EPPLER 636 AIRFOIL (e636-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 636 AIRFOIL (e636-il) Reynolds number: 100,000 Max Cl/Cd: 33 at α=13° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e636-il-100000.txt Download as CSV file: xf-e636-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 636 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4377 0.09664 0.09240 -0.0110 1.0000 0.0898
-8.500 -0.4605 0.09333 0.08915 -0.0165 1.0000 0.0904
-8.250 -0.4831 0.09120 0.08698 -0.0181 1.0000 0.0908
-8.000 -0.4440 0.08425 0.08020 -0.0157 1.0000 0.0939
-7.750 -0.4363 0.08107 0.07707 -0.0150 1.0000 0.0972
-7.500 -0.4405 0.07795 0.07399 -0.0155 1.0000 0.0999
-7.250 -0.4539 0.07508 0.07105 -0.0176 1.0000 0.1042
-7.000 -0.4710 0.07242 0.06818 -0.0182 1.0000 0.1066
-6.750 -0.4468 0.06748 0.06353 -0.0173 1.0000 0.1102
-6.500 -0.4399 0.06471 0.06080 -0.0169 1.0000 0.1158
-6.250 -0.4553 0.06301 0.05890 -0.0163 0.9962 0.1222
-6.000 -0.3435 0.04266 0.03883 -0.0284 0.8677 0.1448
-5.750 -0.3858 0.05460 0.05005 -0.0260 0.9091 0.1526
-5.500 -0.3598 0.05045 0.04598 -0.0262 0.8735 0.1605
-5.250 -0.3495 0.04809 0.04338 -0.0244 0.8430 0.1740
-5.000 -0.3391 0.04600 0.04109 -0.0222 0.8182 0.1903
-4.750 -0.3315 0.04427 0.03912 -0.0197 0.7962 0.2158
-4.500 -0.3178 0.04202 0.03684 -0.0174 0.7771 0.2360
-4.250 -0.3101 0.04159 0.03609 -0.0142 0.7598 0.2749
-4.000 -0.2942 0.03816 0.03285 -0.0121 0.7433 0.2979
-3.750 -0.2337 0.03181 0.02388 -0.0118 0.7330 0.0878
-3.500 -0.2102 0.02949 0.02116 -0.0101 0.7186 0.0823
-3.250 -0.1840 0.02875 0.01968 -0.0078 0.7046 0.0767
-3.000 -0.1572 0.02647 0.01719 -0.0071 0.6913 0.0747
-2.750 -0.1293 0.02490 0.01536 -0.0063 0.6789 0.0734
-2.500 -0.1005 0.02363 0.01384 -0.0057 0.6672 0.0732
-2.250 -0.0713 0.02257 0.01258 -0.0052 0.6553 0.0741
-2.000 -0.0429 0.02174 0.01164 -0.0047 0.6434 0.0770
-1.750 -0.0171 0.02076 0.01077 -0.0041 0.6331 0.0840
-1.500 0.2079 0.01726 0.00975 -0.0366 0.6097 1.0000
-1.250 0.2303 0.01733 0.00961 -0.0359 0.5997 1.0000
-1.000 0.2523 0.01741 0.00942 -0.0349 0.5917 1.0000
-0.750 0.2751 0.01751 0.00939 -0.0343 0.5820 1.0000
-0.500 0.2977 0.01764 0.00932 -0.0334 0.5743 1.0000
-0.250 0.3206 0.01778 0.00934 -0.0328 0.5659 1.0000
0.000 0.3435 0.01795 0.00936 -0.0320 0.5586 1.0000
0.250 0.3666 0.01812 0.00942 -0.0313 0.5507 1.0000
0.500 0.3896 0.01832 0.00948 -0.0306 0.5443 1.0000
0.750 0.4129 0.01856 0.00967 -0.0300 0.5368 1.0000
1.000 0.4360 0.01875 0.00967 -0.0291 0.5313 1.0000
1.250 0.4593 0.01906 0.01003 -0.0287 0.5233 1.0000
1.500 0.4826 0.01927 0.01011 -0.0279 0.5177 1.0000
1.750 0.5057 0.01966 0.01051 -0.0274 0.5114 1.0000
2.000 0.5288 0.01996 0.01078 -0.0268 0.5053 1.0000
2.250 0.5520 0.02023 0.01090 -0.0259 0.5006 1.0000
2.500 0.5744 0.02073 0.01151 -0.0254 0.4933 1.0000
2.750 0.5974 0.02105 0.01178 -0.0247 0.4883 1.0000
3.000 0.6200 0.02153 0.01225 -0.0240 0.4832 1.0000
3.250 0.6419 0.02204 0.01284 -0.0233 0.4768 1.0000
3.500 0.6650 0.02234 0.01306 -0.0225 0.4722 1.0000
3.750 0.6862 0.02304 0.01387 -0.0218 0.4667 1.0000
4.000 0.7077 0.02365 0.01454 -0.0211 0.4612 1.0000
4.250 0.7307 0.02396 0.01479 -0.0202 0.4570 1.0000
4.500 0.7504 0.02483 0.01579 -0.0195 0.4511 1.0000
4.750 0.7711 0.02550 0.01656 -0.0187 0.4457 1.0000
5.000 0.7942 0.02585 0.01686 -0.0178 0.4419 1.0000
5.250 0.8117 0.02695 0.01813 -0.0169 0.4361 1.0000
5.500 0.8312 0.02769 0.01896 -0.0159 0.4305 1.0000
5.750 0.8547 0.02801 0.01926 -0.0150 0.4269 1.0000
6.000 0.8691 0.02945 0.02091 -0.0140 0.4210 1.0000
6.250 0.8870 0.03032 0.02189 -0.0129 0.4154 1.0000
6.500 0.9118 0.03046 0.02198 -0.0120 0.4118 1.0000
6.750 0.9207 0.03240 0.02421 -0.0106 0.4053 1.0000
7.000 0.9381 0.03325 0.02515 -0.0094 0.3999 1.0000
7.250 0.9661 0.03302 0.02485 -0.0086 0.3965 1.0000
7.500 0.9644 0.03588 0.02805 -0.0067 0.3887 1.0000
7.750 0.9870 0.03605 0.02825 -0.0055 0.3839 1.0000
8.000 1.0214 0.03523 0.02735 -0.0050 0.3806 1.0000
8.250 1.0051 0.03911 0.03162 -0.0022 0.3713 1.0000
8.500 1.0426 0.03781 0.03027 -0.0017 0.3674 1.0000
8.750 1.0237 0.04183 0.03458 0.0012 0.3590 1.0000
9.000 1.0576 0.04072 0.03351 0.0020 0.3540 1.0000
9.250 1.0777 0.04105 0.03391 0.0034 0.3486 1.0000
9.500 0.8873 0.06143 0.05435 0.0076 0.3339 1.0000
9.750 0.8398 0.06956 0.06239 0.0064 0.3237 1.0000
10.000 0.9268 0.06111 0.05420 0.0111 0.3229 1.0000
10.250 1.1669 0.04053 0.03373 0.0084 0.3225 1.0000
10.500 0.9029 0.06920 0.06232 0.0112 0.3075 1.0000
10.750 1.2197 0.03916 0.03249 0.0106 0.3071 1.0000
11.250 1.2346 0.04033 0.03399 0.0153 0.2904 1.0000
11.500 1.2495 0.04010 0.03387 0.0173 0.2812 1.0000
11.750 1.2503 0.04093 0.03484 0.0201 0.2727 1.0000
12.000 1.1384 0.05089 0.04491 0.0264 0.2712 1.0000
12.250 1.0410 0.06512 0.05900 0.0228 0.2636 1.0000
12.500 1.2901 0.03961 0.03371 0.0271 0.2422 1.0000
12.750 1.2964 0.03957 0.03367 0.0298 0.2320 1.0000
13.000 1.3037 0.03951 0.03356 0.0322 0.2207 1.0000
13.250 1.2807 0.04227 0.03648 0.0345 0.2133 1.0000
13.500 1.2734 0.04422 0.03845 0.0356 0.2035 1.0000
13.750 1.2707 0.04585 0.04003 0.0364 0.1924 1.0000
14.000 1.2679 0.04772 0.04181 0.0369 0.1810 1.0000
14.250 1.2405 0.05288 0.04717 0.0359 0.1745 1.0000
14.500 1.2330 0.05577 0.05001 0.0357 0.1644 1.0000
14.750 1.2255 0.05867 0.05280 0.0352 0.1537 1.0000
15.000 1.2026 0.06410 0.05837 0.0335 0.1471 1.0000
15.250 1.1916 0.06784 0.06206 0.0325 0.1382 1.0000
15.500 1.1849 0.07098 0.06505 0.0317 0.1281 1.0000
15.750 1.1637 0.07694 0.07120 0.0295 0.1228 1.0000
16.000 1.1552 0.08075 0.07492 0.0282 0.1138 1.0000
16.250 1.1402 0.08605 0.08031 0.0262 0.1076 1.0000
16.500 1.1328 0.09007 0.08433 0.0250 0.1001 1.0000
16.750 1.1293 0.09332 0.08742 0.0240 0.0906 1.0000
17.000 1.1083 0.10025 0.09459 0.0210 0.0867 1.0000
17.250 1.1061 0.10346 0.09766 0.0201 0.0779 1.0000
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