EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1214 AIRFOIL (e1214-il) Reynolds number: 50,000 Max Cl/Cd: 18.63 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1214-il-50000-n5.txt Download as CSV file: xf-e1214-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1214 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5262 0.13276 0.12471 -0.0158 1.0000 0.0880
-15.000 -0.5145 0.13122 0.12319 -0.0161 1.0000 0.0917
-14.750 -0.5312 0.12326 0.11526 -0.0198 1.0000 0.0971
-14.500 -0.5260 0.12048 0.11250 -0.0208 1.0000 0.1024
-14.250 -0.5262 0.11659 0.10864 -0.0223 1.0000 0.1080
-14.000 -0.5481 0.10837 0.10045 -0.0262 1.0000 0.1160
-13.750 -0.5241 0.10979 0.10188 -0.0249 1.0000 0.1214
-13.250 -0.5462 0.09888 0.09102 -0.0296 1.0000 0.1383
-13.000 -0.5169 0.10118 0.09330 -0.0276 1.0000 0.1444
-12.750 -0.5205 0.09735 0.08949 -0.0290 1.0000 0.1528
-12.500 -0.5425 0.09051 0.08267 -0.0322 1.0000 0.1631
-12.000 -0.5220 0.08804 0.08020 -0.0319 1.0000 0.1781
-11.500 -0.5104 0.08403 0.07619 -0.0323 1.0000 0.1940
-11.250 -0.5403 0.07685 0.06906 -0.0355 1.0000 0.2053
-10.750 -0.5348 0.07236 0.06459 -0.0359 1.0000 0.2214
-10.250 -0.5384 0.06685 0.05911 -0.0367 1.0000 0.2381
-10.000 -0.5765 0.05975 0.05205 -0.0395 1.0000 0.2496
-9.750 -0.5636 0.05911 0.05144 -0.0384 1.0000 0.2557
-9.500 -0.6239 0.05235 0.04475 -0.0383 1.0000 0.2647
-9.250 -0.6740 0.04803 0.04046 -0.0344 1.0000 0.2711
-9.000 -0.6466 0.04891 0.04141 -0.0328 1.0000 0.2769
-8.750 -0.6977 0.04529 0.03777 -0.0276 1.0000 0.2834
-8.500 -0.6625 0.04503 0.03749 -0.0295 0.9766 0.2910
-8.250 -0.6359 0.04309 0.03530 -0.0328 0.9407 0.3017
-8.000 -0.5877 0.04264 0.03474 -0.0363 0.9161 0.3096
-7.750 -0.5559 0.04122 0.03307 -0.0389 0.8892 0.3189
-7.500 -0.5258 0.03999 0.03160 -0.0406 0.8641 0.3267
-7.250 -0.4916 0.03957 0.03102 -0.0415 0.8406 0.3333
-7.000 -0.4886 0.03748 0.02847 -0.0404 0.8186 0.3424
-6.750 -0.4558 0.03752 0.02846 -0.0401 0.7979 0.3469
-6.500 -0.4336 0.03708 0.02787 -0.0391 0.7785 0.3528
-6.250 -0.4239 0.03583 0.02629 -0.0376 0.7608 0.3604
-6.000 -0.4022 0.03534 0.02567 -0.0365 0.7440 0.3655
-5.750 -0.3784 0.03503 0.02524 -0.0355 0.7286 0.3707
-5.500 -0.3604 0.03430 0.02428 -0.0343 0.7144 0.3770
-5.250 -0.3451 0.03345 0.02317 -0.0331 0.6998 0.3835
-5.000 -0.3196 0.03320 0.02287 -0.0322 0.6865 0.3879
-4.750 -0.2973 0.03278 0.02232 -0.0313 0.6736 0.3933
-4.500 -0.2786 0.03216 0.02148 -0.0303 0.6608 0.3998
-4.250 -0.2561 0.03166 0.02079 -0.0294 0.6500 0.4053
-4.000 -0.2323 0.03144 0.02055 -0.0286 0.6372 0.4101
-3.750 -0.2085 0.03104 0.01996 -0.0278 0.6275 0.4160
-3.500 -0.1884 0.03060 0.01934 -0.0271 0.6153 0.4227
-3.250 -0.1620 0.03032 0.01896 -0.0265 0.6063 0.4278
-3.000 -0.1383 0.03016 0.01882 -0.0259 0.5946 0.4334
-2.750 -0.1135 0.02983 0.01828 -0.0253 0.5862 0.4402
-2.500 -0.0909 0.02963 0.01801 -0.0247 0.5752 0.4465
-2.250 -0.0646 0.02946 0.01779 -0.0241 0.5668 0.4523
-2.000 -0.0409 0.02937 0.01764 -0.0235 0.5573 0.4593
-1.750 -0.0167 0.02918 0.01730 -0.0230 0.5486 0.4669
-1.500 0.0094 0.02910 0.01721 -0.0225 0.5407 0.4730
-1.250 0.0331 0.02910 0.01719 -0.0219 0.5315 0.4807
-1.000 0.0592 0.02895 0.01689 -0.0215 0.5247 0.4892
-0.750 0.0832 0.02906 0.01708 -0.0209 0.5161 0.4966
-0.500 0.1081 0.02905 0.01698 -0.0205 0.5083 0.5059
-0.250 0.1359 0.02896 0.01681 -0.0201 0.5026 0.5147
0.000 0.1578 0.02923 0.01717 -0.0195 0.4938 0.5245
0.250 0.1831 0.02927 0.01718 -0.0190 0.4871 0.5349
0.500 0.2094 0.02927 0.01711 -0.0185 0.4816 0.5464
0.750 0.2300 0.02963 0.01761 -0.0177 0.4734 0.5576
1.000 0.2547 0.02973 0.01769 -0.0171 0.4673 0.5718
1.250 0.2820 0.02969 0.01763 -0.0166 0.4628 0.5860
1.500 0.2996 0.03025 0.01839 -0.0155 0.4549 0.6010
1.750 0.3226 0.03045 0.01865 -0.0147 0.4489 0.6192
2.000 0.3489 0.03045 0.01866 -0.0140 0.4443 0.6402
2.250 0.3668 0.03099 0.01940 -0.0128 0.4380 0.6622
2.500 0.3859 0.03144 0.02006 -0.0115 0.4318 0.6877
2.750 0.4108 0.03156 0.02028 -0.0106 0.4271 0.7200
3.000 0.4409 0.03157 0.02036 -0.0102 0.4231 0.7596
3.250 0.4586 0.03271 0.02187 -0.0097 0.4155 0.8036
3.500 0.5008 0.03324 0.02252 -0.0122 0.4097 0.8567
3.750 0.5607 0.03337 0.02256 -0.0173 0.4051 0.9090
4.000 0.5989 0.03498 0.02435 -0.0214 0.3973 0.9596
4.250 0.6421 0.03585 0.02518 -0.0255 0.3914 1.0000
4.500 0.6567 0.03627 0.02544 -0.0238 0.3881 1.0000
4.750 0.6790 0.03645 0.02543 -0.0227 0.3854 1.0000
5.000 0.6572 0.03912 0.02829 -0.0183 0.3788 1.0000
5.250 0.6575 0.04060 0.02977 -0.0157 0.3738 1.0000
5.500 0.6736 0.04124 0.03031 -0.0143 0.3703 1.0000
5.750 0.6990 0.04144 0.03039 -0.0136 0.3677 1.0000
6.000 0.6313 0.04720 0.03637 -0.0074 0.3595 1.0000
6.250 0.6077 0.05036 0.03953 -0.0043 0.3538 1.0000
6.500 0.6273 0.05094 0.04004 -0.0033 0.3509 1.0000
6.750 0.6617 0.05058 0.03958 -0.0029 0.3490 1.0000
7.250 0.5616 0.06504 0.05416 -0.0027 0.3317 1.0000
7.750 0.5146 0.07622 0.06536 -0.0047 0.3174 1.0000
8.000 0.5307 0.07760 0.06671 -0.0043 0.3150 1.0000
8.250 0.5525 0.07838 0.06744 -0.0037 0.3132 1.0000
8.500 0.5071 0.08663 0.07575 -0.0062 0.3048 1.0000
8.750 0.5140 0.08904 0.07815 -0.0064 0.3010 1.0000
9.000 0.5289 0.09069 0.07977 -0.0062 0.2984 1.0000
9.250 0.5478 0.09197 0.08104 -0.0059 0.2965 1.0000
9.500 0.5255 0.09786 0.08696 -0.0077 0.2912 1.0000
9.750 0.5223 0.10152 0.09064 -0.0086 0.2869 1.0000
10.000 0.5317 0.10382 0.09294 -0.0089 0.2836 1.0000
10.250 0.5461 0.10572 0.09483 -0.0089 0.2813 1.0000
10.500 0.5651 0.10712 0.09622 -0.0086 0.2794 1.0000
10.750 0.5455 0.11271 0.10186 -0.0107 0.2744 1.0000
11.000 0.5450 0.11613 0.10531 -0.0117 0.2704 1.0000
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