E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 200,000 Max Cl/Cd: 84.88 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e174-il-200000.txt Download as CSV file: xf-e174-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E174 (Dicke 8.92%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3300 0.08652 0.08329 -0.0342 1.0000 0.0403
-7.500 -0.3358 0.08418 0.08104 -0.0360 1.0000 0.0409
-7.250 -0.3404 0.08141 0.07838 -0.0408 1.0000 0.0414
-7.000 -0.3462 0.07885 0.07591 -0.0425 1.0000 0.0415
-6.750 -0.3294 0.07403 0.07105 -0.0511 0.9934 0.0418
-6.500 -0.3155 0.06779 0.06488 -0.0520 0.9869 0.0432
-6.250 -0.2879 0.06418 0.06126 -0.0553 0.9790 0.0452
-5.500 -0.1781 0.04549 0.04197 -0.0848 0.9435 0.0564
-5.250 -0.1511 0.04294 0.03934 -0.0869 0.9295 0.0615
-5.000 -0.1240 0.03823 0.03422 -0.0910 0.9138 0.0697
-4.750 -0.1020 0.03605 0.03194 -0.0912 0.8989 0.0739
-4.500 -0.0785 0.03275 0.02817 -0.0924 0.8843 0.0833
-4.250 -0.0562 0.03066 0.02596 -0.0922 0.8710 0.0875
-4.000 -0.0224 0.02153 0.01532 -0.0915 0.8601 0.0372
-3.750 0.0049 0.01865 0.01167 -0.0905 0.8492 0.0328
-3.500 0.0316 0.01723 0.00990 -0.0897 0.8391 0.0324
-3.250 0.0578 0.01586 0.00833 -0.0890 0.8287 0.0330
-3.000 0.0840 0.01491 0.00730 -0.0885 0.8185 0.0355
-2.750 0.1107 0.01438 0.00663 -0.0880 0.8097 0.0402
-2.500 0.1368 0.01339 0.00558 -0.0874 0.8004 0.0448
-2.250 0.1637 0.01267 0.00484 -0.0870 0.7917 0.0612
-2.000 0.1895 0.01161 0.00432 -0.0869 0.7840 0.1988
-1.750 0.2136 0.01074 0.00429 -0.0867 0.7753 0.4226
-1.500 0.2333 0.00991 0.00428 -0.0848 0.7686 0.6800
-1.250 0.2715 0.00923 0.00410 -0.0855 0.7605 0.9872
-1.000 0.3005 0.00934 0.00394 -0.0856 0.7540 1.0000
-0.750 0.3274 0.00944 0.00389 -0.0855 0.7456 1.0000
-0.500 0.3545 0.00957 0.00380 -0.0852 0.7395 1.0000
-0.250 0.3815 0.00969 0.00382 -0.0851 0.7315 1.0000
0.000 0.4088 0.00983 0.00378 -0.0849 0.7255 1.0000
0.250 0.4358 0.00996 0.00383 -0.0848 0.7179 1.0000
0.500 0.4632 0.01010 0.00383 -0.0846 0.7119 1.0000
0.750 0.4903 0.01025 0.00392 -0.0845 0.7049 1.0000
1.000 0.5176 0.01039 0.00397 -0.0843 0.6986 1.0000
1.250 0.5449 0.01056 0.00408 -0.0842 0.6923 1.0000
1.500 0.5721 0.01071 0.00417 -0.0841 0.6856 1.0000
1.750 0.5995 0.01088 0.00427 -0.0840 0.6799 1.0000
2.000 0.6265 0.01104 0.00444 -0.0839 0.6727 1.0000
2.250 0.6541 0.01121 0.00453 -0.0837 0.6673 1.0000
2.500 0.6809 0.01139 0.00474 -0.0836 0.6598 1.0000
2.750 0.7083 0.01154 0.00484 -0.0834 0.6538 1.0000
3.000 0.7351 0.01172 0.00507 -0.0833 0.6462 1.0000
3.250 0.7623 0.01185 0.00517 -0.0831 0.6395 1.0000
3.500 0.7889 0.01201 0.00537 -0.0828 0.6311 1.0000
3.750 0.8162 0.01213 0.00543 -0.0826 0.6240 1.0000
4.000 0.8424 0.01225 0.00566 -0.0823 0.6144 1.0000
4.250 0.8692 0.01237 0.00579 -0.0819 0.6061 1.0000
4.500 0.8958 0.01246 0.00591 -0.0816 0.5969 1.0000
4.750 0.9220 0.01257 0.00611 -0.0812 0.5868 1.0000
5.000 0.9484 0.01265 0.00623 -0.0808 0.5768 1.0000
5.250 0.9749 0.01271 0.00630 -0.0804 0.5663 1.0000
5.500 1.0005 0.01277 0.00647 -0.0799 0.5539 1.0000
5.750 1.0260 0.01283 0.00663 -0.0793 0.5404 1.0000
6.000 1.0509 0.01283 0.00666 -0.0786 0.5228 1.0000
6.250 1.0746 0.01283 0.00671 -0.0776 0.4971 1.0000
6.500 1.0975 0.01293 0.00680 -0.0766 0.4655 1.0000
6.750 1.1190 0.01320 0.00702 -0.0754 0.4203 1.0000
7.000 1.1387 0.01374 0.00739 -0.0741 0.3653 1.0000
7.250 1.1519 0.01492 0.00810 -0.0722 0.2779 1.0000
7.500 1.1633 0.01640 0.00913 -0.0702 0.2012 1.0000
7.750 1.1709 0.01827 0.01044 -0.0679 0.1163 1.0000
8.000 1.1710 0.02083 0.01239 -0.0646 0.0447 1.0000
8.250 1.1800 0.02241 0.01398 -0.0621 0.0351 1.0000
8.500 1.1917 0.02364 0.01533 -0.0599 0.0315 1.0000
8.750 1.1998 0.02497 0.01675 -0.0574 0.0294 1.0000
9.000 1.2010 0.02666 0.01849 -0.0541 0.0279 1.0000
9.250 1.2021 0.02864 0.02053 -0.0511 0.0270 1.0000
9.500 1.2116 0.03016 0.02215 -0.0490 0.0264 1.0000
9.750 1.2229 0.03180 0.02390 -0.0472 0.0257 1.0000
10.000 1.2363 0.03340 0.02564 -0.0457 0.0248 1.0000
10.250 1.2502 0.03501 0.02736 -0.0444 0.0237 1.0000
10.500 1.2657 0.03682 0.02929 -0.0432 0.0229 1.0000
10.750 1.2841 0.03896 0.03158 -0.0422 0.0224 1.0000
11.000 1.3021 0.04141 0.03424 -0.0412 0.0221 1.0000
11.250 1.3179 0.04429 0.03739 -0.0401 0.0221 1.0000
11.500 1.3277 0.04766 0.04111 -0.0386 0.0224 1.0000
11.750 1.3277 0.05149 0.04535 -0.0367 0.0229 1.0000
12.000 1.3206 0.05563 0.04987 -0.0348 0.0234 1.0000
12.250 1.3093 0.05999 0.05457 -0.0333 0.0240 1.0000
12.500 1.2957 0.06458 0.05945 -0.0323 0.0245 1.0000
12.750 1.2800 0.06944 0.06457 -0.0321 0.0250 1.0000
13.000 1.2624 0.07467 0.07004 -0.0325 0.0254 1.0000
13.250 1.2436 0.08031 0.07589 -0.0336 0.0258 1.0000
13.500 1.2237 0.08646 0.08224 -0.0354 0.0261 1.0000
13.750 1.2035 0.09323 0.08917 -0.0378 0.0265 1.0000
14.000 1.0372 0.09648 0.09295 -0.0360 0.0253 1.0000
14.250 1.0070 0.10349 0.10016 -0.0401 0.0255 1.0000
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Polar data table (+)
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