EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 100,000 Max Cl/Cd: 36.4 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e694-il-100000-n5.txt Download as CSV file: xf-e694-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 694 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 -0.1979 0.11959 0.11420 -0.1046 0.9333 0.0317
-10.750 -0.1966 0.11765 0.11227 -0.1029 0.9286 0.0312
-10.500 -0.1917 0.11434 0.10896 -0.1041 0.9259 0.0306
-10.250 -0.1878 0.11016 0.10480 -0.1065 0.9237 0.0304
-10.000 -0.1828 0.10576 0.10040 -0.1095 0.9220 0.0302
-9.750 -0.1961 0.10310 0.09780 -0.1076 0.9154 0.0305
-9.500 -0.1975 0.09944 0.09417 -0.1086 0.9117 0.0296
-9.250 -0.1981 0.09464 0.08939 -0.1116 0.9091 0.0295
-9.000 -0.1995 0.08884 0.08360 -0.1159 0.9070 0.0293
-8.750 -0.2760 0.07496 0.06968 -0.1207 0.8950 0.0260
-8.500 -0.2846 0.07142 0.06607 -0.1222 0.8923 0.0258
-8.250 -0.3268 0.07076 0.06544 -0.1148 0.8824 0.0258
-8.000 -0.3388 0.06656 0.06105 -0.1158 0.8786 0.0257
-7.750 -0.3591 0.06494 0.05936 -0.1115 0.8725 0.0256
-7.500 -0.3718 0.06173 0.05593 -0.1095 0.8676 0.0256
-7.250 -0.3695 0.05774 0.05163 -0.1099 0.8647 0.0255
-7.000 -0.3597 0.05362 0.04707 -0.1109 0.8628 0.0255
-6.750 -0.3668 0.05170 0.04490 -0.1073 0.8580 0.0255
-6.500 -0.3580 0.04890 0.04172 -0.1064 0.8546 0.0255
-6.250 -0.3395 0.04596 0.03830 -0.1069 0.8523 0.0255
-6.000 -0.3162 0.04335 0.03519 -0.1077 0.8508 0.0256
-5.750 -0.2898 0.04112 0.03249 -0.1086 0.8496 0.0258
-5.500 -0.2613 0.03931 0.03034 -0.1095 0.8485 0.0262
-5.250 -0.2319 0.03787 0.02872 -0.1106 0.8476 0.0269
-5.000 -0.2278 0.03748 0.02825 -0.1072 0.8424 0.0273
-4.750 -0.2056 0.03673 0.02736 -0.1069 0.8398 0.0285
-4.500 -0.1794 0.03599 0.02644 -0.1071 0.8378 0.0307
-4.250 -0.1513 0.03513 0.02545 -0.1076 0.8362 0.0325
-4.000 -0.1220 0.03437 0.02466 -0.1085 0.8349 0.0344
-3.750 -0.0907 0.03371 0.02391 -0.1096 0.8338 0.0368
-3.500 -0.0778 0.03357 0.02367 -0.1077 0.8292 0.0391
-3.250 -0.0543 0.03321 0.02331 -0.1078 0.8263 0.0433
-3.000 -0.0256 0.03277 0.02287 -0.1087 0.8242 0.0556
-2.750 0.0067 0.03215 0.02242 -0.1102 0.8225 0.0917
-2.500 0.0402 0.03135 0.02223 -0.1125 0.8212 0.2051
-2.250 0.0733 0.03009 0.02241 -0.1149 0.8203 0.5038
-2.000 0.0758 0.03045 0.02318 -0.1101 0.8149 0.6042
-1.750 0.0833 0.03085 0.02379 -0.1050 0.8110 0.6780
-1.500 0.1077 0.03125 0.02407 -0.1038 0.8087 0.7325
-1.250 0.1346 0.03158 0.02423 -0.1032 0.8070 0.7652
-1.000 0.1396 0.03223 0.02482 -0.0992 0.8005 0.7842
-0.750 0.1573 0.03256 0.02505 -0.0967 0.7972 0.8067
-0.500 0.1747 0.03271 0.02511 -0.0938 0.7948 0.8291
-0.250 0.1802 0.03305 0.02540 -0.0894 0.7894 0.8463
0.000 0.1951 0.03321 0.02548 -0.0869 0.7849 0.8599
0.250 0.2216 0.03322 0.02537 -0.0868 0.7823 0.8708
0.500 0.2451 0.03303 0.02507 -0.0855 0.7804 0.8812
0.750 0.2493 0.03344 0.02545 -0.0818 0.7728 0.8920
1.000 0.2718 0.03344 0.02537 -0.0810 0.7693 0.9018
1.250 0.3002 0.03331 0.02515 -0.0812 0.7670 0.9091
1.500 0.3324 0.03317 0.02492 -0.0822 0.7653 0.9150
1.750 0.3380 0.03379 0.02552 -0.0793 0.7561 0.9219
2.000 0.3674 0.03378 0.02545 -0.0799 0.7531 0.9273
2.250 0.3989 0.03359 0.02520 -0.0807 0.7509 0.9323
2.500 0.4337 0.03340 0.02495 -0.0822 0.7492 0.9372
2.750 0.4386 0.03414 0.02572 -0.0794 0.7386 0.9436
3.000 0.4709 0.03401 0.02555 -0.0805 0.7359 0.9490
3.250 0.5054 0.03377 0.02529 -0.0818 0.7339 0.9544
3.750 0.5493 0.03439 0.02596 -0.0814 0.7205 0.9676
4.000 0.5870 0.03414 0.02571 -0.0835 0.7183 0.9737
4.500 0.6350 0.03463 0.02628 -0.0840 0.7043 1.0000
4.750 0.6527 0.03533 0.02703 -0.0835 0.6950 1.0000
5.000 0.6850 0.03530 0.02702 -0.0848 0.6906 1.0000
5.250 0.7222 0.03500 0.02678 -0.0866 0.6882 1.0000
5.500 0.7361 0.03588 0.02772 -0.0857 0.6768 1.0000
5.750 0.7736 0.03543 0.02733 -0.0873 0.6740 1.0000
6.000 0.7900 0.03614 0.02811 -0.0866 0.6627 1.0000
6.250 0.8286 0.03539 0.02745 -0.0882 0.6594 1.0000
6.500 0.8465 0.03594 0.02808 -0.0876 0.6476 1.0000
6.750 0.8842 0.03513 0.02736 -0.0889 0.6444 1.0000
7.000 0.9012 0.03581 0.02815 -0.0882 0.6324 1.0000
7.500 0.9559 0.03579 0.02834 -0.0889 0.6171 1.0000
7.750 0.9794 0.03606 0.02873 -0.0888 0.6068 1.0000
8.000 1.0158 0.03523 0.02802 -0.0898 0.6002 1.0000
8.250 1.0403 0.03531 0.02821 -0.0897 0.5869 1.0000
8.500 1.0681 0.03515 0.02817 -0.0899 0.5733 1.0000
8.750 1.0986 0.03479 0.02790 -0.0902 0.5588 1.0000
9.000 1.1304 0.03433 0.02751 -0.0907 0.5424 1.0000
9.250 1.1648 0.03368 0.02692 -0.0914 0.5228 1.0000
9.500 1.1910 0.03372 0.02698 -0.0913 0.4989 1.0000
9.750 1.2182 0.03368 0.02691 -0.0912 0.4719 1.0000
10.000 1.2401 0.03407 0.02724 -0.0907 0.4425 1.0000
10.250 1.2565 0.03487 0.02798 -0.0896 0.4116 1.0000
10.500 1.2687 0.03601 0.02904 -0.0881 0.3804 1.0000
10.750 1.2770 0.03747 0.03039 -0.0864 0.3473 1.0000
11.000 1.2823 0.03921 0.03200 -0.0845 0.3130 1.0000
11.250 1.2852 0.04120 0.03383 -0.0826 0.2777 1.0000
11.500 1.2856 0.04348 0.03591 -0.0805 0.2444 1.0000
11.750 1.2872 0.04579 0.03806 -0.0788 0.2125 1.0000
12.000 1.2892 0.04817 0.04030 -0.0774 0.1776 1.0000
12.250 1.2899 0.05075 0.04270 -0.0759 0.1461 1.0000
12.500 1.2925 0.05323 0.04505 -0.0748 0.1201 1.0000
12.750 1.2957 0.05573 0.04749 -0.0737 0.0992 1.0000
13.000 1.2990 0.05829 0.05001 -0.0727 0.0792 1.0000
13.250 1.3001 0.06114 0.05281 -0.0717 0.0617 1.0000
13.500 1.3002 0.06417 0.05581 -0.0708 0.0475 1.0000
13.750 1.2997 0.06735 0.05901 -0.0699 0.0387 1.0000
14.000 1.2987 0.07067 0.06237 -0.0692 0.0335 1.0000
14.250 1.2988 0.07394 0.06577 -0.0688 0.0302 1.0000
14.500 1.2960 0.07764 0.06954 -0.0684 0.0282 1.0000
14.750 1.2960 0.08106 0.07316 -0.0682 0.0266 1.0000
15.000 1.2953 0.08464 0.07692 -0.0682 0.0253 1.0000
15.250 1.2942 0.08833 0.08076 -0.0683 0.0242 1.0000
15.500 1.2926 0.09214 0.08472 -0.0687 0.0234 1.0000
15.750 1.2902 0.09610 0.08879 -0.0692 0.0228 1.0000
16.000 1.2907 0.09968 0.09252 -0.0697 0.0221 1.0000
16.250 1.2925 0.10309 0.09611 -0.0702 0.0213 1.0000
16.500 1.2944 0.10653 0.09972 -0.0709 0.0205 1.0000
16.750 1.2959 0.11004 0.10337 -0.0718 0.0198 1.0000
17.000 1.2972 0.11361 0.10707 -0.0729 0.0191 1.0000
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