EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 50,000 Max Cl/Cd: 17.74 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e398-il-50000-n5.txt Download as CSV file: xf-e398-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 398 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3038 0.12364 0.11717 -0.0490 1.0000 0.0536
-10.500 -0.3153 0.12150 0.11513 -0.0475 1.0000 0.0533
-10.250 -0.3269 0.11967 0.11340 -0.0456 1.0000 0.0538
-10.000 -0.3155 0.11473 0.10846 -0.0504 0.9941 0.0550
-9.750 -0.3082 0.10939 0.10313 -0.0554 0.9871 0.0569
-9.500 -0.3036 0.10367 0.09743 -0.0607 0.9800 0.0578
-9.250 -0.3017 0.09750 0.09129 -0.0662 0.9722 0.0585
-9.000 -0.3059 0.09099 0.08483 -0.0715 0.9627 0.0590
-8.750 -0.3153 0.08360 0.07750 -0.0776 0.9528 0.0594
-8.500 -0.3337 0.07499 0.06892 -0.0849 0.9414 0.0595
-8.250 -0.3518 0.06508 0.05888 -0.0964 0.9284 0.0591
-8.000 -0.3659 0.05642 0.04979 -0.1060 0.9155 0.0594
-7.750 -0.3572 0.05363 0.04690 -0.1078 0.9058 0.0624
-7.500 -0.3379 0.04922 0.04208 -0.1130 0.8995 0.0668
-7.250 -0.3282 0.04479 0.03701 -0.1160 0.8899 0.0717
-7.000 -0.2992 0.04282 0.03484 -0.1185 0.8848 0.0791
-6.750 -0.2781 0.04064 0.03233 -0.1199 0.8777 0.0862
-6.500 -0.2505 0.03841 0.02961 -0.1220 0.8716 0.0964
-6.250 -0.2153 0.03687 0.02785 -0.1246 0.8678 0.1080
-6.000 -0.1968 0.03607 0.02701 -0.1240 0.8596 0.1168
-5.750 -0.1652 0.03486 0.02555 -0.1257 0.8548 0.1301
-5.500 -0.1280 0.03372 0.02421 -0.1281 0.8515 0.1465
-5.250 -0.1110 0.03324 0.02361 -0.1271 0.8428 0.1593
-5.000 -0.0780 0.03249 0.02270 -0.1286 0.8384 0.1775
-4.750 -0.0400 0.03170 0.02166 -0.1309 0.8353 0.2000
-4.500 -0.0249 0.03163 0.02152 -0.1294 0.8265 0.2159
-4.250 0.0078 0.03124 0.02111 -0.1305 0.8222 0.2371
-4.000 0.0402 0.03088 0.02062 -0.1316 0.8181 0.2607
-3.750 0.0579 0.03094 0.02060 -0.1305 0.8102 0.2803
-3.500 0.0899 0.03071 0.02034 -0.1314 0.8061 0.3035
-3.250 0.1199 0.03056 0.02003 -0.1320 0.8015 0.3284
-3.000 0.1381 0.03076 0.02022 -0.1308 0.7942 0.3480
-2.750 0.1698 0.03062 0.02002 -0.1316 0.7902 0.3728
-2.500 0.1990 0.03060 0.01990 -0.1320 0.7858 0.3974
-2.250 0.2160 0.03093 0.02023 -0.1306 0.7783 0.4175
-2.000 0.2478 0.03087 0.02007 -0.1313 0.7744 0.4445
-1.750 0.2779 0.03084 0.02002 -0.1316 0.7707 0.4692
-1.500 0.2906 0.03140 0.02057 -0.1298 0.7625 0.4898
-1.250 0.3209 0.03138 0.02054 -0.1301 0.7586 0.5166
-0.750 0.3602 0.03211 0.02128 -0.1280 0.7467 0.5664
-0.500 0.3896 0.03213 0.02130 -0.1281 0.7429 0.5967
-0.250 0.4220 0.03201 0.02118 -0.1284 0.7401 0.6294
0.000 0.4232 0.03302 0.02228 -0.1249 0.7306 0.6536
0.250 0.4503 0.03304 0.02234 -0.1245 0.7269 0.6897
0.500 0.4794 0.03286 0.02221 -0.1239 0.7242 0.7299
0.750 0.4736 0.03402 0.02350 -0.1194 0.7142 0.7636
1.000 0.4953 0.03388 0.02344 -0.1176 0.7106 0.8207
1.500 0.5291 0.03507 0.02461 -0.1157 0.6972 1.0000
1.750 0.5670 0.03524 0.02458 -0.1177 0.6942 1.0000
2.000 0.5752 0.03677 0.02602 -0.1165 0.6853 1.0000
2.250 0.6039 0.03729 0.02642 -0.1172 0.6807 1.0000
2.500 0.6401 0.03739 0.02640 -0.1185 0.6779 1.0000
2.750 0.6418 0.03931 0.02829 -0.1166 0.6678 1.0000
3.000 0.6724 0.03967 0.02857 -0.1172 0.6639 1.0000
3.250 0.6966 0.04038 0.02923 -0.1172 0.6588 1.0000
3.500 0.7056 0.04195 0.03078 -0.1160 0.6501 1.0000
3.750 0.7388 0.04211 0.03090 -0.1167 0.6469 1.0000
4.250 0.7693 0.04458 0.03337 -0.1152 0.6325 1.0000
4.500 0.7974 0.04500 0.03379 -0.1153 0.6283 1.0000
4.750 0.8003 0.04703 0.03584 -0.1137 0.6182 1.0000
5.000 0.8343 0.04704 0.03588 -0.1142 0.6150 1.0000
5.250 0.8323 0.04944 0.03832 -0.1123 0.6038 1.0000
5.500 0.8641 0.04955 0.03846 -0.1126 0.6000 1.0000
6.000 0.8946 0.05203 0.04106 -0.1110 0.5849 1.0000
6.500 0.9259 0.05443 0.04359 -0.1095 0.5695 1.0000
7.000 0.9576 0.05677 0.04610 -0.1080 0.5539 1.0000
7.500 0.9908 0.05891 0.04843 -0.1064 0.5381 1.0000
7.750 0.9921 0.06127 0.05088 -0.1051 0.5264 1.0000
8.000 1.0250 0.06085 0.05060 -0.1049 0.5220 1.0000
8.500 1.0409 0.06440 0.05437 -0.1028 0.5010 1.0000
8.750 1.0603 0.06504 0.05514 -0.1020 0.4927 1.0000
9.250 1.0978 0.06629 0.05669 -0.1002 0.4759 1.0000
9.500 1.0995 0.06869 0.05922 -0.0992 0.4630 1.0000
10.000 1.1392 0.06933 0.06019 -0.0972 0.4456 1.0000
10.250 1.1427 0.07153 0.06253 -0.0962 0.4324 1.0000
10.750 1.1873 0.07099 0.06235 -0.0938 0.4145 1.0000
11.000 1.1921 0.07296 0.06448 -0.0928 0.4009 1.0000
11.500 1.2129 0.07540 0.06724 -0.0907 0.3755 1.0000
11.750 1.2557 0.07191 0.06396 -0.0888 0.3678 1.0000
12.000 1.2656 0.07306 0.06528 -0.0877 0.3533 1.0000
12.500 1.2935 0.07415 0.06663 -0.0852 0.3228 1.0000
12.750 1.3046 0.07515 0.06771 -0.0841 0.3059 1.0000
13.000 1.3086 0.07726 0.06991 -0.0832 0.2881 1.0000
13.250 1.3150 0.07904 0.07177 -0.0824 0.2699 1.0000
13.500 1.3221 0.08071 0.07345 -0.0815 0.2513 1.0000
13.750 1.3288 0.08246 0.07514 -0.0807 0.2329 1.0000
14.000 1.3291 0.08536 0.07801 -0.0803 0.2156 1.0000
14.250 1.3271 0.08874 0.08141 -0.0802 0.1989 1.0000
14.500 1.3253 0.09218 0.08485 -0.0803 0.1834 1.0000
14.750 1.3230 0.09577 0.08843 -0.0805 0.1687 1.0000
15.000 1.3208 0.09942 0.09209 -0.0809 0.1552 1.0000
15.250 1.3187 0.10313 0.09577 -0.0814 0.1428 1.0000
15.500 1.3174 0.10671 0.09929 -0.0819 0.1314 1.0000
15.750 1.3138 0.11100 0.10370 -0.0829 0.1207 1.0000
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Polar data table (+)
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