EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 50,000 Max Cl/Cd: 28.75 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e297-il-50000-n5.txt Download as CSV file: xf-e297-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6528 0.09719 0.09051 -0.0203 1.0000 0.0360
-11.250 -0.6684 0.08923 0.08255 -0.0257 1.0000 0.0353
-11.000 -0.6892 0.08177 0.07504 -0.0306 1.0000 0.0348
-10.750 -0.7096 0.07573 0.06890 -0.0341 1.0000 0.0343
-10.500 -0.7298 0.07061 0.06365 -0.0360 1.0000 0.0339
-10.250 -0.7482 0.06626 0.05913 -0.0365 1.0000 0.0336
-10.000 -0.7651 0.06243 0.05510 -0.0356 1.0000 0.0336
-9.750 -0.7787 0.05906 0.05150 -0.0337 1.0000 0.0336
-9.500 -0.7876 0.05549 0.04763 -0.0318 1.0000 0.0340
-9.250 -0.7903 0.05205 0.04383 -0.0298 1.0000 0.0345
-9.000 -0.7882 0.04860 0.03998 -0.0279 1.0000 0.0355
-8.750 -0.7810 0.04527 0.03619 -0.0261 1.0000 0.0371
-8.500 -0.7707 0.04244 0.03279 -0.0242 1.0000 0.0403
-8.250 -0.7571 0.04009 0.03043 -0.0232 1.0000 0.0445
-8.000 -0.7367 0.03747 0.02745 -0.0220 1.0000 0.0491
-7.750 -0.7155 0.03517 0.02499 -0.0211 1.0000 0.0554
-7.500 -0.6950 0.03342 0.02299 -0.0199 1.0000 0.0653
-7.250 -0.6741 0.03155 0.02110 -0.0187 1.0000 0.0746
-7.000 -0.6570 0.03007 0.01943 -0.0172 1.0000 0.0900
-6.750 -0.6444 0.02861 0.01811 -0.0152 1.0000 0.1083
-6.500 -0.6345 0.02723 0.01686 -0.0127 1.0000 0.1335
-6.250 -0.6283 0.02592 0.01578 -0.0098 1.0000 0.1683
-6.000 -0.6246 0.02468 0.01485 -0.0065 1.0000 0.2136
-5.750 -0.6228 0.02350 0.01405 -0.0027 1.0000 0.2718
-5.500 -0.6212 0.02242 0.01340 0.0012 1.0000 0.3444
-5.250 -0.6173 0.02156 0.01300 0.0053 1.0000 0.4283
-5.000 -0.6082 0.02114 0.01299 0.0093 1.0000 0.5165
-4.750 -0.5935 0.02129 0.01335 0.0131 1.0000 0.5910
-4.500 -0.5781 0.02168 0.01371 0.0168 1.0000 0.6446
-4.250 -0.5639 0.02205 0.01387 0.0203 1.0000 0.6853
-4.000 -0.5514 0.02234 0.01397 0.0239 1.0000 0.7191
-3.750 -0.5388 0.02260 0.01404 0.0273 1.0000 0.7486
-3.500 -0.5214 0.02295 0.01421 0.0302 1.0000 0.7735
-3.250 -0.5020 0.02325 0.01432 0.0326 1.0000 0.7960
-3.000 -0.4854 0.02336 0.01426 0.0350 1.0000 0.8180
-2.750 -0.4593 0.02360 0.01429 0.0359 1.0000 0.8362
-2.500 -0.4349 0.02371 0.01417 0.0368 1.0000 0.8541
-2.250 -0.4080 0.02378 0.01405 0.0368 0.9987 0.8712
-2.000 -0.3664 0.02396 0.01402 0.0340 0.9944 0.8851
-1.750 -0.3214 0.02411 0.01394 0.0304 0.9904 0.8966
-1.500 -0.2757 0.02421 0.01387 0.0264 0.9861 0.9069
-1.250 -0.2295 0.02430 0.01381 0.0222 0.9818 0.9167
-1.000 -0.1872 0.02432 0.01369 0.0185 0.9764 0.9263
-0.750 -0.1362 0.02434 0.01362 0.0132 0.9720 0.9330
-0.500 -0.0924 0.02439 0.01360 0.0091 0.9666 0.9414
-0.250 -0.0453 0.02436 0.01353 0.0044 0.9606 0.9476
0.000 0.0000 0.02441 0.01356 0.0000 0.9548 0.9548
0.250 0.0453 0.02436 0.01352 -0.0044 0.9476 0.9606
0.500 0.0923 0.02438 0.01359 -0.0091 0.9414 0.9666
0.750 0.1363 0.02434 0.01361 -0.0132 0.9331 0.9721
1.000 0.1875 0.02431 0.01367 -0.0186 0.9264 0.9765
1.250 0.2298 0.02429 0.01380 -0.0222 0.9167 0.9818
1.500 0.2759 0.02419 0.01385 -0.0265 0.9069 0.9862
1.750 0.3217 0.02409 0.01392 -0.0305 0.8967 0.9905
2.000 0.3667 0.02394 0.01401 -0.0341 0.8852 0.9945
2.250 0.4082 0.02376 0.01403 -0.0369 0.8713 0.9988
2.500 0.4347 0.02370 0.01415 -0.0367 0.8543 1.0000
2.750 0.4590 0.02359 0.01428 -0.0359 0.8363 1.0000
3.000 0.4849 0.02336 0.01424 -0.0349 0.8181 1.0000
3.250 0.5015 0.02323 0.01430 -0.0325 0.7961 1.0000
3.500 0.5210 0.02294 0.01419 -0.0301 0.7736 1.0000
3.750 0.5382 0.02259 0.01403 -0.0272 0.7486 1.0000
4.000 0.5510 0.02233 0.01395 -0.0238 0.7194 1.0000
4.250 0.5633 0.02204 0.01385 -0.0202 0.6855 1.0000
4.500 0.5775 0.02167 0.01371 -0.0167 0.6448 1.0000
4.750 0.5929 0.02129 0.01335 -0.0130 0.5917 1.0000
5.000 0.6075 0.02113 0.01298 -0.0092 0.5173 1.0000
5.250 0.6167 0.02154 0.01299 -0.0052 0.4294 1.0000
5.500 0.6206 0.02241 0.01339 -0.0011 0.3448 1.0000
5.750 0.6224 0.02348 0.01403 0.0028 0.2723 1.0000
6.000 0.6243 0.02466 0.01483 0.0065 0.2139 1.0000
6.250 0.6281 0.02591 0.01577 0.0098 0.1683 1.0000
6.500 0.6346 0.02722 0.01684 0.0127 0.1336 1.0000
6.750 0.6446 0.02861 0.01810 0.0152 0.1082 1.0000
7.000 0.6574 0.03007 0.01945 0.0171 0.0898 1.0000
7.250 0.6746 0.03155 0.02110 0.0187 0.0746 1.0000
7.500 0.6955 0.03345 0.02301 0.0198 0.0651 1.0000
7.750 0.7158 0.03517 0.02498 0.0210 0.0552 1.0000
8.000 0.7375 0.03751 0.02750 0.0219 0.0490 1.0000
8.250 0.7578 0.04013 0.03047 0.0231 0.0444 1.0000
8.500 0.7713 0.04259 0.03288 0.0240 0.0401 1.0000
8.750 0.7819 0.04533 0.03625 0.0259 0.0371 1.0000
9.000 0.7889 0.04871 0.04010 0.0278 0.0354 1.0000
9.250 0.7908 0.05218 0.04398 0.0297 0.0344 1.0000
9.500 0.7883 0.05560 0.04775 0.0316 0.0340 1.0000
9.750 0.7798 0.05914 0.05159 0.0335 0.0337 1.0000
10.000 0.7656 0.06258 0.05526 0.0354 0.0335 1.0000
10.250 0.7499 0.06630 0.05917 0.0362 0.0337 1.0000
10.500 0.7310 0.07071 0.06375 0.0357 0.0339 1.0000
10.750 0.7095 0.07605 0.06923 0.0337 0.0342 1.0000
11.000 0.6896 0.08207 0.07534 0.0302 0.0348 1.0000
11.250 0.6696 0.08945 0.08277 0.0252 0.0354 1.0000
11.500 0.6538 0.09749 0.09081 0.0198 0.0360 1.0000
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Polar data table (+)
Polar graphs
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