EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 50,000 Max Cl/Cd: 29.33 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e297-il-50000.txt Download as CSV file: xf-e297-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6440 0.09890 0.09252 -0.0195 1.0000 0.1320
-10.250 -0.6486 0.09137 0.08502 -0.0233 1.0000 0.1217
-10.000 -0.7065 0.08089 0.07453 -0.0324 1.0000 0.1056
-9.750 -0.7288 0.07628 0.06982 -0.0331 1.0000 0.1021
-9.500 -0.7401 0.07175 0.06524 -0.0325 1.0000 0.1000
-9.250 -0.7547 0.06737 0.06071 -0.0316 1.0000 0.0976
-9.000 -0.7735 0.06279 0.05583 -0.0301 1.0000 0.0946
-8.750 -0.7986 0.05912 0.05134 -0.0268 1.0000 0.0905
-8.500 -0.7943 0.05468 0.04661 -0.0251 1.0000 0.0900
-8.250 -0.7928 0.05112 0.04254 -0.0226 1.0000 0.0906
-8.000 -0.7770 0.04763 0.03925 -0.0218 1.0000 0.0986
-7.750 -0.7709 0.04429 0.03537 -0.0192 1.0000 0.1014
-7.500 -0.7612 0.04102 0.03144 -0.0163 1.0000 0.1035
-7.250 -0.7428 0.03778 0.02822 -0.0149 1.0000 0.1122
-7.000 -0.7285 0.03539 0.02565 -0.0128 1.0000 0.1251
-6.750 -0.7068 0.03258 0.02255 -0.0111 1.0000 0.1378
-6.500 -0.6869 0.03031 0.02028 -0.0093 1.0000 0.1610
-6.250 -0.6669 0.02814 0.01827 -0.0074 1.0000 0.1969
-6.000 -0.6545 0.02614 0.01673 -0.0045 1.0000 0.2519
-5.750 -0.6494 0.02403 0.01538 -0.0005 1.0000 0.3340
-5.500 -0.6524 0.02224 0.01470 0.0055 1.0000 0.4528
-5.250 -0.6468 0.02240 0.01574 0.0132 1.0000 0.5949
-5.000 -0.6293 0.02458 0.01791 0.0206 1.0000 0.6781
-4.750 -0.6004 0.02715 0.02016 0.0264 1.0000 0.7330
-4.500 -0.5297 0.03030 0.02262 0.0264 1.0000 0.7830
-4.250 -0.4295 0.03198 0.02354 0.0188 1.0000 0.8303
-4.000 -0.3249 0.03193 0.02277 0.0075 1.0000 0.8692
-3.750 -0.2689 0.03120 0.02169 0.0023 1.0000 0.9000
-3.500 -0.2067 0.03010 0.02026 -0.0047 1.0000 0.9278
-3.250 -0.1466 0.02879 0.01865 -0.0120 1.0000 0.9531
-3.000 -0.0834 0.02719 0.01683 -0.0204 1.0000 0.9760
-2.750 -0.0196 0.02548 0.01490 -0.0294 1.0000 0.9973
-2.500 -0.0053 0.02498 0.01435 -0.0293 1.0000 1.0000
-2.250 -0.0020 0.02478 0.01414 -0.0270 1.0000 1.0000
-2.000 -0.0007 0.02467 0.01401 -0.0244 1.0000 1.0000
-1.750 -0.0008 0.02460 0.01393 -0.0214 1.0000 1.0000
-1.500 -0.0012 0.02456 0.01388 -0.0183 1.0000 1.0000
-1.250 -0.0016 0.02453 0.01383 -0.0152 1.0000 1.0000
-1.000 -0.0017 0.02450 0.01378 -0.0122 1.0000 1.0000
-0.750 -0.0016 0.02448 0.01374 -0.0091 1.0000 1.0000
-0.500 -0.0012 0.02446 0.01371 -0.0061 1.0000 1.0000
-0.250 -0.0006 0.02445 0.01369 -0.0030 1.0000 1.0000
0.000 0.0000 0.02444 0.01369 0.0000 1.0000 1.0000
0.250 0.0006 0.02445 0.01369 0.0030 1.0000 1.0000
0.500 0.0012 0.02446 0.01371 0.0061 1.0000 1.0000
0.750 0.0016 0.02447 0.01373 0.0091 1.0000 1.0000
1.000 0.0017 0.02449 0.01377 0.0122 1.0000 1.0000
1.250 0.0016 0.02452 0.01382 0.0153 1.0000 1.0000
1.500 0.0012 0.02455 0.01386 0.0184 1.0000 1.0000
1.750 0.0007 0.02459 0.01392 0.0214 1.0000 1.0000
2.000 0.0007 0.02465 0.01400 0.0244 1.0000 1.0000
2.250 0.0020 0.02476 0.01412 0.0270 1.0000 1.0000
2.500 0.0054 0.02496 0.01433 0.0293 1.0000 1.0000
2.750 0.0200 0.02547 0.01488 0.0293 0.9973 1.0000
3.000 0.0834 0.02717 0.01680 0.0204 0.9761 1.0000
3.250 0.1466 0.02877 0.01863 0.0120 0.9533 1.0000
3.500 0.2064 0.03006 0.02023 0.0047 0.9279 1.0000
3.750 0.2692 0.03117 0.02166 -0.0024 0.9000 1.0000
4.000 0.3252 0.03190 0.02274 -0.0076 0.8692 1.0000
4.250 0.4303 0.03194 0.02351 -0.0189 0.8304 1.0000
4.500 0.5298 0.03027 0.02259 -0.0264 0.7830 1.0000
4.750 0.6004 0.02713 0.02014 -0.0264 0.7334 1.0000
5.000 0.6289 0.02457 0.01789 -0.0205 0.6784 1.0000
5.250 0.6463 0.02239 0.01573 -0.0131 0.5957 1.0000
5.500 0.6518 0.02222 0.01469 -0.0054 0.4542 1.0000
5.750 0.6490 0.02400 0.01534 0.0005 0.3352 1.0000
6.000 0.6540 0.02612 0.01669 0.0046 0.2527 1.0000
6.250 0.6663 0.02812 0.01824 0.0075 0.1973 1.0000
6.500 0.6866 0.03030 0.02028 0.0094 0.1617 1.0000
6.750 0.7062 0.03255 0.02252 0.0112 0.1381 1.0000
7.000 0.7280 0.03537 0.02563 0.0129 0.1253 1.0000
7.250 0.7426 0.03776 0.02819 0.0150 0.1124 1.0000
7.500 0.7611 0.04100 0.03142 0.0163 0.1036 1.0000
7.750 0.7709 0.04430 0.03538 0.0192 0.1014 1.0000
8.000 0.7772 0.04766 0.03927 0.0218 0.0986 1.0000
8.250 0.7930 0.05116 0.04258 0.0226 0.0906 1.0000
8.500 0.7942 0.05475 0.04670 0.0251 0.0899 1.0000
8.750 0.7996 0.05921 0.05142 0.0267 0.0905 1.0000
9.000 0.7736 0.06293 0.05597 0.0300 0.0946 1.0000
9.250 0.7548 0.06753 0.06088 0.0315 0.0975 1.0000
9.500 0.7408 0.07190 0.06539 0.0322 0.1001 1.0000
9.750 0.7312 0.07643 0.06997 0.0329 0.1023 1.0000
10.000 0.6087 0.07604 0.07007 0.0328 0.1151 1.0000
10.250 0.6006 0.08192 0.07594 0.0314 0.1166 1.0000
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Polar data table (+)
Polar graphs
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