EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 360 AIRFOIL (e360-il) Reynolds number: 200,000 Max Cl/Cd: 63.33 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e360-il-200000.txt Download as CSV file: xf-e360-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 360 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5083 0.09377 0.09021 -0.0297 1.0000 0.0498
-10.000 -0.5024 0.09097 0.08742 -0.0294 1.0000 0.0505
-9.750 -0.5023 0.08705 0.08354 -0.0310 1.0000 0.0512
-9.500 -0.5078 0.08201 0.07854 -0.0341 1.0000 0.0522
-9.250 -0.5235 0.07598 0.07250 -0.0387 1.0000 0.0527
-9.000 -0.5420 0.07139 0.06788 -0.0406 1.0000 0.0530
-8.750 -0.5610 0.06790 0.06435 -0.0397 1.0000 0.0535
-8.500 -0.5776 0.06483 0.06121 -0.0376 1.0000 0.0543
-8.250 -0.5900 0.06168 0.05794 -0.0355 1.0000 0.0558
-8.000 -0.6233 0.06147 0.05712 -0.0295 1.0000 0.0588
-7.750 -0.6300 0.05546 0.05104 -0.0275 1.0000 0.0599
-7.500 -0.6195 0.05197 0.04767 -0.0264 1.0000 0.0610
-7.250 -0.6121 0.04959 0.04531 -0.0243 1.0000 0.0624
-7.000 -0.6085 0.04746 0.04312 -0.0215 1.0000 0.0640
-6.750 -0.6088 0.04560 0.04113 -0.0178 1.0000 0.0668
-6.250 -0.6014 0.03141 0.02509 -0.0088 0.9936 0.0314
-6.000 -0.5674 0.02631 0.01915 -0.0096 0.9867 0.0272
-5.750 -0.5279 0.02412 0.01657 -0.0115 0.9795 0.0267
-5.500 -0.4867 0.02187 0.01412 -0.0141 0.9737 0.0269
-5.250 -0.4484 0.02006 0.01230 -0.0163 0.9652 0.0282
-5.000 -0.4051 0.01873 0.01093 -0.0193 0.9594 0.0305
-4.750 -0.3684 0.01748 0.00968 -0.0211 0.9484 0.0344
-4.500 -0.3311 0.01647 0.00864 -0.0229 0.9372 0.0396
-4.250 -0.2976 0.01520 0.00743 -0.0241 0.9248 0.0497
-4.000 -0.2686 0.01400 0.00638 -0.0244 0.9104 0.0780
-3.750 -0.2485 0.01260 0.00555 -0.0233 0.8939 0.1814
-3.500 -0.2454 0.01073 0.00502 -0.0193 0.8761 0.4704
-3.250 -0.2340 0.01007 0.00529 -0.0149 0.8613 0.6969
-3.000 -0.2109 0.01029 0.00554 -0.0126 0.8486 0.7636
-2.750 -0.1875 0.01056 0.00573 -0.0106 0.8357 0.7979
-2.500 -0.1625 0.01087 0.00595 -0.0090 0.8233 0.8207
-2.250 -0.1363 0.01120 0.00616 -0.0075 0.8124 0.8391
-2.000 -0.1086 0.01155 0.00639 -0.0063 0.8026 0.8555
-1.750 -0.0779 0.01206 0.00683 -0.0054 0.7920 0.8730
-1.500 -0.0381 0.01267 0.00730 -0.0061 0.7834 0.8882
-1.250 -0.0031 0.01296 0.00748 -0.0067 0.7736 0.8991
-1.000 0.0414 0.01322 0.00761 -0.0095 0.7648 0.9048
-0.750 0.0685 0.01326 0.00755 -0.0092 0.7560 0.9134
-0.500 0.1139 0.01336 0.00755 -0.0126 0.7471 0.9164
-0.250 0.1531 0.01342 0.00749 -0.0148 0.7390 0.9206
0.000 0.1755 0.01341 0.00745 -0.0138 0.7301 0.9286
0.250 0.2168 0.01343 0.00735 -0.0165 0.7225 0.9312
0.500 0.2533 0.01343 0.00733 -0.0184 0.7134 0.9350
0.750 0.2815 0.01344 0.00724 -0.0185 0.7058 0.9408
1.000 0.3118 0.01339 0.00718 -0.0192 0.6954 0.9454
1.250 0.3482 0.01334 0.00707 -0.0210 0.6844 0.9486
1.500 0.3800 0.01328 0.00692 -0.0217 0.6726 0.9531
1.750 0.4044 0.01322 0.00682 -0.0211 0.6598 0.9590
2.000 0.4412 0.01312 0.00669 -0.0231 0.6465 0.9620
2.250 0.4748 0.01306 0.00661 -0.0243 0.6348 0.9660
2.500 0.5028 0.01303 0.00653 -0.0245 0.6241 0.9711
2.750 0.5371 0.01294 0.00644 -0.0260 0.6121 0.9747
3.000 0.5712 0.01286 0.00637 -0.0275 0.5993 0.9785
3.250 0.6014 0.01281 0.00633 -0.0282 0.5866 0.9831
3.500 0.6355 0.01270 0.00621 -0.0296 0.5719 0.9867
3.750 0.6694 0.01259 0.00612 -0.0311 0.5560 0.9906
4.000 0.7016 0.01251 0.00605 -0.0322 0.5378 0.9947
4.250 0.7361 0.01240 0.00590 -0.0339 0.5166 0.9984
4.500 0.7614 0.01237 0.00589 -0.0337 0.4915 1.0000
4.750 0.7796 0.01242 0.00591 -0.0320 0.4638 1.0000
5.000 0.7961 0.01257 0.00595 -0.0301 0.4250 1.0000
5.250 0.8099 0.01292 0.00606 -0.0278 0.3685 1.0000
5.500 0.8203 0.01356 0.00635 -0.0250 0.3058 1.0000
5.750 0.8302 0.01426 0.00677 -0.0223 0.2601 1.0000
6.000 0.8407 0.01489 0.00722 -0.0196 0.2311 1.0000
6.250 0.8505 0.01550 0.00768 -0.0167 0.2117 1.0000
6.500 0.8607 0.01603 0.00814 -0.0138 0.1971 1.0000
6.750 0.8712 0.01650 0.00858 -0.0110 0.1853 1.0000
7.000 0.8810 0.01702 0.00906 -0.0080 0.1760 1.0000
7.250 0.8905 0.01757 0.00954 -0.0050 0.1680 1.0000
7.500 0.9026 0.01805 0.01006 -0.0023 0.1603 1.0000
7.750 0.9145 0.01864 0.01058 0.0002 0.1536 1.0000
8.000 0.9288 0.01921 0.01119 0.0024 0.1474 1.0000
8.250 0.9435 0.01975 0.01173 0.0045 0.1413 1.0000
8.500 0.9588 0.02053 0.01247 0.0063 0.1358 1.0000
8.750 0.9755 0.02107 0.01310 0.0080 0.1305 1.0000
9.000 0.9921 0.02179 0.01377 0.0096 0.1255 1.0000
9.250 1.0098 0.02261 0.01464 0.0109 0.1207 1.0000
9.500 1.0265 0.02321 0.01532 0.0125 0.1158 1.0000
9.750 1.0445 0.02404 0.01612 0.0136 0.1116 1.0000
10.000 1.0626 0.02501 0.01719 0.0148 0.1074 1.0000
10.250 1.0782 0.02570 0.01800 0.0163 0.1033 1.0000
10.500 1.0949 0.02646 0.01875 0.0176 0.0994 1.0000
10.750 1.1150 0.02782 0.02014 0.0182 0.0956 1.0000
11.000 1.1263 0.02853 0.02105 0.0203 0.0922 1.0000
11.250 1.1385 0.02930 0.02191 0.0222 0.0889 1.0000
11.500 1.1542 0.03025 0.02283 0.0234 0.0858 1.0000
11.750 1.1686 0.03173 0.02444 0.0246 0.0828 1.0000
12.000 1.1752 0.03268 0.02560 0.0270 0.0802 1.0000
12.250 1.1833 0.03366 0.02670 0.0290 0.0775 1.0000
12.500 1.1943 0.03459 0.02764 0.0304 0.0750 1.0000
12.750 1.2088 0.03652 0.02962 0.0311 0.0721 1.0000
13.000 1.2083 0.03779 0.03113 0.0335 0.0703 1.0000
13.250 1.2101 0.03925 0.03279 0.0352 0.0682 1.0000
13.500 1.2139 0.04069 0.03435 0.0365 0.0661 1.0000
13.750 1.2217 0.04185 0.03551 0.0374 0.0640 1.0000
14.000 1.2291 0.04422 0.03793 0.0380 0.0617 1.0000
14.250 1.2217 0.04651 0.04049 0.0392 0.0605 1.0000
14.500 1.2152 0.04904 0.04325 0.0398 0.0591 1.0000
14.750 1.2094 0.05169 0.04610 0.0401 0.0575 1.0000
15.000 1.2062 0.05429 0.04883 0.0401 0.0561 1.0000
15.250 1.2099 0.05618 0.05074 0.0400 0.0545 1.0000
15.500 1.2147 0.05877 0.05331 0.0400 0.0527 1.0000
15.750 1.1979 0.06324 0.05803 0.0391 0.0521 1.0000
16.000 1.1784 0.06817 0.06321 0.0374 0.0516 1.0000
16.250 1.1557 0.07397 0.06926 0.0351 0.0512 1.0000
16.500 1.1292 0.08077 0.07632 0.0318 0.0509 1.0000
16.750 1.0965 0.08926 0.08504 0.0272 0.0509 1.0000
17.000 1.0541 0.10037 0.09639 0.0206 0.0513 1.0000
17.250 0.9954 0.11616 0.11237 0.0109 0.0523 1.0000
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Polar data table (+)
Polar graphs
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