EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 329 AIRFOIL (e329-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.92 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e329-il-1000000.txt Download as CSV file: xf-e329-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 329 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3648 0.12209 0.12039 -0.0231 1.0000 0.0084
-11.500 -0.3647 0.11777 0.11609 -0.0243 1.0000 0.0085
-11.250 -0.3620 0.11446 0.11279 -0.0250 1.0000 0.0086
-11.000 -0.3582 0.11141 0.10976 -0.0256 1.0000 0.0086
-10.750 -0.3543 0.10843 0.10679 -0.0262 1.0000 0.0087
-10.500 -0.3511 0.10534 0.10372 -0.0271 1.0000 0.0088
-8.250 -0.3026 0.06133 0.05962 -0.0706 0.9249 0.0096
-8.000 -0.2928 0.05653 0.05432 -0.0751 0.8316 0.0096
-7.750 -0.2999 0.05375 0.05129 -0.0728 0.7902 0.0098
-7.500 -0.3025 0.05079 0.04813 -0.0707 0.7623 0.0098
-7.250 -0.3020 0.04774 0.04488 -0.0686 0.7401 0.0100
-7.000 -0.2992 0.04399 0.04090 -0.0661 0.7217 0.0105
-6.750 -0.2909 0.03928 0.03586 -0.0631 0.7062 0.0109
-6.500 -0.2825 0.03599 0.03229 -0.0604 0.6905 0.0110
-6.250 -0.2845 0.03109 0.02705 -0.0569 0.6780 0.0112
-6.000 -0.2620 0.01550 0.01158 -0.0527 0.6441 0.0114
-5.750 -0.2472 0.01393 0.00987 -0.0514 0.6325 0.0116
-5.500 -0.2311 0.01243 0.00819 -0.0500 0.6211 0.0118
-5.250 -0.2138 0.01096 0.00653 -0.0487 0.6098 0.0121
-5.000 -0.1957 0.00937 0.00470 -0.0471 0.5995 0.0128
-4.750 -0.1748 0.00831 0.00310 -0.0447 0.5894 0.0140
-4.500 -0.1576 0.00621 0.00088 -0.0438 0.5808 0.0146
-4.250 -0.1340 0.01456 0.00824 -0.0434 0.5838 0.0086
-4.000 -0.1091 0.01337 0.00694 -0.0427 0.5735 0.0080
-3.750 -0.0846 0.01233 0.00576 -0.0419 0.5636 0.0077
-3.500 -0.0604 0.01170 0.00503 -0.0410 0.5538 0.0076
-3.250 -0.0364 0.01120 0.00444 -0.0401 0.5438 0.0075
-3.000 -0.0124 0.01075 0.00391 -0.0393 0.5350 0.0076
-2.750 0.0118 0.01041 0.00348 -0.0384 0.5261 0.0078
-2.500 0.0368 0.01011 0.00314 -0.0378 0.5178 0.0080
-2.250 0.0619 0.00992 0.00287 -0.0372 0.5090 0.0083
-2.000 0.0869 0.00962 0.00254 -0.0365 0.5011 0.0097
-1.750 0.1122 0.00946 0.00233 -0.0360 0.4930 0.0122
-1.500 0.1382 0.00927 0.00214 -0.0355 0.4861 0.0199
-1.250 0.1631 0.00907 0.00203 -0.0350 0.4786 0.0502
-1.000 0.1886 0.00886 0.00195 -0.0345 0.4720 0.0950
-0.750 0.1998 0.00740 0.00172 -0.0321 0.4659 0.4875
-0.500 0.2100 0.00647 0.00180 -0.0286 0.4601 0.8012
-0.250 0.2362 0.00662 0.00193 -0.0279 0.4541 0.8271
0.000 0.2621 0.00680 0.00209 -0.0272 0.4479 0.8422
0.250 0.2883 0.00695 0.00223 -0.0265 0.4421 0.8524
0.500 0.3154 0.00709 0.00232 -0.0262 0.4363 0.8592
0.750 0.3413 0.00721 0.00241 -0.0256 0.4304 0.8655
1.000 0.3677 0.00737 0.00256 -0.0250 0.4257 0.8730
1.250 0.3955 0.00745 0.00258 -0.0250 0.4202 0.8753
1.500 0.4231 0.00753 0.00259 -0.0251 0.4147 0.8762
1.750 0.4511 0.00752 0.00256 -0.0252 0.4106 0.8774
2.000 0.4790 0.00755 0.00256 -0.0253 0.4057 0.8784
2.250 0.5064 0.00762 0.00258 -0.0252 0.4009 0.8795
2.500 0.5339 0.00768 0.00262 -0.0252 0.3966 0.8806
2.750 0.5619 0.00772 0.00265 -0.0253 0.3926 0.8817
3.000 0.5894 0.00779 0.00268 -0.0254 0.3878 0.8827
3.250 0.6164 0.00790 0.00274 -0.0253 0.3831 0.8838
3.500 0.6444 0.00794 0.00279 -0.0255 0.3797 0.8849
3.750 0.6721 0.00800 0.00284 -0.0256 0.3755 0.8860
4.000 0.6993 0.00809 0.00290 -0.0256 0.3712 0.8873
4.250 0.7261 0.00821 0.00299 -0.0255 0.3667 0.8887
4.500 0.7540 0.00825 0.00306 -0.0257 0.3632 0.8899
4.750 0.7815 0.00833 0.00313 -0.0258 0.3592 0.8909
5.000 0.8083 0.00845 0.00321 -0.0257 0.3545 0.8919
5.250 0.8350 0.00853 0.00330 -0.0257 0.3504 0.8932
5.500 0.8623 0.00858 0.00338 -0.0257 0.3467 0.8945
5.750 0.8889 0.00867 0.00347 -0.0257 0.3423 0.8958
6.000 0.9145 0.00882 0.00360 -0.0254 0.3372 0.8972
6.250 0.9416 0.00889 0.00370 -0.0255 0.3336 0.8986
6.500 0.9682 0.00898 0.00381 -0.0254 0.3290 0.9001
6.750 0.9937 0.00913 0.00395 -0.0252 0.3237 0.9019
7.000 1.0201 0.00924 0.00408 -0.0251 0.3191 0.9036
7.250 1.0464 0.00934 0.00421 -0.0251 0.3135 0.9052
7.500 1.0715 0.00952 0.00437 -0.0248 0.3078 0.9068
7.750 1.0976 0.00962 0.00450 -0.0247 0.3026 0.9084
8.000 1.1225 0.00975 0.00465 -0.0244 0.2964 0.9104
8.250 1.1469 0.00991 0.00483 -0.0240 0.2907 0.9124
8.500 1.1717 0.01006 0.00500 -0.0237 0.2835 0.9144
8.750 1.1952 0.01026 0.00521 -0.0232 0.2766 0.9168
9.000 1.2195 0.01043 0.00540 -0.0229 0.2691 0.9192
9.250 1.2425 0.01067 0.00563 -0.0223 0.2608 0.9216
9.500 1.2646 0.01091 0.00587 -0.0216 0.2512 0.9245
9.750 1.2860 0.01115 0.00612 -0.0207 0.2411 0.9278
10.000 1.3063 0.01144 0.00642 -0.0197 0.2312 0.9316
10.250 1.3252 0.01180 0.00675 -0.0184 0.2189 0.9357
10.500 1.3425 0.01218 0.00710 -0.0169 0.2061 0.9403
10.750 1.3579 0.01258 0.00749 -0.0150 0.1936 0.9465
11.000 1.3712 0.01296 0.00786 -0.0128 0.1817 0.9543
11.250 1.3854 0.01340 0.00830 -0.0108 0.1694 0.9661
11.500 1.4099 0.01409 0.00895 -0.0115 0.1541 0.9788
11.750 1.4303 0.01480 0.00963 -0.0113 0.1398 1.0000
12.000 1.4405 0.01551 0.01029 -0.0091 0.1278 1.0000
12.250 1.4495 0.01627 0.01101 -0.0069 0.1167 1.0000
12.500 1.4581 0.01705 0.01178 -0.0047 0.1072 1.0000
12.750 1.4652 0.01794 0.01266 -0.0024 0.0988 1.0000
13.000 1.4692 0.01904 0.01374 -0.0001 0.0901 1.0000
13.250 1.4728 0.02026 0.01496 0.0020 0.0826 1.0000
13.500 1.4771 0.02157 0.01629 0.0037 0.0762 1.0000
13.750 1.4770 0.02331 0.01802 0.0053 0.0690 1.0000
14.000 1.4804 0.02498 0.01973 0.0064 0.0643 1.0000
14.250 1.4799 0.02711 0.02188 0.0073 0.0591 1.0000
14.500 1.4799 0.02937 0.02418 0.0078 0.0544 1.0000
14.750 1.4763 0.03209 0.02692 0.0082 0.0490 1.0000
15.000 1.4741 0.03481 0.02969 0.0083 0.0457 1.0000
15.250 1.4690 0.03790 0.03283 0.0083 0.0426 1.0000
15.500 1.4661 0.04083 0.03583 0.0081 0.0398 1.0000
15.750 1.4563 0.04456 0.03960 0.0078 0.0366 1.0000
16.250 1.4437 0.05152 0.04671 0.0069 0.0327 1.0000
16.500 1.4326 0.05565 0.05089 0.0061 0.0304 1.0000
16.750 1.4247 0.05953 0.05485 0.0054 0.0287 1.0000
17.000 1.4180 0.06335 0.05874 0.0045 0.0273 1.0000
17.250 1.4068 0.06778 0.06322 0.0034 0.0255 1.0000
17.500 1.3973 0.07208 0.06760 0.0023 0.0244 1.0000
17.750 1.3905 0.07612 0.07172 0.0012 0.0235 1.0000
18.000 1.3837 0.08019 0.07586 0.0000 0.0222 1.0000
18.250 1.3733 0.08482 0.08054 -0.0015 0.0208 1.0000
18.500 1.3643 0.08936 0.08516 -0.0030 0.0201 1.0000
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Polar data table (+)
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