EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 200,000 Max Cl/Cd: 46.91 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e297-il-200000.txt Download as CSV file: xf-e297-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.8194 0.04348 0.03840 -0.0268 1.0000 0.0177
-9.000 -0.8207 0.03970 0.03427 -0.0244 1.0000 0.0172
-8.750 -0.8171 0.03611 0.03028 -0.0219 1.0000 0.0169
-8.500 -0.8083 0.03289 0.02666 -0.0198 1.0000 0.0167
-8.250 -0.7952 0.03008 0.02350 -0.0179 1.0000 0.0167
-8.000 -0.7800 0.02773 0.02084 -0.0160 1.0000 0.0173
-7.750 -0.7658 0.02590 0.01878 -0.0139 1.0000 0.0178
-7.500 -0.7577 0.02482 0.01752 -0.0105 1.0000 0.0187
-7.250 -0.7550 0.02263 0.01523 -0.0066 1.0000 0.0210
-7.000 -0.7506 0.02209 0.01468 -0.0031 1.0000 0.0241
-6.750 -0.7418 0.02130 0.01378 0.0001 1.0000 0.0274
-6.500 -0.7370 0.01964 0.01208 0.0038 1.0000 0.0323
-6.250 -0.7122 0.01847 0.01084 0.0036 0.9969 0.0439
-6.000 -0.6822 0.01738 0.00976 0.0023 0.9930 0.0598
-5.750 -0.6562 0.01620 0.00868 0.0018 0.9883 0.0873
-5.500 -0.6298 0.01484 0.00772 0.0009 0.9839 0.1514
-5.250 -0.6032 0.01373 0.00711 -0.0001 0.9799 0.2482
-5.000 -0.5819 0.01274 0.00664 0.0001 0.9745 0.3577
-4.750 -0.5563 0.01188 0.00634 -0.0003 0.9703 0.4794
-4.500 -0.5291 0.01142 0.00626 -0.0004 0.9666 0.5782
-4.250 -0.5044 0.01135 0.00638 0.0004 0.9616 0.6417
-4.000 -0.4721 0.01149 0.00656 -0.0002 0.9580 0.6859
-3.750 -0.4360 0.01173 0.00674 -0.0015 0.9553 0.7185
-3.500 -0.4083 0.01200 0.00696 -0.0012 0.9507 0.7402
-3.250 -0.3781 0.01226 0.00712 -0.0014 0.9464 0.7589
-3.000 -0.3434 0.01250 0.00727 -0.0024 0.9433 0.7748
-2.750 -0.3069 0.01275 0.00746 -0.0037 0.9409 0.7883
-2.500 -0.2843 0.01300 0.00769 -0.0023 0.9347 0.7995
-2.250 -0.2525 0.01322 0.00785 -0.0026 0.9308 0.8105
-2.000 -0.2181 0.01338 0.00796 -0.0035 0.9278 0.8207
-1.750 -0.1963 0.01352 0.00806 -0.0022 0.9213 0.8315
-1.500 -0.1646 0.01369 0.00822 -0.0024 0.9170 0.8388
-1.250 -0.1321 0.01376 0.00824 -0.0029 0.9136 0.8473
-1.000 -0.1106 0.01389 0.00836 -0.0015 0.9063 0.8560
-0.750 -0.0796 0.01394 0.00839 -0.0016 0.9018 0.8625
-0.500 -0.0561 0.01399 0.00843 -0.0007 0.8953 0.8710
-0.250 -0.0266 0.01402 0.00845 -0.0005 0.8895 0.8764
0.000 0.0000 0.01403 0.00844 0.0000 0.8837 0.8837
0.250 0.0266 0.01402 0.00845 0.0005 0.8764 0.8895
0.500 0.0561 0.01399 0.00842 0.0007 0.8710 0.8953
0.750 0.0796 0.01394 0.00839 0.0017 0.8625 0.9018
1.000 0.1106 0.01389 0.00835 0.0015 0.8560 0.9063
1.250 0.1320 0.01376 0.00824 0.0029 0.8474 0.9136
1.500 0.1645 0.01369 0.00821 0.0024 0.8387 0.9171
1.750 0.1960 0.01351 0.00805 0.0023 0.8316 0.9214
2.000 0.2180 0.01337 0.00795 0.0036 0.8207 0.9278
2.250 0.2522 0.01321 0.00784 0.0027 0.8104 0.9309
2.500 0.2839 0.01300 0.00769 0.0024 0.7996 0.9349
2.750 0.3067 0.01274 0.00745 0.0038 0.7881 0.9409
3.000 0.3432 0.01249 0.00726 0.0025 0.7748 0.9434
3.250 0.3777 0.01225 0.00711 0.0014 0.7589 0.9466
3.500 0.4075 0.01199 0.00695 0.0013 0.7405 0.9510
3.750 0.4358 0.01172 0.00673 0.0016 0.7186 0.9555
4.000 0.4718 0.01148 0.00655 0.0002 0.6862 0.9581
4.250 0.5038 0.01133 0.00636 -0.0003 0.6418 0.9618
4.500 0.5280 0.01141 0.00625 0.0006 0.5790 0.9670
4.750 0.5563 0.01186 0.00633 0.0003 0.4799 0.9705
5.000 0.5818 0.01272 0.00663 -0.0001 0.3598 0.9747
5.250 0.6028 0.01370 0.00709 0.0002 0.2494 0.9803
5.500 0.6300 0.01483 0.00771 -0.0010 0.1507 0.9841
5.750 0.6563 0.01619 0.00867 -0.0019 0.0869 0.9885
6.000 0.6822 0.01737 0.00975 -0.0023 0.0599 0.9933
6.250 0.7124 0.01847 0.01083 -0.0036 0.0437 0.9971
6.500 0.7361 0.01961 0.01205 -0.0037 0.0325 1.0000
6.750 0.7408 0.02129 0.01376 0.0001 0.0275 1.0000
7.000 0.7494 0.02191 0.01449 0.0032 0.0234 1.0000
7.250 0.7539 0.02257 0.01517 0.0068 0.0210 1.0000
7.500 0.7570 0.02493 0.01763 0.0106 0.0188 1.0000
7.750 0.7655 0.02592 0.01879 0.0139 0.0179 1.0000
8.000 0.7802 0.02772 0.02083 0.0160 0.0171 1.0000
8.250 0.7957 0.03013 0.02355 0.0178 0.0166 1.0000
8.500 0.8086 0.03300 0.02680 0.0197 0.0166 1.0000
8.750 0.8177 0.03619 0.03036 0.0218 0.0169 1.0000
9.000 0.8210 0.03984 0.03443 0.0243 0.0172 1.0000
9.250 0.8196 0.04365 0.03859 0.0267 0.0176 1.0000
9.500 0.8133 0.04759 0.04280 0.0291 0.0182 1.0000
10.500 0.7314 0.06599 0.06237 0.0363 0.0253 1.0000
10.750 0.7080 0.07158 0.06808 0.0340 0.0258 1.0000
11.000 0.6875 0.07785 0.07445 0.0297 0.0258 1.0000
11.250 0.6644 0.08703 0.08371 0.0226 0.0259 1.0000
11.500 0.6479 0.09704 0.09371 0.0161 0.0269 1.0000
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Polar data table (+)
Polar graphs
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