E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E174 (Dicke 8.92%) (e174-il) Reynolds number: 200,000 Max Cl/Cd: 83 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e174-il-200000-n5.txt Download as CSV file: xf-e174-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3347 0.08691 0.08359 -0.0328 1.0000 0.0235
-7.750 -0.3331 0.08390 0.08064 -0.0338 1.0000 0.0237
-7.500 -0.3333 0.08111 0.07792 -0.0343 1.0000 0.0240
-7.250 -0.3343 0.07802 0.07492 -0.0357 0.9963 0.0240
-7.000 -0.3122 0.06688 0.06373 -0.0525 0.9596 0.0168
-6.750 -0.2896 0.06379 0.06058 -0.0564 0.9386 0.0155
-6.250 -0.2436 0.05043 0.04690 -0.0736 0.8899 0.0157
-6.000 -0.2244 0.04488 0.04110 -0.0781 0.8700 0.0154
-5.750 -0.2054 0.03903 0.03490 -0.0814 0.8523 0.0154
-5.500 -0.1857 0.03385 0.02929 -0.0833 0.8371 0.0149
-5.250 -0.1645 0.02894 0.02382 -0.0844 0.8237 0.0143
-5.000 -0.1414 0.02476 0.01898 -0.0848 0.8115 0.0139
-4.750 -0.1167 0.02167 0.01524 -0.0847 0.7998 0.0136
-4.500 -0.0909 0.01951 0.01256 -0.0844 0.7889 0.0136
-4.250 -0.0646 0.01791 0.01056 -0.0840 0.7788 0.0138
-4.000 -0.0382 0.01667 0.00901 -0.0836 0.7690 0.0142
-3.750 -0.0116 0.01564 0.00776 -0.0833 0.7595 0.0147
-3.500 0.0151 0.01483 0.00674 -0.0829 0.7509 0.0156
-3.250 0.0417 0.01416 0.00594 -0.0827 0.7421 0.0174
-3.000 0.0686 0.01363 0.00532 -0.0825 0.7341 0.0191
-2.750 0.0958 0.01315 0.00469 -0.0822 0.7262 0.0207
-2.500 0.1233 0.01272 0.00413 -0.0821 0.7186 0.0232
-2.250 0.1507 0.01233 0.00367 -0.0819 0.7114 0.0317
-2.000 0.1779 0.01186 0.00336 -0.0819 0.7043 0.0780
-1.750 0.2048 0.01145 0.00319 -0.0819 0.6974 0.1513
-1.500 0.2314 0.01097 0.00307 -0.0820 0.6909 0.2662
-1.250 0.2579 0.01059 0.00297 -0.0819 0.6843 0.3735
-1.000 0.2832 0.01015 0.00293 -0.0815 0.6783 0.5132
-0.750 0.3057 0.00963 0.00294 -0.0802 0.6719 0.6857
-0.500 0.3275 0.00918 0.00289 -0.0780 0.6665 0.8739
-0.250 0.3694 0.00909 0.00274 -0.0807 0.6599 1.0000
0.000 0.3968 0.00918 0.00269 -0.0806 0.6540 1.0000
0.250 0.4243 0.00928 0.00266 -0.0805 0.6484 1.0000
0.500 0.4518 0.00937 0.00266 -0.0804 0.6422 1.0000
0.750 0.4792 0.00948 0.00265 -0.0803 0.6371 1.0000
1.000 0.5067 0.00958 0.00269 -0.0803 0.6309 1.0000
1.250 0.5341 0.00969 0.00273 -0.0802 0.6253 1.0000
1.500 0.5616 0.00981 0.00278 -0.0801 0.6199 1.0000
1.750 0.5891 0.00992 0.00287 -0.0800 0.6137 1.0000
2.000 0.6164 0.01005 0.00294 -0.0799 0.6085 1.0000
2.250 0.6438 0.01016 0.00305 -0.0799 0.6023 1.0000
2.500 0.6711 0.01029 0.00316 -0.0798 0.5964 1.0000
2.750 0.6984 0.01042 0.00329 -0.0796 0.5904 1.0000
3.000 0.7256 0.01055 0.00343 -0.0795 0.5835 1.0000
3.250 0.7527 0.01069 0.00355 -0.0794 0.5768 1.0000
3.500 0.7796 0.01081 0.00369 -0.0792 0.5683 1.0000
3.750 0.8065 0.01094 0.00386 -0.0790 0.5596 1.0000
4.000 0.8331 0.01107 0.00399 -0.0788 0.5506 1.0000
4.250 0.8598 0.01120 0.00417 -0.0786 0.5401 1.0000
4.500 0.8863 0.01134 0.00437 -0.0783 0.5297 1.0000
4.750 0.9126 0.01149 0.00455 -0.0780 0.5186 1.0000
5.000 0.9386 0.01165 0.00474 -0.0777 0.5059 1.0000
5.250 0.9645 0.01182 0.00496 -0.0773 0.4916 1.0000
5.500 0.9901 0.01201 0.00522 -0.0770 0.4755 1.0000
5.750 1.0151 0.01223 0.00546 -0.0765 0.4546 1.0000
6.000 1.0373 0.01260 0.00568 -0.0755 0.4091 1.0000
6.250 1.0555 0.01336 0.00607 -0.0742 0.3327 1.0000
6.500 1.0714 0.01448 0.00678 -0.0727 0.2554 1.0000
6.750 1.0876 0.01563 0.00759 -0.0714 0.1917 1.0000
7.000 1.1045 0.01671 0.00841 -0.0702 0.1432 1.0000
7.250 1.1213 0.01776 0.00925 -0.0690 0.1025 1.0000
7.500 1.1368 0.01891 0.01019 -0.0676 0.0645 1.0000
7.750 1.1508 0.02015 0.01125 -0.0660 0.0344 1.0000
8.000 1.1657 0.02125 0.01232 -0.0644 0.0216 1.0000
8.250 1.1815 0.02221 0.01333 -0.0630 0.0178 1.0000
8.500 1.1967 0.02317 0.01439 -0.0614 0.0162 1.0000
8.750 1.2095 0.02427 0.01558 -0.0596 0.0151 1.0000
9.000 1.2203 0.02534 0.01678 -0.0575 0.0145 1.0000
9.250 1.2291 0.02646 0.01804 -0.0552 0.0140 1.0000
9.500 1.2362 0.02772 0.01945 -0.0529 0.0137 1.0000
9.750 1.2422 0.02914 0.02100 -0.0507 0.0133 1.0000
10.000 1.2475 0.03070 0.02269 -0.0488 0.0131 1.0000
10.250 1.2522 0.03244 0.02455 -0.0471 0.0128 1.0000
10.500 1.2571 0.03427 0.02649 -0.0456 0.0123 1.0000
10.750 1.2624 0.03614 0.02847 -0.0443 0.0121 1.0000
11.000 1.2671 0.03816 0.03058 -0.0432 0.0116 1.0000
11.250 1.2709 0.04036 0.03287 -0.0422 0.0112 1.0000
11.500 1.2725 0.04296 0.03556 -0.0411 0.0107 1.0000
11.750 1.2771 0.04539 0.03812 -0.0401 0.0106 1.0000
12.000 1.2834 0.04766 0.04055 -0.0393 0.0105 1.0000
12.250 1.2891 0.05006 0.04312 -0.0385 0.0104 1.0000
12.500 1.2940 0.05263 0.04587 -0.0379 0.0103 1.0000
12.750 1.2976 0.05539 0.04883 -0.0374 0.0102 1.0000
13.000 1.2992 0.05848 0.05214 -0.0370 0.0100 1.0000
13.250 1.2987 0.06185 0.05573 -0.0369 0.0099 1.0000
13.500 1.2963 0.06553 0.05963 -0.0371 0.0099 1.0000
13.750 1.2914 0.06959 0.06394 -0.0375 0.0098 1.0000
14.000 1.2842 0.07408 0.06866 -0.0383 0.0098 1.0000
14.250 1.2750 0.07900 0.07382 -0.0396 0.0098 1.0000
14.500 1.2638 0.08438 0.07944 -0.0414 0.0097 1.0000
14.750 1.2514 0.09022 0.08551 -0.0437 0.0098 1.0000
15.000 1.2376 0.09661 0.09213 -0.0466 0.0097 1.0000
15.250 1.2224 0.10363 0.09937 -0.0501 0.0098 1.0000
15.500 1.2069 0.11111 0.10705 -0.0542 0.0098 1.0000
15.750 1.1905 0.11927 0.11541 -0.0590 0.0098 1.0000
16.000 1.1736 0.12802 0.12435 -0.0644 0.0099 1.0000
16.250 1.1559 0.13765 0.13415 -0.0706 0.0099 1.0000
16.500 1.1378 0.14815 0.14480 -0.0774 0.0100 1.0000
16.750 1.1182 0.15998 0.15676 -0.0851 0.0102 1.0000
17.000 1.0964 0.17372 0.17059 -0.0935 0.0103 1.0000
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Polar data table (+)
Polar graphs
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