E387 (e387-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 100,000 Max Cl/Cd: 60.95 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e387-il-100000-n5.txt Download as CSV file: xf-e387-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E387
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3381 0.09095 0.08633 -0.0331 1.0000 0.0499
-7.750 -0.3356 0.08800 0.08344 -0.0338 1.0000 0.0504
-7.500 -0.3359 0.08516 0.08069 -0.0343 1.0000 0.0508
-7.250 -0.3394 0.08244 0.07808 -0.0347 1.0000 0.0509
-7.000 -0.3418 0.07955 0.07530 -0.0359 1.0000 0.0508
-6.500 -0.3175 0.06403 0.05970 -0.0545 0.9790 0.0269
-6.250 -0.2922 0.05927 0.05486 -0.0602 0.9645 0.0259
-6.000 -0.2644 0.05334 0.04877 -0.0676 0.9490 0.0248
-5.750 -0.2355 0.04672 0.04185 -0.0746 0.9337 0.0237
-5.500 -0.2070 0.03972 0.03434 -0.0803 0.9189 0.0225
-5.250 -0.1789 0.03314 0.02689 -0.0838 0.9048 0.0215
-5.000 -0.1513 0.03018 0.02350 -0.0853 0.8918 0.0219
-4.750 -0.1237 0.02823 0.02119 -0.0862 0.8790 0.0235
-4.500 -0.0957 0.02583 0.01825 -0.0866 0.8671 0.0249
-4.250 -0.0678 0.02362 0.01551 -0.0866 0.8559 0.0254
-4.000 -0.0407 0.02183 0.01330 -0.0862 0.8439 0.0259
-3.750 -0.0136 0.02039 0.01152 -0.0858 0.8327 0.0266
-3.500 0.0131 0.01913 0.01003 -0.0853 0.8226 0.0278
-3.250 0.0396 0.01820 0.00899 -0.0850 0.8126 0.0300
-3.000 0.0663 0.01757 0.00820 -0.0846 0.8022 0.0350
-2.750 0.0929 0.01679 0.00733 -0.0843 0.7932 0.0417
-2.500 0.1198 0.01603 0.00646 -0.0838 0.7841 0.0579
-2.250 0.1458 0.01526 0.00603 -0.0837 0.7751 0.1292
-2.000 0.1715 0.01454 0.00575 -0.0835 0.7675 0.2503
-1.750 0.1967 0.01397 0.00558 -0.0832 0.7585 0.3842
-1.500 0.2201 0.01333 0.00544 -0.0821 0.7513 0.5649
-1.250 0.2394 0.01269 0.00542 -0.0792 0.7432 0.7821
-1.000 0.2876 0.01237 0.00503 -0.0826 0.7366 1.0000
-0.750 0.3140 0.01248 0.00491 -0.0823 0.7283 1.0000
-0.500 0.3409 0.01261 0.00479 -0.0820 0.7217 1.0000
-0.250 0.3675 0.01274 0.00475 -0.0818 0.7139 1.0000
0.000 0.3944 0.01288 0.00468 -0.0816 0.7077 1.0000
0.250 0.4210 0.01303 0.00471 -0.0814 0.7001 1.0000
0.500 0.4481 0.01318 0.00469 -0.0812 0.6943 1.0000
0.750 0.4746 0.01335 0.00479 -0.0810 0.6867 1.0000
1.000 0.5016 0.01351 0.00482 -0.0808 0.6808 1.0000
1.250 0.5283 0.01370 0.00495 -0.0806 0.6739 1.0000
1.500 0.5551 0.01388 0.00505 -0.0804 0.6676 1.0000
1.750 0.5819 0.01407 0.00519 -0.0802 0.6615 1.0000
2.000 0.6085 0.01427 0.00536 -0.0800 0.6547 1.0000
2.250 0.6356 0.01446 0.00549 -0.0798 0.6493 1.0000
2.500 0.6618 0.01469 0.00575 -0.0796 0.6420 1.0000
2.750 0.6888 0.01488 0.00592 -0.0794 0.6364 1.0000
3.000 0.7150 0.01513 0.00621 -0.0792 0.6292 1.0000
3.250 0.7417 0.01533 0.00641 -0.0789 0.6230 1.0000
3.500 0.7678 0.01557 0.00671 -0.0787 0.6157 1.0000
3.750 0.7943 0.01577 0.00696 -0.0784 0.6086 1.0000
4.000 0.8202 0.01600 0.00726 -0.0781 0.6004 1.0000
4.250 0.8467 0.01617 0.00745 -0.0777 0.5927 1.0000
4.500 0.8720 0.01639 0.00782 -0.0773 0.5828 1.0000
4.750 0.8977 0.01656 0.00806 -0.0768 0.5733 1.0000
5.000 0.9237 0.01670 0.00825 -0.0763 0.5634 1.0000
5.250 0.9485 0.01688 0.00857 -0.0757 0.5514 1.0000
5.500 0.9734 0.01705 0.00888 -0.0751 0.5387 1.0000
5.750 0.9980 0.01720 0.00915 -0.0744 0.5248 1.0000
6.000 1.0224 0.01735 0.00942 -0.0736 0.5094 1.0000
6.250 1.0465 0.01750 0.00967 -0.0728 0.4922 1.0000
6.500 1.0697 0.01771 0.01006 -0.0719 0.4716 1.0000
6.750 1.0923 0.01793 0.01037 -0.0709 0.4476 1.0000
7.000 1.1123 0.01825 0.01068 -0.0695 0.4075 1.0000
7.250 1.1282 0.01890 0.01107 -0.0676 0.3417 1.0000
7.500 1.1368 0.02029 0.01188 -0.0651 0.2553 1.0000
7.750 1.1439 0.02201 0.01314 -0.0628 0.1838 1.0000
8.000 1.1510 0.02374 0.01446 -0.0607 0.1246 1.0000
8.250 1.1597 0.02530 0.01579 -0.0586 0.0840 1.0000
8.500 1.1670 0.02693 0.01725 -0.0564 0.0551 1.0000
8.750 1.1731 0.02859 0.01886 -0.0540 0.0398 1.0000
9.000 1.1756 0.03029 0.02053 -0.0511 0.0335 1.0000
9.250 1.1808 0.03184 0.02224 -0.0487 0.0300 1.0000
9.500 1.1850 0.03352 0.02404 -0.0466 0.0273 1.0000
9.750 1.1865 0.03552 0.02614 -0.0446 0.0255 1.0000
10.000 1.1910 0.03738 0.02816 -0.0430 0.0238 1.0000
10.250 1.1952 0.03936 0.03031 -0.0416 0.0226 1.0000
10.500 1.1990 0.04150 0.03259 -0.0404 0.0218 1.0000
10.750 1.2029 0.04372 0.03495 -0.0392 0.0211 1.0000
11.000 1.2072 0.04601 0.03735 -0.0382 0.0205 1.0000
11.250 1.2117 0.04839 0.03983 -0.0373 0.0199 1.0000
11.500 1.2172 0.05083 0.04237 -0.0363 0.0195 1.0000
11.750 1.2247 0.05334 0.04498 -0.0352 0.0190 1.0000
12.000 1.2338 0.05579 0.04767 -0.0343 0.0188 1.0000
12.250 1.2416 0.05852 0.05064 -0.0334 0.0185 1.0000
12.500 1.2466 0.06155 0.05394 -0.0328 0.0182 1.0000
12.750 1.2478 0.06497 0.05765 -0.0325 0.0179 1.0000
13.000 1.2457 0.06872 0.06167 -0.0325 0.0176 1.0000
13.250 1.2402 0.07281 0.06605 -0.0329 0.0172 1.0000
13.500 1.2327 0.07728 0.07078 -0.0337 0.0170 1.0000
13.750 1.2229 0.08215 0.07590 -0.0350 0.0167 1.0000
14.000 1.2109 0.08749 0.08150 -0.0368 0.0166 1.0000
14.250 1.1972 0.09332 0.08757 -0.0392 0.0165 1.0000
14.500 1.1812 0.09989 0.09438 -0.0422 0.0165 1.0000
14.750 1.1634 0.10725 0.10198 -0.0461 0.0166 1.0000
15.000 1.1441 0.11552 0.11048 -0.0509 0.0167 1.0000
15.250 1.1228 0.12498 0.12014 -0.0568 0.0170 1.0000
15.500 1.1005 0.13566 0.13100 -0.0638 0.0174 1.0000
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Polar data table (+)
Polar graphs
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