EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 500,000 Max Cl/Cd: 109.23 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e431-il-500000-n5.txt Download as CSV file: xf-e431-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 431 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0256 0.08862 0.08569 -0.1125 0.8527 0.0073
-11.500 -0.1110 0.09579 0.09310 -0.1099 0.9199 0.0074
-11.250 -0.0902 0.09127 0.08850 -0.1165 0.9082 0.0072
-11.000 -0.0757 0.08648 0.08362 -0.1220 0.8927 0.0070
-10.750 -0.0699 0.08183 0.07888 -0.1258 0.8751 0.0067
-10.250 -0.1124 0.06423 0.06116 -0.1335 0.8442 0.0054
-10.000 -0.1298 0.05636 0.05326 -0.1390 0.8319 0.0053
-9.500 -0.1940 0.04146 0.03797 -0.1443 0.8092 0.0051
-9.250 -0.2236 0.03716 0.03344 -0.1413 0.8002 0.0051
-9.000 -0.2530 0.03281 0.02875 -0.1368 0.7917 0.0050
-8.750 -0.2650 0.02894 0.02446 -0.1336 0.7857 0.0049
-8.500 -0.2677 0.02544 0.02051 -0.1308 0.7802 0.0048
-8.250 -0.2591 0.02307 0.01775 -0.1288 0.7753 0.0048
-8.000 -0.2455 0.02114 0.01546 -0.1273 0.7710 0.0048
-7.750 -0.2279 0.01966 0.01371 -0.1262 0.7669 0.0048
-7.500 -0.2084 0.01839 0.01220 -0.1253 0.7628 0.0048
-7.250 -0.1871 0.01742 0.01104 -0.1245 0.7591 0.0048
-7.000 -0.1652 0.01651 0.00994 -0.1238 0.7556 0.0049
-6.750 -0.1424 0.01578 0.00909 -0.1232 0.7521 0.0049
-6.500 -0.1193 0.01510 0.00831 -0.1227 0.7483 0.0050
-6.250 -0.0959 0.01447 0.00757 -0.1222 0.7449 0.0052
-6.000 -0.0720 0.01396 0.00696 -0.1217 0.7416 0.0053
-5.500 -0.0231 0.01302 0.00588 -0.1210 0.7352 0.0056
-5.250 0.0018 0.01260 0.00542 -0.1208 0.7318 0.0060
-5.000 0.0274 0.01227 0.00505 -0.1206 0.7285 0.0064
-4.750 0.0533 0.01198 0.00469 -0.1204 0.7253 0.0071
-4.250 0.1058 0.01144 0.00407 -0.1202 0.7193 0.0090
-4.000 0.1323 0.01120 0.00380 -0.1202 0.7161 0.0111
-3.750 0.1589 0.01097 0.00357 -0.1202 0.7127 0.0157
-3.500 0.1853 0.01069 0.00337 -0.1202 0.7096 0.0317
-3.250 0.2121 0.01044 0.00319 -0.1203 0.7067 0.0558
-3.000 0.2388 0.01014 0.00304 -0.1205 0.7036 0.0936
-2.750 0.2653 0.00977 0.00290 -0.1207 0.7001 0.1547
-2.500 0.2919 0.00934 0.00275 -0.1210 0.6968 0.2445
-2.250 0.3188 0.00885 0.00259 -0.1215 0.6936 0.3568
-1.750 0.3730 0.00788 0.00254 -0.1222 0.6874 0.6526
-1.500 0.4009 0.00790 0.00260 -0.1223 0.6838 0.6850
-1.250 0.4289 0.00795 0.00262 -0.1223 0.6802 0.7024
-1.000 0.4573 0.00802 0.00262 -0.1225 0.6769 0.7145
-0.750 0.4854 0.00810 0.00267 -0.1226 0.6735 0.7279
-0.500 0.5128 0.00820 0.00279 -0.1225 0.6697 0.7451
-0.250 0.5395 0.00830 0.00291 -0.1221 0.6656 0.7563
0.000 0.5679 0.00837 0.00291 -0.1224 0.6617 0.7620
0.250 0.5957 0.00841 0.00291 -0.1225 0.6579 0.7640
0.500 0.6234 0.00843 0.00293 -0.1226 0.6535 0.7659
0.750 0.6510 0.00847 0.00295 -0.1227 0.6489 0.7680
1.000 0.6786 0.00852 0.00296 -0.1228 0.6445 0.7700
1.250 0.7063 0.00856 0.00299 -0.1229 0.6399 0.7721
1.500 0.7338 0.00861 0.00302 -0.1230 0.6346 0.7744
1.750 0.7612 0.00867 0.00304 -0.1231 0.6295 0.7767
2.250 0.8153 0.00877 0.00313 -0.1232 0.6182 0.7803
2.500 0.8416 0.00885 0.00318 -0.1230 0.6124 0.7820
2.750 0.8682 0.00890 0.00327 -0.1230 0.6059 0.7839
3.000 0.8940 0.00899 0.00333 -0.1227 0.5990 0.7861
3.250 0.9202 0.00907 0.00342 -0.1226 0.5920 0.7884
3.500 0.9457 0.00917 0.00350 -0.1223 0.5843 0.7907
3.750 0.9714 0.00927 0.00360 -0.1221 0.5765 0.7929
4.000 0.9963 0.00940 0.00370 -0.1218 0.5678 0.7950
4.250 1.0208 0.00950 0.00382 -0.1213 0.5586 0.7968
4.500 1.0440 0.00964 0.00396 -0.1206 0.5485 0.7988
4.750 1.0667 0.00980 0.00411 -0.1198 0.5370 0.8011
5.000 1.0890 0.00997 0.00427 -0.1189 0.5243 0.8037
5.250 1.1105 0.01017 0.00445 -0.1179 0.5113 0.8064
5.500 1.1309 0.01039 0.00464 -0.1167 0.4971 0.8090
5.750 1.1497 0.01064 0.00486 -0.1152 0.4821 0.8115
6.000 1.1654 0.01090 0.00509 -0.1130 0.4661 0.8138
6.250 1.1802 0.01120 0.00537 -0.1108 0.4497 0.8165
6.500 1.1944 0.01157 0.00569 -0.1084 0.4321 0.8195
6.750 1.2074 0.01200 0.00607 -0.1060 0.4137 0.8229
7.000 1.2197 0.01249 0.00649 -0.1034 0.3949 0.8265
7.250 1.2320 0.01297 0.00694 -0.1009 0.3764 0.8296
7.500 1.2429 0.01351 0.00744 -0.0983 0.3571 0.8331
7.750 1.2532 0.01412 0.00800 -0.0957 0.3379 0.8368
8.000 1.2634 0.01478 0.00860 -0.0931 0.3198 0.8408
8.250 1.2732 0.01547 0.00926 -0.0906 0.3028 0.8445
8.500 1.2824 0.01621 0.00996 -0.0881 0.2852 0.8487
8.750 1.2910 0.01703 0.01074 -0.0856 0.2670 0.8537
9.250 1.3083 0.01878 0.01245 -0.0810 0.2345 0.8641
9.500 1.3166 0.01974 0.01339 -0.0788 0.2189 0.8701
9.750 1.3251 0.02072 0.01436 -0.0767 0.2046 0.8763
10.000 1.3317 0.02182 0.01543 -0.0744 0.1887 0.8839
10.250 1.3392 0.02290 0.01651 -0.0723 0.1753 0.8927
10.750 1.3515 0.02518 0.01882 -0.0680 0.1499 0.9251
11.000 1.3586 0.02644 0.02008 -0.0664 0.1357 1.0000
11.250 1.3666 0.02783 0.02144 -0.0651 0.1238 1.0000
11.500 1.3743 0.02929 0.02287 -0.0637 0.1126 1.0000
11.750 1.3826 0.03071 0.02429 -0.0625 0.1025 1.0000
12.000 1.3908 0.03219 0.02576 -0.0614 0.0931 1.0000
12.250 1.3980 0.03378 0.02734 -0.0602 0.0846 1.0000
12.500 1.4044 0.03547 0.02902 -0.0591 0.0766 1.0000
12.750 1.4120 0.03711 0.03067 -0.0581 0.0689 1.0000
13.000 1.4188 0.03884 0.03242 -0.0572 0.0626 1.0000
13.250 1.4243 0.04075 0.03432 -0.0563 0.0561 1.0000
13.500 1.4305 0.04263 0.03623 -0.0554 0.0499 1.0000
13.750 1.4361 0.04461 0.03823 -0.0547 0.0448 1.0000
14.250 1.4463 0.04882 0.04250 -0.0534 0.0359 1.0000
14.500 1.4504 0.05111 0.04482 -0.0529 0.0321 1.0000
14.750 1.4557 0.05332 0.04708 -0.0524 0.0293 1.0000
15.000 1.4592 0.05577 0.04957 -0.0521 0.0263 1.0000
15.250 1.4629 0.05826 0.05212 -0.0518 0.0239 1.0000
15.500 1.4664 0.06083 0.05476 -0.0516 0.0219 1.0000
15.750 1.4695 0.06351 0.05750 -0.0516 0.0199 1.0000
16.000 1.4712 0.06639 0.06045 -0.0516 0.0181 1.0000
16.250 1.4731 0.06931 0.06344 -0.0517 0.0161 1.0000
16.500 1.4741 0.07242 0.06662 -0.0519 0.0150 1.0000
16.750 1.4755 0.07554 0.06982 -0.0523 0.0135 1.0000
17.000 1.4753 0.07894 0.07330 -0.0527 0.0125 1.0000
17.250 1.4754 0.08233 0.07677 -0.0533 0.0111 1.0000
17.500 1.4747 0.08591 0.08045 -0.0540 0.0104 1.0000
17.750 1.4726 0.08977 0.08439 -0.0549 0.0097 1.0000
18.000 1.4717 0.09350 0.08823 -0.0558 0.0090 1.0000
18.250 1.4697 0.09746 0.09230 -0.0570 0.0082 1.0000
18.500 1.4660 0.10173 0.09665 -0.0583 0.0076 1.0000
18.750 1.4634 0.10587 0.10091 -0.0597 0.0072 1.0000
19.000 1.4601 0.11018 0.10532 -0.0612 0.0067 1.0000
19.250 1.4561 0.11466 0.10991 -0.0629 0.0062 1.0000
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Polar data table (+)
Polar graphs
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