EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 500,000 Max Cl/Cd: 81.35 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e327-il-500000-n5.txt Download as CSV file: xf-e327-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3592 0.08687 0.08479 -0.0231 1.0000 0.0075
-10.000 -0.3669 0.08122 0.07916 -0.0252 1.0000 0.0073
-9.750 -0.3789 0.07475 0.07271 -0.0279 1.0000 0.0071
-9.500 -0.3942 0.06780 0.06578 -0.0318 1.0000 0.0071
-9.000 -0.5540 0.06100 0.05861 -0.0333 1.0000 0.0065
-8.500 -0.5786 0.05273 0.05007 -0.0275 0.9887 0.0063
-8.250 -0.5524 0.04505 0.04197 -0.0339 0.9083 0.0062
-8.000 -0.5571 0.03762 0.03388 -0.0310 0.8411 0.0064
-7.750 -0.5526 0.03547 0.03138 -0.0280 0.8005 0.0066
-7.500 -0.5562 0.02983 0.02510 -0.0231 0.7754 0.0065
-7.000 -0.5315 0.02490 0.01926 -0.0178 0.7307 0.0063
-6.750 -0.5152 0.02289 0.01688 -0.0158 0.7114 0.0062
-6.500 -0.4958 0.02130 0.01496 -0.0143 0.6931 0.0062
-6.250 -0.4743 0.01986 0.01321 -0.0131 0.6767 0.0062
-6.000 -0.4513 0.01868 0.01178 -0.0122 0.6609 0.0062
-5.750 -0.4273 0.01762 0.01048 -0.0114 0.6457 0.0062
-5.500 -0.4030 0.01672 0.00940 -0.0106 0.6322 0.0062
-5.250 -0.3788 0.01602 0.00855 -0.0099 0.6194 0.0062
-5.000 -0.3548 0.01536 0.00776 -0.0091 0.6064 0.0063
-4.750 -0.3314 0.01473 0.00701 -0.0082 0.5936 0.0063
-4.500 -0.3090 0.01405 0.00624 -0.0072 0.5817 0.0065
-4.250 -0.2859 0.01359 0.00571 -0.0062 0.5713 0.0066
-4.000 -0.2629 0.01320 0.00524 -0.0053 0.5603 0.0068
-3.750 -0.2394 0.01284 0.00482 -0.0044 0.5495 0.0072
-3.500 -0.2156 0.01255 0.00446 -0.0036 0.5393 0.0074
-3.250 -0.1917 0.01229 0.00412 -0.0028 0.5294 0.0078
-3.000 -0.1673 0.01205 0.00382 -0.0021 0.5204 0.0083
-2.750 -0.1434 0.01181 0.00351 -0.0012 0.5113 0.0097
-2.500 -0.1188 0.01161 0.00326 -0.0006 0.5020 0.0115
-2.250 -0.0946 0.01140 0.00304 0.0002 0.4936 0.0179
-2.000 -0.0708 0.01115 0.00286 0.0009 0.4855 0.0381
-1.750 -0.0475 0.01088 0.00271 0.0018 0.4781 0.0755
-1.500 -0.0270 0.01040 0.00255 0.0030 0.4702 0.1682
-1.000 -0.0226 0.00790 0.00242 0.0130 0.4587 0.8096
-0.750 0.0035 0.00804 0.00249 0.0136 0.4517 0.8258
-0.500 0.0296 0.00818 0.00256 0.0143 0.4453 0.8389
-0.250 0.0551 0.00838 0.00270 0.0151 0.4381 0.8517
0.000 0.0818 0.00857 0.00285 0.0157 0.4316 0.8595
0.250 0.1078 0.00870 0.00292 0.0163 0.4255 0.8669
0.500 0.1349 0.00876 0.00289 0.0164 0.4195 0.8693
0.750 0.1629 0.00878 0.00286 0.0164 0.4135 0.8703
1.000 0.1906 0.00883 0.00285 0.0164 0.4073 0.8714
1.250 0.2181 0.00888 0.00283 0.0164 0.4021 0.8724
1.500 0.2460 0.00892 0.00283 0.0163 0.3968 0.8734
1.750 0.2736 0.00897 0.00283 0.0163 0.3911 0.8746
2.000 0.3009 0.00904 0.00285 0.0163 0.3860 0.8760
2.250 0.3287 0.00908 0.00287 0.0163 0.3811 0.8772
2.500 0.3561 0.00915 0.00289 0.0162 0.3757 0.8783
2.750 0.3834 0.00922 0.00292 0.0162 0.3710 0.8795
3.000 0.4111 0.00927 0.00296 0.0161 0.3663 0.8807
3.250 0.4385 0.00934 0.00300 0.0161 0.3613 0.8819
3.500 0.4655 0.00944 0.00306 0.0161 0.3565 0.8833
3.750 0.4931 0.00950 0.00312 0.0160 0.3521 0.8845
4.000 0.5204 0.00957 0.00319 0.0160 0.3472 0.8855
4.250 0.5472 0.00968 0.00327 0.0160 0.3424 0.8865
4.500 0.5744 0.00976 0.00337 0.0160 0.3381 0.8875
4.750 0.6015 0.00985 0.00347 0.0160 0.3331 0.8886
5.000 0.6281 0.00997 0.00357 0.0161 0.3282 0.8898
5.250 0.6549 0.01007 0.00370 0.0161 0.3236 0.8911
5.500 0.6818 0.01017 0.00382 0.0161 0.3185 0.8924
5.750 0.7081 0.01030 0.00394 0.0162 0.3131 0.8938
6.000 0.7347 0.01042 0.00409 0.0162 0.3081 0.8954
6.250 0.7612 0.01054 0.00423 0.0163 0.3024 0.8971
6.750 0.8135 0.01083 0.00454 0.0164 0.2906 0.9000
7.000 0.8390 0.01098 0.00472 0.0166 0.2842 0.9013
7.250 0.8644 0.01114 0.00490 0.0168 0.2781 0.9027
7.500 0.8895 0.01131 0.00510 0.0171 0.2703 0.9042
7.750 0.9144 0.01149 0.00531 0.0174 0.2636 0.9059
8.000 0.9389 0.01170 0.00553 0.0177 0.2551 0.9078
8.250 0.9633 0.01191 0.00578 0.0180 0.2468 0.9097
8.500 0.9867 0.01217 0.00604 0.0185 0.2379 0.9118
8.750 1.0104 0.01243 0.00631 0.0189 0.2274 0.9140
9.000 1.0331 0.01270 0.00661 0.0194 0.2176 0.9162
9.250 1.0543 0.01303 0.00695 0.0203 0.2063 0.9187
9.500 1.0746 0.01339 0.00731 0.0212 0.1949 0.9215
9.750 1.0941 0.01380 0.00771 0.0222 0.1820 0.9247
10.000 1.1126 0.01426 0.00816 0.0234 0.1686 0.9281
10.500 1.1448 0.01529 0.00917 0.0264 0.1416 0.9360
10.750 1.1581 0.01588 0.00974 0.0283 0.1280 0.9416
11.000 1.1684 0.01648 0.01035 0.0307 0.1156 0.9485
11.250 1.1793 0.01716 0.01103 0.0328 0.1044 0.9577
11.500 1.1954 0.01797 0.01185 0.0335 0.0933 0.9675
11.750 1.2155 0.01887 0.01278 0.0331 0.0834 0.9786
12.000 1.2362 0.01990 0.01384 0.0322 0.0746 1.0000
12.250 1.2396 0.02097 0.01492 0.0344 0.0683 1.0000
12.500 1.2445 0.02211 0.01609 0.0361 0.0628 1.0000
12.750 1.2464 0.02360 0.01761 0.0375 0.0573 1.0000
13.000 1.2492 0.02522 0.01927 0.0386 0.0527 1.0000
13.250 1.2498 0.02718 0.02127 0.0393 0.0485 1.0000
13.500 1.2509 0.02927 0.02342 0.0396 0.0447 1.0000
13.750 1.2486 0.03182 0.02602 0.0398 0.0412 1.0000
14.000 1.2489 0.03423 0.02851 0.0397 0.0385 1.0000
14.250 1.2457 0.03708 0.03143 0.0395 0.0358 1.0000
14.500 1.2409 0.04019 0.03461 0.0391 0.0335 1.0000
14.750 1.2378 0.04318 0.03768 0.0386 0.0316 1.0000
15.000 1.2314 0.04658 0.04115 0.0379 0.0295 1.0000
15.500 1.2177 0.05371 0.04843 0.0363 0.0261 1.0000
15.750 1.2115 0.05735 0.05216 0.0353 0.0252 1.0000
16.000 1.2036 0.06132 0.05620 0.0341 0.0237 1.0000
16.500 1.1900 0.06930 0.06434 0.0315 0.0215 1.0000
16.750 1.1835 0.07336 0.06849 0.0300 0.0203 1.0000
17.000 1.1763 0.07761 0.07282 0.0284 0.0194 1.0000
17.250 1.1681 0.08211 0.07738 0.0266 0.0185 1.0000
17.500 1.1619 0.08641 0.08176 0.0249 0.0177 1.0000
17.750 1.1564 0.09065 0.08609 0.0231 0.0166 1.0000
18.000 1.1474 0.09548 0.09096 0.0210 0.0149 1.0000
18.250 1.1436 0.09966 0.09526 0.0192 0.0153 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 327 AIRFOIL (e327-il)