E184 (8.33%) (e184-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 50,000 Max Cl/Cd: 31.74 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e184-il-50000-n5.txt Download as CSV file: xf-e184-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E184 (8.33%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6554 0.08332 0.07727 0.0010 1.0000 0.0428
-8.250 -0.6564 0.07849 0.07241 -0.0011 1.0000 0.0426
-8.000 -0.6577 0.07353 0.06737 -0.0033 1.0000 0.0424
-7.750 -0.6576 0.06860 0.06228 -0.0052 1.0000 0.0424
-7.500 -0.6562 0.06364 0.05704 -0.0067 1.0000 0.0427
-7.000 -0.6394 0.05548 0.04860 -0.0079 1.0000 0.0453
-6.750 -0.6282 0.05129 0.04408 -0.0083 1.0000 0.0459
-6.500 -0.6154 0.04681 0.03911 -0.0083 1.0000 0.0455
-6.250 -0.5993 0.04278 0.03454 -0.0080 1.0000 0.0454
-6.000 -0.5802 0.03924 0.03050 -0.0076 1.0000 0.0456
-5.750 -0.5587 0.03613 0.02685 -0.0072 1.0000 0.0461
-5.500 -0.5351 0.03337 0.02367 -0.0069 1.0000 0.0470
-5.250 -0.5098 0.03093 0.02085 -0.0066 1.0000 0.0483
-5.000 -0.4833 0.02876 0.01836 -0.0063 1.0000 0.0501
-4.750 -0.4559 0.02685 0.01616 -0.0061 1.0000 0.0527
-4.500 -0.4295 0.02528 0.01444 -0.0060 1.0000 0.0583
-4.250 -0.4037 0.02404 0.01306 -0.0058 1.0000 0.0674
-4.000 -0.3790 0.02268 0.01167 -0.0055 1.0000 0.0772
-3.750 -0.3558 0.02132 0.01032 -0.0051 1.0000 0.0973
-3.500 -0.3375 0.01992 0.00933 -0.0045 1.0000 0.1664
-3.250 -0.3117 0.01799 0.00865 -0.0055 0.9786 0.3748
-3.000 -0.2829 0.01647 0.00845 -0.0047 0.9649 0.6555
-2.750 -0.1945 0.01624 0.00829 -0.0124 0.9731 0.9066
-2.500 -0.1208 0.01630 0.00775 -0.0207 0.9719 0.9829
-2.250 -0.0676 0.01614 0.00716 -0.0266 0.9565 1.0000
-2.000 -0.0321 0.01615 0.00682 -0.0289 0.9359 1.0000
-1.750 -0.0008 0.01621 0.00660 -0.0302 0.9182 1.0000
-1.500 0.0266 0.01633 0.00648 -0.0306 0.9024 1.0000
-1.250 0.0512 0.01648 0.00643 -0.0304 0.8877 1.0000
-1.000 0.0746 0.01665 0.00641 -0.0298 0.8743 1.0000
-0.750 0.0976 0.01684 0.00644 -0.0292 0.8617 1.0000
-0.500 0.1205 0.01704 0.00652 -0.0285 0.8498 1.0000
-0.250 0.1435 0.01725 0.00663 -0.0278 0.8385 1.0000
0.000 0.1664 0.01748 0.00676 -0.0271 0.8280 1.0000
0.250 0.1891 0.01772 0.00692 -0.0262 0.8183 1.0000
0.500 0.2123 0.01797 0.00712 -0.0255 0.8081 1.0000
0.750 0.2357 0.01825 0.00737 -0.0250 0.7981 1.0000
1.000 0.2587 0.01852 0.00764 -0.0241 0.7888 1.0000
1.250 0.2817 0.01881 0.00792 -0.0233 0.7796 1.0000
1.500 0.3053 0.01912 0.00826 -0.0227 0.7695 1.0000
1.750 0.3285 0.01944 0.00860 -0.0219 0.7600 1.0000
2.000 0.3512 0.01972 0.00897 -0.0208 0.7510 1.0000
2.250 0.3745 0.02007 0.00939 -0.0202 0.7399 1.0000
2.500 0.3973 0.02039 0.00980 -0.0192 0.7288 1.0000
2.750 0.4199 0.02069 0.01019 -0.0181 0.7174 1.0000
3.000 0.4422 0.02096 0.01056 -0.0168 0.7056 1.0000
3.250 0.4643 0.02120 0.01097 -0.0154 0.6929 1.0000
3.500 0.4862 0.02141 0.01132 -0.0138 0.6787 1.0000
3.750 0.5081 0.02160 0.01166 -0.0123 0.6629 1.0000
4.000 0.5298 0.02171 0.01193 -0.0105 0.6459 1.0000
4.250 0.5512 0.02170 0.01207 -0.0084 0.6279 1.0000
4.500 0.5728 0.02169 0.01226 -0.0065 0.6059 1.0000
4.750 0.5941 0.02154 0.01236 -0.0042 0.5818 1.0000
5.000 0.6156 0.02139 0.01242 -0.0021 0.5513 1.0000
5.250 0.6368 0.02119 0.01240 0.0002 0.5134 1.0000
5.500 0.6576 0.02110 0.01243 0.0024 0.4585 1.0000
5.750 0.6763 0.02131 0.01245 0.0048 0.3702 1.0000
6.000 0.6902 0.02270 0.01308 0.0067 0.2563 1.0000
6.250 0.7017 0.02502 0.01474 0.0076 0.1629 1.0000
6.500 0.7122 0.02750 0.01673 0.0085 0.0961 1.0000
6.750 0.7242 0.02974 0.01868 0.0097 0.0661 1.0000
7.000 0.7390 0.03158 0.02058 0.0111 0.0507 1.0000
7.250 0.7542 0.03343 0.02245 0.0126 0.0439 1.0000
7.500 0.7740 0.03542 0.02469 0.0144 0.0402 1.0000
7.750 0.7956 0.03758 0.02715 0.0160 0.0375 1.0000
8.000 0.8160 0.04008 0.02993 0.0173 0.0356 1.0000
8.250 0.8327 0.04266 0.03276 0.0183 0.0334 1.0000
8.500 0.8454 0.04582 0.03607 0.0191 0.0313 1.0000
8.750 0.8556 0.04908 0.03977 0.0201 0.0302 1.0000
9.000 0.8611 0.05249 0.04367 0.0210 0.0291 1.0000
9.250 0.8620 0.05619 0.04786 0.0217 0.0287 1.0000
9.500 0.8571 0.06008 0.05209 0.0222 0.0285 1.0000
9.750 0.8465 0.06395 0.05621 0.0225 0.0285 1.0000
10.000 0.8321 0.06792 0.06035 0.0221 0.0286 1.0000
10.250 0.8161 0.07256 0.06514 0.0203 0.0287 1.0000
10.500 0.8008 0.07770 0.07040 0.0176 0.0291 1.0000
10.750 0.7847 0.08369 0.07638 0.0139 0.0293 1.0000
11.000 0.7709 0.09002 0.08276 0.0099 0.0297 1.0000
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Polar data table (+)
Polar graphs
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