EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 500,000 Max Cl/Cd: 56.02 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e297-il-500000.txt Download as CSV file: xf-e297-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 297 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5221 0.13897 0.13699 0.0081 1.0000 0.0174
-13.250 -0.5202 0.13475 0.13276 0.0054 1.0000 0.0186
-9.750 -0.8860 0.03470 0.03048 -0.0240 1.0000 0.0072
-9.500 -0.8755 0.03315 0.02872 -0.0221 1.0000 0.0069
-9.250 -0.8627 0.03172 0.02713 -0.0206 1.0000 0.0068
-9.000 -0.8480 0.03036 0.02559 -0.0193 1.0000 0.0067
-8.750 -0.8418 0.02604 0.02089 -0.0171 1.0000 0.0064
-8.500 -0.8281 0.02356 0.01815 -0.0155 1.0000 0.0064
-8.000 -0.7784 0.01955 0.01370 -0.0163 0.9830 0.0065
-7.750 -0.7495 0.01803 0.01202 -0.0173 0.9731 0.0066
-7.500 -0.7257 0.01634 0.01014 -0.0173 0.9625 0.0069
-7.250 -0.7082 0.01487 0.00849 -0.0160 0.9509 0.0081
-7.000 -0.6880 0.01424 0.00778 -0.0147 0.9417 0.0101
-6.750 -0.6700 0.01338 0.00685 -0.0130 0.9332 0.0172
-6.500 -0.6497 0.01286 0.00627 -0.0118 0.9267 0.0257
-6.250 -0.6272 0.01242 0.00583 -0.0110 0.9204 0.0354
-6.000 -0.6055 0.01197 0.00544 -0.0101 0.9151 0.0530
-5.750 -0.5845 0.01137 0.00502 -0.0093 0.9098 0.0879
-5.500 -0.5627 0.01082 0.00465 -0.0085 0.9047 0.1292
-5.250 -0.5409 0.01033 0.00432 -0.0077 0.9004 0.1734
-4.750 -0.4959 0.00930 0.00370 -0.0065 0.8914 0.2863
-4.500 -0.4745 0.00875 0.00343 -0.0056 0.8874 0.3603
-4.250 -0.4533 0.00814 0.00318 -0.0047 0.8833 0.4488
-4.000 -0.4308 0.00768 0.00299 -0.0040 0.8790 0.5223
-3.750 -0.4071 0.00737 0.00286 -0.0033 0.8752 0.5796
-3.500 -0.3823 0.00719 0.00279 -0.0026 0.8718 0.6262
-3.250 -0.3562 0.00707 0.00277 -0.0023 0.8677 0.6635
-3.000 -0.3296 0.00704 0.00277 -0.0020 0.8638 0.6907
-2.750 -0.3027 0.00706 0.00277 -0.0017 0.8603 0.7107
-2.500 -0.2754 0.00709 0.00279 -0.0015 0.8567 0.7262
-2.250 -0.2477 0.00712 0.00279 -0.0014 0.8523 0.7391
-2.000 -0.2203 0.00716 0.00279 -0.0013 0.8483 0.7506
-1.500 -0.1653 0.00726 0.00287 -0.0009 0.8401 0.7699
-1.250 -0.1377 0.00729 0.00286 -0.0008 0.8356 0.7783
-1.000 -0.1104 0.00733 0.00288 -0.0005 0.8316 0.7855
-0.750 -0.0826 0.00735 0.00290 -0.0005 0.8263 0.7924
-0.500 -0.0551 0.00736 0.00291 -0.0003 0.8212 0.7990
-0.250 -0.0276 0.00739 0.00290 -0.0001 0.8168 0.8053
0.000 0.0000 0.00738 0.00293 0.0000 0.8108 0.8108
0.250 0.0276 0.00739 0.00290 0.0001 0.8053 0.8169
0.500 0.0551 0.00736 0.00291 0.0003 0.7989 0.8212
0.750 0.0826 0.00735 0.00289 0.0005 0.7924 0.8263
1.000 0.1104 0.00733 0.00288 0.0005 0.7855 0.8316
1.250 0.1377 0.00729 0.00286 0.0008 0.7782 0.8356
1.500 0.1653 0.00726 0.00287 0.0009 0.7699 0.8401
1.750 0.1930 0.00723 0.00281 0.0010 0.7613 0.8449
2.000 0.2203 0.00716 0.00279 0.0013 0.7506 0.8483
2.250 0.2477 0.00712 0.00279 0.0014 0.7391 0.8523
2.500 0.2754 0.00709 0.00279 0.0015 0.7262 0.8567
2.750 0.3027 0.00706 0.00277 0.0017 0.7107 0.8603
3.000 0.3296 0.00704 0.00277 0.0020 0.6909 0.8638
3.250 0.3563 0.00707 0.00277 0.0023 0.6636 0.8677
3.500 0.3824 0.00719 0.00279 0.0026 0.6259 0.8719
3.750 0.4071 0.00737 0.00286 0.0033 0.5795 0.8752
4.000 0.4308 0.00769 0.00299 0.0040 0.5213 0.8790
4.250 0.4534 0.00815 0.00318 0.0047 0.4483 0.8833
4.500 0.4747 0.00875 0.00343 0.0056 0.3604 0.8874
4.750 0.4962 0.00930 0.00370 0.0064 0.2864 0.8913
5.250 0.5413 0.01034 0.00432 0.0076 0.1732 0.9004
5.500 0.5631 0.01083 0.00466 0.0084 0.1290 0.9047
5.750 0.5850 0.01137 0.00503 0.0092 0.0873 0.9098
6.000 0.6062 0.01197 0.00544 0.0100 0.0531 0.9150
6.250 0.6279 0.01242 0.00584 0.0109 0.0353 0.9203
6.500 0.6504 0.01286 0.00628 0.0116 0.0258 0.9266
6.750 0.6708 0.01338 0.00685 0.0129 0.0171 0.9330
7.000 0.6889 0.01425 0.00778 0.0145 0.0096 0.9415
7.250 0.7091 0.01489 0.00851 0.0158 0.0080 0.9507
7.500 0.7274 0.01624 0.01003 0.0170 0.0070 0.9621
7.750 0.7502 0.01811 0.01209 0.0171 0.0066 0.9731
8.000 0.7795 0.01955 0.01370 0.0161 0.0064 0.9829
8.500 0.8286 0.02369 0.01829 0.0154 0.0064 1.0000
8.750 0.8426 0.02614 0.02099 0.0169 0.0065 1.0000
9.000 0.8487 0.03051 0.02576 0.0192 0.0067 1.0000
9.250 0.8640 0.03178 0.02719 0.0204 0.0068 1.0000
9.500 0.8773 0.03311 0.02869 0.0218 0.0070 1.0000
9.750 0.8877 0.03471 0.03050 0.0237 0.0072 1.0000
10.000 0.7834 0.03445 0.03135 0.0338 0.0099 1.0000
10.250 0.7635 0.03798 0.03506 0.0358 0.0102 1.0000
10.500 0.7398 0.04238 0.03964 0.0366 0.0105 1.0000
10.750 0.7156 0.04740 0.04482 0.0362 0.0106 1.0000
11.000 0.6940 0.05284 0.05040 0.0347 0.0106 1.0000
11.250 0.6716 0.05937 0.05707 0.0317 0.0106 1.0000
11.500 0.6489 0.06722 0.06505 0.0272 0.0104 1.0000
11.750 0.6311 0.07548 0.07341 0.0219 0.0101 1.0000
12.000 0.6054 0.08764 0.08568 0.0146 0.0099 1.0000
12.250 0.5735 0.10270 0.10076 0.0078 0.0102 1.0000
12.500 0.5561 0.11166 0.10970 0.0038 0.0108 1.0000
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Polar data table (+)
Polar graphs
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