EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.26 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e327-il-1000000.txt Download as CSV file: xf-e327-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 327 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3480 0.10299 0.10147 -0.0187 1.0000 0.0086
-11.000 -0.3491 0.09847 0.09696 -0.0203 1.0000 0.0086
-6.000 -0.4394 0.01325 0.00888 -0.0152 0.6742 0.0127
-5.750 -0.4212 0.01223 0.00733 -0.0123 0.6599 0.0143
-4.750 -0.3373 0.01422 0.00776 -0.0080 0.6234 0.0088
-4.500 -0.3116 0.01394 0.00739 -0.0074 0.6096 0.0086
-4.250 -0.2870 0.01284 0.00622 -0.0068 0.5973 0.0084
-4.000 -0.2635 0.01215 0.00545 -0.0058 0.5857 0.0083
-3.750 -0.2407 0.01159 0.00479 -0.0047 0.5739 0.0083
-3.500 -0.2175 0.01117 0.00431 -0.0037 0.5622 0.0083
-3.250 -0.1939 0.01080 0.00387 -0.0028 0.5512 0.0083
-3.000 -0.1700 0.01051 0.00351 -0.0019 0.5412 0.0084
-2.750 -0.1458 0.01023 0.00317 -0.0011 0.5309 0.0086
-2.500 -0.1221 0.00990 0.00278 -0.0002 0.5211 0.0093
-2.250 -0.0972 0.00973 0.00255 0.0005 0.5113 0.0112
-2.000 -0.0732 0.00943 0.00228 0.0013 0.5023 0.0232
-1.750 -0.0502 0.00911 0.00212 0.0022 0.4940 0.0729
-1.500 -0.0272 0.00880 0.00200 0.0031 0.4854 0.1362
-1.250 -0.0112 0.00800 0.00180 0.0050 0.4779 0.3244
-1.000 -0.0173 0.00607 0.00151 0.0114 0.4721 0.7710
-0.750 0.0062 0.00626 0.00179 0.0128 0.4643 0.8296
-0.500 0.0329 0.00643 0.00195 0.0134 0.4571 0.8439
-0.250 0.0598 0.00660 0.00203 0.0138 0.4493 0.8515
0.000 0.0870 0.00674 0.00218 0.0143 0.4424 0.8598
0.250 0.1136 0.00694 0.00232 0.0147 0.4352 0.8673
0.500 0.1407 0.00702 0.00238 0.0151 0.4292 0.8724
0.750 0.1679 0.00717 0.00249 0.0155 0.4226 0.8768
1.000 0.1956 0.00723 0.00250 0.0155 0.4164 0.8787
1.250 0.2239 0.00726 0.00248 0.0153 0.4105 0.8798
1.500 0.2518 0.00731 0.00247 0.0152 0.4045 0.8810
1.750 0.2801 0.00735 0.00247 0.0151 0.3991 0.8821
2.000 0.3083 0.00739 0.00247 0.0149 0.3935 0.8830
2.250 0.3361 0.00747 0.00248 0.0148 0.3878 0.8838
2.500 0.3644 0.00747 0.00248 0.0146 0.3833 0.8848
2.750 0.3922 0.00749 0.00247 0.0145 0.3780 0.8860
3.000 0.4196 0.00756 0.00251 0.0145 0.3727 0.8870
3.250 0.4478 0.00759 0.00254 0.0143 0.3684 0.8879
3.500 0.4758 0.00765 0.00258 0.0142 0.3634 0.8888
3.750 0.5032 0.00774 0.00263 0.0141 0.3583 0.8898
4.000 0.5311 0.00779 0.00269 0.0140 0.3539 0.8908
4.250 0.5590 0.00785 0.00275 0.0139 0.3492 0.8918
4.500 0.5864 0.00794 0.00282 0.0138 0.3443 0.8930
4.750 0.6139 0.00803 0.00290 0.0137 0.3395 0.8943
5.000 0.6418 0.00809 0.00296 0.0136 0.3349 0.8955
5.250 0.6691 0.00819 0.00305 0.0135 0.3297 0.8966
5.500 0.6964 0.00829 0.00315 0.0134 0.3247 0.8977
5.750 0.7242 0.00836 0.00323 0.0132 0.3196 0.8987
6.000 0.7513 0.00848 0.00333 0.0131 0.3141 0.8996
6.250 0.7783 0.00856 0.00343 0.0131 0.3091 0.9008
6.500 0.8054 0.00863 0.00352 0.0130 0.3036 0.9021
6.750 0.8315 0.00877 0.00365 0.0131 0.2972 0.9034
7.000 0.8585 0.00886 0.00377 0.0131 0.2920 0.9047
7.250 0.8848 0.00899 0.00390 0.0132 0.2856 0.9062
7.500 0.9109 0.00913 0.00406 0.0133 0.2791 0.9078
7.750 0.9371 0.00927 0.00421 0.0133 0.2720 0.9094
8.000 0.9628 0.00944 0.00438 0.0134 0.2650 0.9111
8.250 0.9887 0.00960 0.00456 0.0135 0.2569 0.9126
8.500 1.0141 0.00979 0.00475 0.0137 0.2486 0.9142
8.750 1.0388 0.01002 0.00496 0.0139 0.2394 0.9157
9.000 1.0634 0.01020 0.00516 0.0142 0.2299 0.9178
9.250 1.0867 0.01045 0.00541 0.0147 0.2188 0.9198
9.500 1.1094 0.01075 0.00569 0.0153 0.2069 0.9220
9.750 1.1311 0.01110 0.00601 0.0160 0.1925 0.9245
10.000 1.1521 0.01148 0.00635 0.0168 0.1781 0.9272
10.250 1.1722 0.01191 0.00674 0.0177 0.1632 0.9299
10.500 1.1909 0.01234 0.00714 0.0189 0.1495 0.9334
10.750 1.2075 0.01282 0.00759 0.0204 0.1353 0.9375
11.000 1.2234 0.01334 0.00807 0.0220 0.1220 0.9421
11.250 1.2383 0.01385 0.00857 0.0237 0.1106 0.9472
11.500 1.2502 0.01438 0.00909 0.0260 0.0994 0.9543
11.750 1.2594 0.01491 0.00963 0.0288 0.0897 0.9644
12.000 1.2748 0.01564 0.01035 0.0299 0.0789 0.9766
12.250 1.2986 0.01653 0.01121 0.0289 0.0683 0.9869
12.500 1.3157 0.01748 0.01213 0.0289 0.0589 1.0000
12.750 1.3227 0.01827 0.01293 0.0311 0.0534 1.0000
13.000 1.3259 0.01934 0.01399 0.0335 0.0469 1.0000
13.250 1.3290 0.02055 0.01522 0.0354 0.0427 1.0000
13.500 1.3309 0.02198 0.01667 0.0370 0.0376 1.0000
13.750 1.3313 0.02373 0.01844 0.0382 0.0342 1.0000
14.000 1.3356 0.02537 0.02015 0.0389 0.0321 1.0000
14.250 1.3315 0.02785 0.02264 0.0395 0.0276 1.0000
14.500 1.3329 0.03003 0.02489 0.0396 0.0259 1.0000
14.750 1.3287 0.03285 0.02774 0.0396 0.0233 1.0000
15.000 1.3269 0.03554 0.03052 0.0394 0.0219 1.0000
15.250 1.3241 0.03841 0.03345 0.0391 0.0206 1.0000
15.500 1.3154 0.04197 0.03705 0.0385 0.0185 1.0000
15.750 1.3099 0.04524 0.04042 0.0380 0.0180 1.0000
16.000 1.3050 0.04852 0.04379 0.0373 0.0174 1.0000
16.250 1.2976 0.05214 0.04750 0.0365 0.0167 1.0000
16.500 1.2883 0.05611 0.05152 0.0354 0.0156 1.0000
16.750 1.2789 0.06024 0.05572 0.0342 0.0148 1.0000
17.000 1.2714 0.06419 0.05977 0.0329 0.0142 1.0000
17.250 1.2651 0.06810 0.06376 0.0316 0.0137 1.0000
17.500 1.2574 0.07227 0.06801 0.0301 0.0132 1.0000
17.750 1.2479 0.07677 0.07256 0.0285 0.0122 1.0000
18.000 1.2380 0.08140 0.07726 0.0267 0.0115 1.0000
18.250 1.2286 0.08610 0.08205 0.0248 0.0115 1.0000
18.500 1.2225 0.09037 0.08641 0.0230 0.0111 1.0000
18.750 1.2168 0.09464 0.09076 0.0212 0.0105 1.0000
19.000 1.2092 0.09928 0.09547 0.0192 0.0102 1.0000
19.250 1.2007 0.10415 0.10042 0.0169 0.0100 1.0000
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Polar data table (+)
Polar graphs
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