EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 682 AIRFOIL (e682-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.69 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e682-il-1000000-n5.txt Download as CSV file: xf-e682-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 682 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5305 0.05328 0.05024 -0.1091 0.7667 0.0059
-13.000 -0.5560 0.04708 0.04388 -0.1124 0.7649 0.0059
-12.750 -0.5918 0.04131 0.03784 -0.1126 0.7630 0.0061
-12.500 -0.6203 0.03713 0.03341 -0.1105 0.7612 0.0061
-12.250 -0.6329 0.03453 0.03063 -0.1081 0.7597 0.0061
-12.000 -0.6437 0.03214 0.02804 -0.1053 0.7583 0.0060
-11.750 -0.6492 0.03011 0.02583 -0.1024 0.7572 0.0062
-11.500 -0.6493 0.02850 0.02405 -0.0997 0.7561 0.0063
-11.250 -0.6514 0.02669 0.02205 -0.0966 0.7549 0.0062
-11.000 -0.6444 0.02560 0.02081 -0.0942 0.7537 0.0064
-10.750 -0.6354 0.02471 0.01980 -0.0919 0.7526 0.0065
-10.500 -0.6311 0.02326 0.01817 -0.0889 0.7514 0.0065
-10.250 -0.6188 0.02274 0.01754 -0.0868 0.7503 0.0066
-10.000 -0.6051 0.02186 0.01653 -0.0850 0.7492 0.0066
-9.750 -0.5897 0.02092 0.01545 -0.0835 0.7482 0.0066
-9.500 -0.5723 0.02011 0.01453 -0.0823 0.7473 0.0067
-9.250 -0.5569 0.01874 0.01298 -0.0808 0.7462 0.0068
-9.000 -0.5385 0.01778 0.01190 -0.0797 0.7450 0.0069
-8.750 -0.5185 0.01705 0.01108 -0.0788 0.7438 0.0070
-8.500 -0.4970 0.01653 0.01050 -0.0781 0.7430 0.0071
-8.250 -0.4754 0.01590 0.00981 -0.0774 0.7423 0.0072
-8.000 -0.4528 0.01540 0.00926 -0.0768 0.7416 0.0073
-7.750 -0.4302 0.01489 0.00870 -0.0762 0.7409 0.0074
-7.500 -0.4070 0.01445 0.00821 -0.0757 0.7401 0.0076
-7.250 -0.3836 0.01402 0.00774 -0.0752 0.7393 0.0077
-7.000 -0.3602 0.01358 0.00727 -0.0747 0.7385 0.0078
-6.750 -0.3364 0.01319 0.00685 -0.0743 0.7376 0.0080
-6.500 -0.3124 0.01283 0.00644 -0.0739 0.7367 0.0083
-6.250 -0.2880 0.01250 0.00608 -0.0735 0.7357 0.0085
-6.000 -0.2639 0.01215 0.00569 -0.0731 0.7347 0.0088
-5.750 -0.2395 0.01182 0.00534 -0.0727 0.7338 0.0089
-5.500 -0.2148 0.01153 0.00501 -0.0723 0.7330 0.0091
-5.250 -0.1894 0.01129 0.00474 -0.0721 0.7322 0.0093
-5.000 -0.1650 0.01096 0.00438 -0.0717 0.7311 0.0095
-4.750 -0.1405 0.01064 0.00403 -0.0713 0.7300 0.0099
-4.500 -0.1152 0.01041 0.00377 -0.0711 0.7288 0.0103
-4.250 -0.0893 0.01022 0.00357 -0.0710 0.7276 0.0107
-4.000 -0.0632 0.01002 0.00337 -0.0708 0.7266 0.0111
-3.750 -0.0370 0.00984 0.00319 -0.0707 0.7253 0.0116
-3.500 -0.0105 0.00968 0.00302 -0.0707 0.7239 0.0122
-3.250 0.0160 0.00952 0.00286 -0.0707 0.7224 0.0131
-3.000 0.0426 0.00936 0.00270 -0.0706 0.7209 0.0145
-2.750 0.0694 0.00922 0.00256 -0.0706 0.7195 0.0165
-2.500 0.0949 0.00896 0.00241 -0.0704 0.7179 0.0423
-2.250 0.1201 0.00870 0.00229 -0.0703 0.7163 0.0798
-2.000 0.1449 0.00840 0.00217 -0.0700 0.7147 0.1358
-1.750 0.1689 0.00805 0.00206 -0.0697 0.7129 0.2138
-1.500 0.1920 0.00759 0.00195 -0.0692 0.7114 0.3140
-1.250 0.2133 0.00696 0.00182 -0.0686 0.7096 0.4571
-1.000 0.2324 0.00600 0.00160 -0.0676 0.7075 0.6653
-0.750 0.2569 0.00582 0.00182 -0.0670 0.7055 0.7842
-0.500 0.2858 0.00593 0.00193 -0.0672 0.7034 0.8045
-0.250 0.3147 0.00605 0.00201 -0.0675 0.7013 0.8148
0.000 0.3433 0.00614 0.00210 -0.0677 0.6992 0.8202
0.250 0.3717 0.00627 0.00222 -0.0679 0.6969 0.8257
0.500 0.4007 0.00636 0.00231 -0.0682 0.6941 0.8313
0.750 0.4286 0.00641 0.00239 -0.0683 0.6906 0.8346
1.000 0.4570 0.00645 0.00241 -0.0686 0.6869 0.8364
1.250 0.4855 0.00646 0.00239 -0.0689 0.6833 0.8373
1.500 0.5145 0.00645 0.00240 -0.0694 0.6791 0.8379
1.750 0.5432 0.00644 0.00239 -0.0698 0.6737 0.8384
2.000 0.5715 0.00645 0.00236 -0.0701 0.6679 0.8389
2.250 0.5999 0.00645 0.00237 -0.0705 0.6600 0.8396
2.500 0.6277 0.00647 0.00237 -0.0707 0.6508 0.8403
2.750 0.6549 0.00651 0.00237 -0.0708 0.6385 0.8408
3.000 0.6811 0.00659 0.00238 -0.0708 0.6218 0.8413
3.250 0.7057 0.00672 0.00244 -0.0704 0.6018 0.8419
3.500 0.7294 0.00691 0.00253 -0.0699 0.5817 0.8424
3.750 0.7525 0.00712 0.00265 -0.0692 0.5589 0.8430
4.000 0.7745 0.00737 0.00280 -0.0684 0.5367 0.8436
4.250 0.7960 0.00763 0.00297 -0.0675 0.5124 0.8443
4.500 0.8172 0.00789 0.00314 -0.0665 0.4914 0.8450
4.750 0.8387 0.00812 0.00331 -0.0656 0.4718 0.8455
5.000 0.8590 0.00838 0.00350 -0.0645 0.4515 0.8460
5.250 0.8778 0.00867 0.00370 -0.0631 0.4313 0.8465
5.500 0.8959 0.00896 0.00391 -0.0616 0.4101 0.8469
5.750 0.9092 0.00928 0.00414 -0.0591 0.3871 0.8476
6.000 0.9178 0.00967 0.00442 -0.0557 0.3599 0.8484
6.500 0.9338 0.01075 0.00525 -0.0491 0.3016 0.8500
6.750 0.9387 0.01147 0.00580 -0.0456 0.2667 0.8509
7.000 0.9435 0.01226 0.00642 -0.0422 0.2309 0.8517
7.250 0.9544 0.01289 0.00696 -0.0399 0.2089 0.8526
7.500 0.9646 0.01359 0.00755 -0.0376 0.1850 0.8535
7.750 0.9743 0.01435 0.00820 -0.0353 0.1613 0.8543
8.000 0.9870 0.01502 0.00880 -0.0336 0.1435 0.8550
8.250 0.9967 0.01586 0.00951 -0.0315 0.1209 0.8557
8.500 1.0083 0.01664 0.01021 -0.0297 0.1017 0.8564
8.750 1.0185 0.01751 0.01098 -0.0278 0.0822 0.8571
9.000 1.0290 0.01840 0.01177 -0.0260 0.0636 0.8578
9.250 1.0391 0.01933 0.01261 -0.0243 0.0465 0.8585
9.500 1.0513 0.02016 0.01339 -0.0228 0.0359 0.8591
9.750 1.0622 0.02110 0.01427 -0.0212 0.0244 0.8597
10.000 1.0703 0.02223 0.01532 -0.0194 0.0112 0.8603
10.250 1.0840 0.02304 0.01613 -0.0183 0.0086 0.8608
10.500 1.0980 0.02384 0.01695 -0.0172 0.0077 0.8613
10.750 1.1124 0.02464 0.01778 -0.0162 0.0069 0.8618
11.000 1.1272 0.02543 0.01861 -0.0153 0.0066 0.8622
11.250 1.1414 0.02623 0.01945 -0.0144 0.0063 0.8628
11.500 1.1551 0.02709 0.02036 -0.0134 0.0061 0.8635
11.750 1.1671 0.02809 0.02140 -0.0123 0.0056 0.8642
12.000 1.1802 0.02903 0.02239 -0.0114 0.0055 0.8648
12.250 1.1914 0.03012 0.02353 -0.0103 0.0052 0.8655
12.500 1.2023 0.03126 0.02473 -0.0093 0.0052 0.8663
12.750 1.2123 0.03250 0.02604 -0.0083 0.0050 0.8671
13.000 1.2241 0.03363 0.02722 -0.0074 0.0048 0.8679
13.250 1.2344 0.03490 0.02855 -0.0066 0.0048 0.8686
13.500 1.2451 0.03617 0.02988 -0.0058 0.0047 0.8693
13.750 1.2556 0.03748 0.03125 -0.0051 0.0046 0.8700
14.000 1.2640 0.03901 0.03285 -0.0043 0.0046 0.8707
14.250 1.2722 0.04058 0.03449 -0.0035 0.0044 0.8714
14.500 1.2803 0.04222 0.03620 -0.0029 0.0044 0.8721
14.750 1.2873 0.04399 0.03804 -0.0023 0.0043 0.8728
15.000 1.2941 0.04583 0.03995 -0.0018 0.0041 0.8735
15.250 1.3013 0.04768 0.04187 -0.0014 0.0041 0.8742
15.500 1.3054 0.04992 0.04419 -0.0009 0.0040 0.8749
15.750 1.3114 0.05199 0.04633 -0.0007 0.0039 0.8755
16.000 1.3153 0.05434 0.04876 -0.0005 0.0039 0.8761
16.250 1.3180 0.05691 0.05142 -0.0004 0.0039 0.8767
16.750 1.3221 0.06240 0.05708 -0.0007 0.0038 0.8782
17.000 1.3235 0.06533 0.06010 -0.0010 0.0037 0.8790
17.250 1.3230 0.06856 0.06343 -0.0014 0.0037 0.8797
17.500 1.3213 0.07207 0.06705 -0.0021 0.0037 0.8805
17.750 1.3178 0.07590 0.07097 -0.0029 0.0035 0.8813
18.000 1.3134 0.08000 0.07519 -0.0040 0.0035 0.8820
18.250 1.3087 0.08421 0.07950 -0.0052 0.0034 0.8827
18.500 1.2993 0.08925 0.08466 -0.0069 0.0034 0.8833
18.750 1.2912 0.09424 0.08977 -0.0087 0.0033 0.8840
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Polar data table (+)
Polar graphs
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