EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 50,000 Max Cl/Cd: 21.87 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e472-il-50000-n5.txt Download as CSV file: xf-e472-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 472 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6555 0.10121 0.09234 -0.0046 1.0000 0.1432
-10.750 -0.6741 0.09436 0.08551 -0.0083 1.0000 0.1465
-10.500 -0.7699 0.07428 0.06551 -0.0231 1.0000 0.1502
-10.250 -0.7221 0.07864 0.06986 -0.0173 1.0000 0.1525
-10.000 -0.7516 0.07083 0.06204 -0.0217 1.0000 0.1551
-9.750 -0.8036 0.06313 0.05428 -0.0228 1.0000 0.1569
-9.500 -0.8373 0.05742 0.04835 -0.0218 1.0000 0.1596
-9.250 -0.8674 0.05188 0.04238 -0.0199 1.0000 0.1631
-9.000 -0.8641 0.04940 0.03974 -0.0182 1.0000 0.1664
-8.750 -0.8475 0.04828 0.03859 -0.0169 1.0000 0.1697
-8.500 -0.8395 0.04619 0.03631 -0.0152 1.0000 0.1734
-8.250 -0.8384 0.04333 0.03305 -0.0132 1.0000 0.1780
-8.000 -0.8261 0.04159 0.03114 -0.0116 1.0000 0.1820
-7.750 -0.8077 0.04055 0.03007 -0.0103 1.0000 0.1859
-7.500 -0.7937 0.03894 0.02826 -0.0087 1.0000 0.1903
-7.250 -0.7841 0.03685 0.02569 -0.0068 1.0000 0.1957
-7.000 -0.7625 0.03602 0.02497 -0.0057 1.0000 0.1996
-6.750 -0.7437 0.03498 0.02385 -0.0043 1.0000 0.2043
-6.500 -0.7272 0.03355 0.02212 -0.0028 1.0000 0.2097
-6.250 -0.7079 0.03242 0.02089 -0.0015 1.0000 0.2143
-6.000 -0.6868 0.03160 0.02009 -0.0003 1.0000 0.2192
-5.750 -0.6675 0.03056 0.01885 0.0010 1.0000 0.2253
-5.500 -0.6468 0.02957 0.01774 0.0022 1.0000 0.2304
-5.250 -0.6249 0.02882 0.01702 0.0033 1.0000 0.2356
-5.000 -0.6039 0.02798 0.01603 0.0045 1.0000 0.2423
-4.750 -0.5819 0.02721 0.01523 0.0056 1.0000 0.2480
-4.500 -0.5595 0.02652 0.01456 0.0067 1.0000 0.2539
-4.250 -0.5375 0.02579 0.01365 0.0078 1.0000 0.2612
-4.000 -0.5146 0.02519 0.01318 0.0088 1.0000 0.2674
-3.750 -0.4919 0.02459 0.01253 0.0098 1.0000 0.2752
-3.500 -0.4687 0.02400 0.01199 0.0108 1.0000 0.2821
-3.250 -0.4455 0.02347 0.01149 0.0117 1.0000 0.2903
-3.000 -0.4221 0.02297 0.01104 0.0127 1.0000 0.2991
-2.750 -0.3985 0.02251 0.01062 0.0135 1.0000 0.3089
-2.500 -0.3746 0.02206 0.01027 0.0143 1.0000 0.3184
-2.250 -0.3504 0.02166 0.00992 0.0151 1.0000 0.3301
-2.000 -0.3264 0.02127 0.00966 0.0158 1.0000 0.3430
-1.750 -0.3032 0.02090 0.00944 0.0166 1.0000 0.3570
-1.500 -0.2812 0.02056 0.00927 0.0177 1.0000 0.3727
-1.250 -0.2599 0.02024 0.00915 0.0188 1.0000 0.3917
-1.000 -0.2339 0.01994 0.00909 0.0189 0.9964 0.4163
-0.750 -0.1790 0.01941 0.00899 0.0136 0.9607 0.4605
-0.500 -0.1349 0.01876 0.00881 0.0110 0.9153 0.5185
-0.250 -0.0824 0.01803 0.00867 0.0075 0.8585 0.6079
0.000 0.0000 0.01750 0.00863 0.0000 0.7527 0.7528
0.250 0.0824 0.01803 0.00867 -0.0075 0.6079 0.8584
0.500 0.1349 0.01877 0.00881 -0.0109 0.5183 0.9153
0.750 0.1790 0.01941 0.00899 -0.0135 0.4602 0.9607
1.000 0.2341 0.01994 0.00909 -0.0189 0.4162 0.9965
1.250 0.2599 0.02024 0.00915 -0.0188 0.3918 1.0000
1.500 0.2811 0.02056 0.00927 -0.0177 0.3727 1.0000
1.750 0.3032 0.02090 0.00944 -0.0166 0.3571 1.0000
2.000 0.3264 0.02127 0.00966 -0.0158 0.3431 1.0000
2.250 0.3503 0.02166 0.00992 -0.0151 0.3302 1.0000
2.500 0.3746 0.02206 0.01028 -0.0143 0.3184 1.0000
2.750 0.3986 0.02251 0.01062 -0.0135 0.3089 1.0000
3.000 0.4221 0.02297 0.01104 -0.0127 0.2990 1.0000
3.250 0.4455 0.02347 0.01149 -0.0117 0.2904 1.0000
3.500 0.4687 0.02400 0.01199 -0.0108 0.2822 1.0000
3.750 0.4919 0.02459 0.01253 -0.0098 0.2752 1.0000
4.000 0.5146 0.02518 0.01317 -0.0088 0.2674 1.0000
4.250 0.5375 0.02579 0.01365 -0.0078 0.2612 1.0000
4.500 0.5595 0.02652 0.01456 -0.0067 0.2539 1.0000
4.750 0.5819 0.02721 0.01523 -0.0056 0.2480 1.0000
5.000 0.6039 0.02798 0.01602 -0.0045 0.2423 1.0000
5.250 0.6249 0.02882 0.01702 -0.0033 0.2356 1.0000
5.500 0.6468 0.02957 0.01774 -0.0022 0.2304 1.0000
6.000 0.6868 0.03161 0.02009 0.0003 0.2193 1.0000
6.250 0.7079 0.03242 0.02089 0.0015 0.2143 1.0000
6.500 0.7272 0.03355 0.02213 0.0028 0.2096 1.0000
6.750 0.7437 0.03497 0.02385 0.0043 0.2043 1.0000
7.000 0.7625 0.03602 0.02497 0.0057 0.1996 1.0000
7.250 0.7842 0.03684 0.02569 0.0068 0.1957 1.0000
7.500 0.7937 0.03894 0.02826 0.0087 0.1904 1.0000
7.750 0.8077 0.04055 0.03008 0.0103 0.1859 1.0000
8.000 0.8262 0.04158 0.03113 0.0116 0.1820 1.0000
8.250 0.8386 0.04332 0.03303 0.0132 0.1781 1.0000
8.500 0.8395 0.04619 0.03631 0.0152 0.1734 1.0000
8.750 0.8475 0.04830 0.03861 0.0169 0.1697 1.0000
9.000 0.8637 0.04947 0.03981 0.0182 0.1664 1.0000
9.250 0.8678 0.05185 0.04235 0.0198 0.1632 1.0000
9.500 0.8375 0.05740 0.04834 0.0218 0.1596 1.0000
9.750 0.8037 0.06316 0.05431 0.0227 0.1570 1.0000
10.000 0.7527 0.07074 0.06195 0.0217 0.1550 1.0000
10.250 0.7240 0.07840 0.06961 0.0174 0.1525 1.0000
10.500 0.7682 0.07459 0.06583 0.0228 0.1502 1.0000
10.750 0.6749 0.09435 0.08550 0.0082 0.1466 1.0000
11.000 0.6563 0.10120 0.09233 0.0045 0.1432 1.0000
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