EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.3 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e337-il-1000000.txt Download as CSV file: xf-e337-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 337 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2939 0.09947 0.09801 -0.0206 1.0000 0.0090
-10.500 -0.2934 0.09552 0.09407 -0.0218 1.0000 0.0090
-10.250 -0.2959 0.09064 0.08920 -0.0235 1.0000 0.0091
-10.000 -0.2853 0.08408 0.08261 -0.0294 0.9405 0.0091
-9.750 -0.2826 0.07750 0.07570 -0.0343 0.8462 0.0091
-9.500 -0.2874 0.07338 0.07139 -0.0353 0.7961 0.0091
-9.250 -0.3010 0.06786 0.06579 -0.0371 0.7716 0.0094
-9.000 -0.3133 0.06175 0.05962 -0.0408 0.7542 0.0093
-8.750 -0.3359 0.05528 0.05310 -0.0459 0.7414 0.0094
-8.500 -0.3555 0.05094 0.04864 -0.0465 0.7247 0.0094
-8.250 -0.3777 0.04665 0.04423 -0.0449 0.7095 0.0093
-8.000 -0.3907 0.04430 0.04178 -0.0419 0.6938 0.0094
-7.750 -0.3981 0.04087 0.03822 -0.0398 0.6797 0.0095
-7.500 -0.4001 0.03772 0.03495 -0.0379 0.6663 0.0095
-7.250 -0.3992 0.03464 0.03173 -0.0359 0.6538 0.0096
-7.000 -0.3964 0.03146 0.02839 -0.0339 0.6420 0.0098
-6.750 -0.3890 0.02898 0.02579 -0.0322 0.6300 0.0102
-6.500 -0.3826 0.02573 0.02236 -0.0300 0.6197 0.0107
-6.250 -0.3916 0.01739 0.01340 -0.0239 0.6157 0.0121
-6.000 -0.3771 0.01597 0.01189 -0.0225 0.6039 0.0123
-5.750 -0.3620 0.01454 0.01031 -0.0210 0.5926 0.0125
-5.500 -0.3456 0.01313 0.00875 -0.0195 0.5812 0.0128
-5.250 -0.3287 0.01161 0.00703 -0.0179 0.5715 0.0133
-5.000 -0.3086 0.01040 0.00537 -0.0153 0.5618 0.0151
-4.000 -0.2288 0.01540 0.00884 -0.0098 0.5355 0.0121
-3.750 -0.2000 0.01341 0.00663 -0.0092 0.5266 0.0092
-3.500 -0.1742 0.01272 0.00586 -0.0086 0.5168 0.0090
-3.250 -0.1498 0.01191 0.00498 -0.0078 0.5085 0.0089
-3.000 -0.1258 0.01138 0.00437 -0.0069 0.5000 0.0088
-2.750 -0.1016 0.01097 0.00391 -0.0060 0.4922 0.0088
-2.500 -0.0775 0.01062 0.00348 -0.0051 0.4838 0.0088
-2.250 -0.0526 0.01034 0.00316 -0.0044 0.4762 0.0089
-2.000 -0.0276 0.01013 0.00288 -0.0037 0.4685 0.0091
-1.750 -0.0030 0.00984 0.00255 -0.0029 0.4619 0.0096
-1.500 0.0224 0.00967 0.00233 -0.0023 0.4551 0.0113
-1.250 0.0464 0.00937 0.00210 -0.0014 0.4487 0.0342
-1.000 0.0709 0.00913 0.00201 -0.0007 0.4423 0.0784
-0.750 0.0944 0.00888 0.00193 0.0001 0.4359 0.1450
-0.500 0.0988 0.00739 0.00171 0.0042 0.4318 0.5304
-0.250 0.0966 0.00628 0.00181 0.0109 0.4278 0.8619
0.000 0.1184 0.00670 0.00224 0.0129 0.4225 0.9015
0.250 0.1446 0.00705 0.00256 0.0139 0.4172 0.9123
0.500 0.1699 0.00726 0.00274 0.0149 0.4122 0.9203
0.750 0.1992 0.00769 0.00312 0.0153 0.4068 0.9277
1.000 0.2237 0.00792 0.00330 0.0163 0.4023 0.9343
1.250 0.2645 0.00827 0.00362 0.0141 0.3974 0.9380
1.500 0.2989 0.00844 0.00372 0.0128 0.3922 0.9398
1.750 0.3261 0.00850 0.00372 0.0129 0.3876 0.9410
2.000 0.3527 0.00850 0.00370 0.0131 0.3843 0.9424
2.250 0.3764 0.00849 0.00367 0.0140 0.3803 0.9442
2.500 0.3960 0.00849 0.00363 0.0156 0.3762 0.9466
2.750 0.4154 0.00852 0.00361 0.0173 0.3723 0.9486
3.000 0.4430 0.00847 0.00356 0.0172 0.3692 0.9493
3.250 0.4707 0.00847 0.00355 0.0172 0.3655 0.9499
3.500 0.4984 0.00851 0.00355 0.0171 0.3615 0.9507
3.750 0.5251 0.00859 0.00359 0.0172 0.3572 0.9514
4.000 0.5526 0.00859 0.00361 0.0172 0.3545 0.9520
4.250 0.5796 0.00861 0.00362 0.0172 0.3509 0.9528
4.500 0.6063 0.00866 0.00366 0.0173 0.3473 0.9536
4.750 0.6319 0.00876 0.00372 0.0176 0.3430 0.9547
5.000 0.6579 0.00878 0.00376 0.0178 0.3402 0.9556
5.250 0.6835 0.00880 0.00379 0.0181 0.3371 0.9565
5.500 0.7084 0.00884 0.00383 0.0185 0.3333 0.9576
5.750 0.7323 0.00892 0.00388 0.0191 0.3290 0.9587
6.000 0.7569 0.00897 0.00394 0.0196 0.3253 0.9598
6.250 0.7816 0.00900 0.00399 0.0200 0.3213 0.9610
6.500 0.8060 0.00906 0.00405 0.0205 0.3174 0.9620
6.750 0.8308 0.00916 0.00414 0.0208 0.3130 0.9628
7.000 0.8579 0.00920 0.00422 0.0208 0.3100 0.9635
7.250 0.8850 0.00926 0.00430 0.0207 0.3061 0.9642
7.500 0.9111 0.00936 0.00440 0.0207 0.3010 0.9649
7.750 0.9373 0.00947 0.00452 0.0207 0.2959 0.9658
8.000 0.9639 0.00955 0.00464 0.0207 0.2911 0.9666
8.250 0.9890 0.00969 0.00477 0.0209 0.2853 0.9676
8.500 1.0146 0.00980 0.00491 0.0210 0.2804 0.9686
8.750 1.0396 0.00992 0.00505 0.0212 0.2741 0.9697
9.000 1.0631 0.01008 0.00521 0.0217 0.2676 0.9713
9.250 1.0868 0.01021 0.00536 0.0222 0.2609 0.9728
9.500 1.1085 0.01040 0.00555 0.0230 0.2539 0.9743
9.750 1.1331 0.01056 0.00574 0.0232 0.2458 0.9754
10.000 1.1584 0.01080 0.00597 0.0232 0.2373 0.9765
10.250 1.1830 0.01110 0.00626 0.0232 0.2265 0.9777
10.500 1.2074 0.01143 0.00657 0.0232 0.2149 0.9789
10.750 1.2310 0.01179 0.00692 0.0233 0.2028 0.9804
11.000 1.2525 0.01224 0.00733 0.0237 0.1886 0.9822
11.250 1.2719 0.01273 0.00777 0.0245 0.1746 0.9845
11.500 1.2933 0.01329 0.00830 0.0247 0.1603 0.9863
11.750 1.3164 0.01397 0.00893 0.0243 0.1444 0.9875
12.000 1.3378 0.01472 0.00963 0.0241 0.1290 0.9889
12.250 1.3569 0.01560 0.01044 0.0242 0.1144 0.9910
12.500 1.3742 0.01649 0.01130 0.0244 0.1029 0.9936
12.750 1.3916 0.01743 0.01222 0.0244 0.0919 0.9963
13.000 1.4076 0.01859 0.01336 0.0241 0.0808 0.9992
13.250 1.3961 0.01946 0.01424 0.0291 0.0763 1.0000
13.500 1.3945 0.02054 0.01537 0.0319 0.0714 1.0000
13.750 1.3909 0.02229 0.01711 0.0338 0.0641 1.0000
14.000 1.3853 0.02455 0.01935 0.0351 0.0562 1.0000
14.250 1.3916 0.02610 0.02100 0.0357 0.0561 1.0000
14.500 1.3826 0.02910 0.02399 0.0361 0.0480 1.0000
14.750 1.3860 0.03113 0.02612 0.0362 0.0480 1.0000
15.000 1.3814 0.03400 0.02905 0.0363 0.0441 1.0000
15.250 1.3744 0.03719 0.03228 0.0361 0.0410 1.0000
15.500 1.3641 0.04079 0.03592 0.0358 0.0372 1.0000
15.750 1.3558 0.04424 0.03944 0.0354 0.0348 1.0000
16.000 1.3427 0.04827 0.04351 0.0349 0.0321 1.0000
16.250 1.3336 0.05195 0.04725 0.0342 0.0298 1.0000
16.500 1.3272 0.05547 0.05086 0.0335 0.0291 1.0000
16.750 1.3196 0.05921 0.05468 0.0327 0.0283 1.0000
17.000 1.3051 0.06384 0.05935 0.0315 0.0256 1.0000
17.250 1.2980 0.06769 0.06327 0.0305 0.0243 1.0000
17.500 1.2890 0.07183 0.06747 0.0293 0.0227 1.0000
17.750 1.2795 0.07611 0.07182 0.0280 0.0217 1.0000
18.000 1.2695 0.08056 0.07633 0.0265 0.0205 1.0000
18.250 1.2635 0.08450 0.08033 0.0252 0.0190 1.0000
18.500 1.2552 0.08884 0.08472 0.0236 0.0177 1.0000
18.750 1.2459 0.09343 0.08937 0.0219 0.0169 1.0000
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