EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 435 AIRFOIL (e435-il) Reynolds number: 100,000 Max Cl/Cd: 44.77 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e435-il-100000-n5.txt Download as CSV file: xf-e435-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 435 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2033 0.07523 0.07019 -0.1124 0.9326 0.0192
-9.750 -0.2083 0.06811 0.06299 -0.1194 0.9266 0.0189
-9.500 -0.2229 0.06118 0.05590 -0.1260 0.9181 0.0187
-9.250 -0.2387 0.05589 0.05040 -0.1303 0.9089 0.0186
-9.000 -0.2488 0.05194 0.04622 -0.1328 0.9004 0.0184
-8.750 -0.2633 0.04896 0.04300 -0.1322 0.8893 0.0183
-8.500 -0.2632 0.04502 0.03864 -0.1337 0.8835 0.0183
-8.250 -0.2687 0.04262 0.03594 -0.1315 0.8743 0.0183
-8.000 -0.2583 0.03951 0.03237 -0.1318 0.8693 0.0185
-7.750 -0.2474 0.03650 0.02876 -0.1313 0.8640 0.0194
-7.500 -0.2357 0.03539 0.02754 -0.1299 0.8573 0.0200
-7.250 -0.2126 0.03387 0.02580 -0.1305 0.8537 0.0213
-7.000 -0.1855 0.03172 0.02320 -0.1313 0.8511 0.0226
-6.750 -0.1732 0.03047 0.02170 -0.1290 0.8446 0.0233
-6.500 -0.1518 0.02929 0.02045 -0.1285 0.8400 0.0241
-6.250 -0.1245 0.02802 0.01904 -0.1288 0.8371 0.0255
-6.000 -0.0948 0.02676 0.01757 -0.1293 0.8348 0.0276
-5.750 -0.0832 0.02632 0.01717 -0.1271 0.8283 0.0299
-5.500 -0.0621 0.02558 0.01635 -0.1264 0.8238 0.0337
-5.250 -0.0348 0.02468 0.01535 -0.1267 0.8207 0.0383
-5.000 -0.0050 0.02379 0.01447 -0.1277 0.8184 0.0468
-4.750 0.0075 0.02345 0.01417 -0.1255 0.8122 0.0561
-4.500 0.0292 0.02286 0.01363 -0.1250 0.8076 0.0749
-4.250 0.0579 0.02201 0.01296 -0.1260 0.8046 0.1146
-4.000 0.0896 0.02079 0.01223 -0.1282 0.8024 0.2156
-3.750 0.1081 0.01975 0.01224 -0.1281 0.7976 0.4202
-3.500 0.1242 0.02019 0.01300 -0.1253 0.7921 0.5433
-3.250 0.1537 0.02051 0.01317 -0.1252 0.7889 0.5918
-3.000 0.1836 0.02087 0.01339 -0.1248 0.7865 0.6197
-2.750 0.2104 0.02120 0.01356 -0.1243 0.7833 0.6407
-2.500 0.2191 0.02182 0.01417 -0.1204 0.7763 0.6539
-2.250 0.2429 0.02218 0.01444 -0.1190 0.7728 0.6719
-2.000 0.2697 0.02243 0.01460 -0.1179 0.7703 0.6875
-1.750 0.3018 0.02244 0.01447 -0.1182 0.7684 0.6977
-1.500 0.3051 0.02299 0.01501 -0.1143 0.7599 0.7044
-1.250 0.3361 0.02294 0.01480 -0.1153 0.7566 0.7107
-1.000 0.3676 0.02283 0.01460 -0.1159 0.7542 0.7145
-0.750 0.4034 0.02266 0.01430 -0.1175 0.7523 0.7187
-0.500 0.4096 0.02322 0.01483 -0.1145 0.7438 0.7239
-0.250 0.4398 0.02318 0.01469 -0.1153 0.7404 0.7275
0.000 0.4727 0.02304 0.01448 -0.1162 0.7379 0.7306
0.250 0.5091 0.02287 0.01421 -0.1179 0.7360 0.7339
0.500 0.5121 0.02354 0.01491 -0.1144 0.7269 0.7380
0.750 0.5458 0.02348 0.01476 -0.1159 0.7236 0.7422
1.000 0.5798 0.02331 0.01455 -0.1170 0.7212 0.7450
1.500 0.6145 0.02392 0.01516 -0.1142 0.7092 0.7516
1.750 0.6494 0.02377 0.01497 -0.1157 0.7062 0.7554
2.000 0.6891 0.02354 0.01469 -0.1180 0.7040 0.7593
2.250 0.6876 0.02430 0.01552 -0.1134 0.6946 0.7628
2.500 0.7188 0.02421 0.01544 -0.1141 0.6909 0.7661
2.750 0.7575 0.02395 0.01516 -0.1161 0.6884 0.7695
3.250 0.7905 0.02458 0.01585 -0.1131 0.6751 0.7779
3.500 0.8291 0.02426 0.01555 -0.1149 0.6724 0.7815
3.750 0.8292 0.02501 0.01638 -0.1107 0.6628 0.7864
4.000 0.8637 0.02481 0.01619 -0.1120 0.6586 0.7906
4.250 0.9050 0.02438 0.01577 -0.1142 0.6558 0.7941
4.500 0.9007 0.02528 0.01679 -0.1094 0.6452 0.7991
4.750 0.9383 0.02488 0.01642 -0.1109 0.6414 0.8040
5.250 0.9750 0.02535 0.01704 -0.1082 0.6270 0.8145
5.500 1.0182 0.02470 0.01643 -0.1105 0.6234 0.8195
5.750 1.0160 0.02569 0.01752 -0.1063 0.6121 0.8259
6.000 1.0568 0.02500 0.01690 -0.1080 0.6079 0.8312
6.250 1.0571 0.02594 0.01795 -0.1043 0.5964 0.8393
6.500 1.0894 0.02549 0.01757 -0.1047 0.5904 0.8460
6.750 1.0980 0.02609 0.01828 -0.1021 0.5796 0.8551
7.000 1.1120 0.02639 0.01870 -0.1001 0.5700 0.8642
7.250 1.1401 0.02610 0.01848 -0.0999 0.5617 0.8740
7.500 1.1463 0.02675 0.01925 -0.0970 0.5499 0.8883
7.750 1.1637 0.02680 0.01942 -0.0954 0.5395 0.9077
8.000 1.1846 0.02646 0.01918 -0.0941 0.5291 0.9717
8.250 1.2011 0.02713 0.01991 -0.0933 0.5154 1.0000
8.500 1.2202 0.02769 0.02053 -0.0928 0.5017 1.0000
8.750 1.2402 0.02817 0.02104 -0.0923 0.4876 1.0000
9.000 1.2592 0.02870 0.02159 -0.0916 0.4725 1.0000
9.250 1.2764 0.02933 0.02222 -0.0907 0.4567 1.0000
9.500 1.2921 0.03004 0.02295 -0.0896 0.4401 1.0000
9.750 1.3061 0.03087 0.02376 -0.0884 0.4227 1.0000
10.000 1.3189 0.03180 0.02467 -0.0871 0.4052 1.0000
10.250 1.3303 0.03284 0.02569 -0.0857 0.3876 1.0000
10.500 1.3403 0.03401 0.02683 -0.0842 0.3700 1.0000
10.750 1.3481 0.03536 0.02818 -0.0826 0.3525 1.0000
11.000 1.3547 0.03685 0.02966 -0.0811 0.3351 1.0000
11.250 1.3607 0.03843 0.03124 -0.0795 0.3182 1.0000
11.500 1.3658 0.04013 0.03294 -0.0781 0.3016 1.0000
11.750 1.3704 0.04192 0.03473 -0.0766 0.2854 1.0000
12.000 1.3741 0.04384 0.03666 -0.0753 0.2694 1.0000
12.250 1.3774 0.04587 0.03869 -0.0740 0.2540 1.0000
12.500 1.3801 0.04801 0.04084 -0.0728 0.2391 1.0000
12.750 1.3823 0.05028 0.04311 -0.0718 0.2247 1.0000
13.000 1.3838 0.05268 0.04553 -0.0708 0.2109 1.0000
13.250 1.3845 0.05523 0.04808 -0.0699 0.1976 1.0000
13.500 1.3856 0.05785 0.05074 -0.0692 0.1848 1.0000
13.750 1.3866 0.06056 0.05351 -0.0686 0.1724 1.0000
14.000 1.3870 0.06340 0.05640 -0.0681 0.1608 1.0000
14.250 1.3867 0.06641 0.05944 -0.0677 0.1502 1.0000
14.750 1.3850 0.07279 0.06594 -0.0673 0.1302 1.0000
15.000 1.3840 0.07612 0.06934 -0.0674 0.1213 1.0000
15.250 1.3805 0.07982 0.07305 -0.0675 0.1134 1.0000
15.500 1.3801 0.08327 0.07662 -0.0678 0.1052 1.0000
15.750 1.3770 0.08709 0.08049 -0.0683 0.0984 1.0000
16.000 1.3747 0.09091 0.08442 -0.0689 0.0916 1.0000
16.250 1.3716 0.09487 0.08844 -0.0696 0.0858 1.0000
16.500 1.3688 0.09889 0.09257 -0.0705 0.0801 1.0000
16.750 1.3650 0.10307 0.09680 -0.0716 0.0753 1.0000
17.000 1.3627 0.10715 0.10104 -0.0727 0.0703 1.0000
17.500 1.3563 0.11562 0.10970 -0.0754 0.0620 1.0000
17.750 1.3523 0.12006 0.11422 -0.0771 0.0586 1.0000
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Polar data table (+)
Polar graphs
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