2504 1.0000
11.250 0.5182 0.11709 0.11067 -0.0038 0.2687 1.0000
11.500 0.5525 0.12088 0.11452 -0.0025 0.2662 1.0000
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