EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 100,000 Max Cl/Cd: 45.86 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e403-il-100000-n5.txt Download as CSV file: xf-e403-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 403 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5564 0.09191 0.08701 -0.0571 0.9971 0.0222
-10.750 -0.5842 0.08247 0.07742 -0.0641 0.9946 0.0218
-10.500 -0.6083 0.07592 0.07072 -0.0680 0.9915 0.0216
-10.250 -0.6317 0.07042 0.06502 -0.0705 0.9883 0.0213
-10.000 -0.6517 0.06558 0.05992 -0.0727 0.9849 0.0210
-9.750 -0.6738 0.06231 0.05646 -0.0716 0.9801 0.0209
-9.500 -0.6890 0.05938 0.05332 -0.0710 0.9758 0.0209
-9.250 -0.6941 0.05558 0.04916 -0.0719 0.9720 0.0208
-9.000 -0.6967 0.05296 0.04629 -0.0706 0.9679 0.0210
-8.750 -0.6909 0.05028 0.04331 -0.0704 0.9645 0.0214
-8.500 -0.6782 0.04759 0.04028 -0.0710 0.9617 0.0220
-8.250 -0.6609 0.04494 0.03724 -0.0718 0.9596 0.0227
-8.000 -0.6512 0.04279 0.03476 -0.0703 0.9565 0.0231
-7.750 -0.6352 0.04069 0.03235 -0.0695 0.9536 0.0233
-7.500 -0.6148 0.03878 0.03015 -0.0691 0.9512 0.0235
-7.250 -0.5921 0.03710 0.02820 -0.0687 0.9492 0.0239
-7.000 -0.5682 0.03571 0.02661 -0.0685 0.9476 0.0242
-6.750 -0.5425 0.03450 0.02526 -0.0685 0.9461 0.0247
-6.500 -0.5236 0.03335 0.02412 -0.0675 0.9434 0.0254
-6.250 -0.5067 0.03241 0.02316 -0.0663 0.9402 0.0262
-6.000 -0.4853 0.03155 0.02224 -0.0660 0.9374 0.0276
-5.750 -0.4602 0.03077 0.02135 -0.0664 0.9349 0.0297
-5.500 -0.4332 0.02986 0.02040 -0.0674 0.9329 0.0321
-5.250 -0.4033 0.02907 0.01954 -0.0689 0.9312 0.0349
-5.000 -0.3828 0.02840 0.01872 -0.0684 0.9276 0.0379
-4.750 -0.3582 0.02761 0.01792 -0.0689 0.9243 0.0443
-4.500 -0.3286 0.02657 0.01711 -0.0707 0.9219 0.0775
-4.250 -0.2877 0.02380 0.01586 -0.0776 0.9211 0.3450
-4.000 -0.2643 0.02466 0.01766 -0.0755 0.9182 0.5469
-3.750 -0.2364 0.02597 0.01887 -0.0743 0.9157 0.5906
-3.500 -0.2242 0.02671 0.01956 -0.0705 0.9099 0.6071
-3.250 -0.2020 0.02749 0.02023 -0.0685 0.9060 0.6224
-3.000 -0.1710 0.02787 0.02043 -0.0691 0.9034 0.6353
-2.750 -0.1417 0.02819 0.02065 -0.0688 0.9012 0.6393
-2.500 -0.1259 0.02823 0.02058 -0.0669 0.8951 0.6441
-2.250 -0.0912 0.02804 0.02019 -0.0695 0.8917 0.6513
-2.000 -0.0617 0.02811 0.02017 -0.0698 0.8888 0.6540
-1.750 -0.0282 0.02815 0.02010 -0.0711 0.8866 0.6573
-1.500 -0.0086 0.02811 0.01998 -0.0703 0.8801 0.6614
-1.250 0.0270 0.02794 0.01966 -0.0729 0.8765 0.6669
-1.000 0.0589 0.02793 0.01959 -0.0738 0.8734 0.6692
-0.750 0.0863 0.02793 0.01955 -0.0740 0.8691 0.6719
-0.500 0.1106 0.02792 0.01949 -0.0739 0.8629 0.6753
-0.250 0.1462 0.02780 0.01930 -0.0759 0.8595 0.6790
0.000 0.1870 0.02762 0.01903 -0.0791 0.8572 0.6832
0.250 0.2035 0.02768 0.01910 -0.0773 0.8485 0.6855
0.500 0.2372 0.02755 0.01897 -0.0785 0.8447 0.6880
0.750 0.2641 0.02750 0.01891 -0.0788 0.8385 0.6910
1.000 0.2949 0.02737 0.01878 -0.0798 0.8324 0.6945
1.250 0.3358 0.02709 0.01847 -0.0827 0.8291 0.6986
1.500 0.3555 0.02711 0.01853 -0.0815 0.8199 0.7007
1.750 0.3901 0.02683 0.01829 -0.0826 0.8155 0.7030
2.000 0.4136 0.02679 0.01830 -0.0821 0.8066 0.7059
2.250 0.4487 0.02648 0.01803 -0.0836 0.8014 0.7092
2.500 0.4771 0.02637 0.01796 -0.0841 0.7929 0.7128
2.750 0.5110 0.02603 0.01768 -0.0853 0.7869 0.7154
3.000 0.5352 0.02592 0.01766 -0.0847 0.7776 0.7178
3.250 0.5683 0.02548 0.01732 -0.0854 0.7715 0.7205
3.500 0.5932 0.02535 0.01728 -0.0850 0.7607 0.7238
3.750 0.6308 0.02472 0.01672 -0.0864 0.7551 0.7271
4.000 0.6569 0.02455 0.01665 -0.0863 0.7424 0.7302
4.250 0.6818 0.02429 0.01651 -0.0855 0.7297 0.7325
4.500 0.7095 0.02396 0.01629 -0.0852 0.7168 0.7354
4.750 0.7400 0.02357 0.01603 -0.0854 0.7029 0.7385
5.000 0.7730 0.02314 0.01569 -0.0860 0.6871 0.7419
5.250 0.8100 0.02261 0.01523 -0.0873 0.6687 0.7452
5.500 0.8481 0.02193 0.01463 -0.0883 0.6469 0.7475
5.750 0.8863 0.02140 0.01411 -0.0894 0.6172 0.7504
6.000 0.9228 0.02113 0.01381 -0.0905 0.5803 0.7535
6.250 0.9567 0.02115 0.01371 -0.0914 0.5401 0.7570
6.500 0.9846 0.02147 0.01391 -0.0915 0.5002 0.7606
6.750 1.0052 0.02192 0.01427 -0.0903 0.4635 0.7631
7.000 1.0233 0.02249 0.01476 -0.0888 0.4281 0.7661
7.250 1.0400 0.02316 0.01535 -0.0872 0.3925 0.7697
7.500 1.0559 0.02393 0.01601 -0.0856 0.3565 0.7737
7.750 1.0699 0.02477 0.01674 -0.0838 0.3212 0.7772
8.000 1.0815 0.02565 0.01754 -0.0816 0.2867 0.7803
8.250 1.0931 0.02664 0.01841 -0.0796 0.2494 0.7837
8.500 1.1038 0.02779 0.01937 -0.0777 0.2113 0.7875
8.750 1.1143 0.02909 0.02044 -0.0760 0.1688 0.7916
9.000 1.1232 0.03039 0.02153 -0.0739 0.1309 0.7950
9.250 1.1338 0.03170 0.02271 -0.0722 0.1018 0.7989
9.500 1.1450 0.03308 0.02403 -0.0706 0.0778 0.8032
9.750 1.1545 0.03467 0.02553 -0.0689 0.0582 0.8071
10.000 1.1616 0.03630 0.02718 -0.0667 0.0460 0.8107
10.250 1.1676 0.03810 0.02900 -0.0646 0.0389 0.8150
10.500 1.1752 0.03984 0.03087 -0.0628 0.0341 0.8197
10.750 1.1800 0.04173 0.03285 -0.0608 0.0312 0.8241
11.000 1.1862 0.04348 0.03481 -0.0590 0.0288 0.8289
11.250 1.1918 0.04541 0.03688 -0.0574 0.0272 0.8342
11.500 1.1947 0.04756 0.03916 -0.0557 0.0261 0.8390
11.750 1.1972 0.04979 0.04154 -0.0539 0.0253 0.8442
12.000 1.2023 0.05199 0.04394 -0.0526 0.0245 0.8502
12.250 1.2064 0.05420 0.04635 -0.0511 0.0238 0.8563
12.500 1.2110 0.05651 0.04885 -0.0498 0.0231 0.8635
12.750 1.2151 0.05885 0.05137 -0.0486 0.0226 0.8713
13.000 1.2189 0.06128 0.05399 -0.0475 0.0220 0.8807
13.250 1.2209 0.06372 0.05659 -0.0464 0.0214 0.8925
13.500 1.2212 0.06623 0.05924 -0.0452 0.0209 0.9095
13.750 1.2179 0.06861 0.06173 -0.0437 0.0205 0.9782
14.000 1.2214 0.07204 0.06546 -0.0440 0.0199 1.0000
14.250 1.2228 0.07577 0.06946 -0.0445 0.0194 1.0000
14.500 1.2218 0.07981 0.07376 -0.0451 0.0191 1.0000
14.750 1.2187 0.08422 0.07842 -0.0461 0.0188 1.0000
15.000 1.2132 0.08906 0.08351 -0.0474 0.0186 1.0000
15.250 1.2052 0.09439 0.08910 -0.0492 0.0185 1.0000
15.500 1.1948 0.10028 0.09524 -0.0517 0.0184 1.0000
15.750 1.1820 0.10679 0.10202 -0.0548 0.0184 1.0000
16.000 1.1669 0.11406 0.10954 -0.0589 0.0184 1.0000
16.250 1.1493 0.12225 0.11798 -0.0639 0.0185 1.0000
16.500 1.1290 0.13161 0.12758 -0.0701 0.0186 1.0000
16.750 1.1055 0.14248 0.13869 -0.0777 0.0188 1.0000
17.000 1.0770 0.15581 0.15221 -0.0871 0.0192 1.0000
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