E387 (e387-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 200,000 Max Cl/Cd: 84.35 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e387-il-200000.txt Download as CSV file: xf-e387-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2667 0.09393 0.09074 -0.0316 1.0000 0.0394
-9.000 -0.2708 0.09096 0.08781 -0.0345 1.0000 0.0400
-8.750 -0.2727 0.08774 0.08463 -0.0368 1.0000 0.0403
-8.500 -0.2740 0.08442 0.08136 -0.0386 1.0000 0.0404
-8.250 -0.2755 0.08102 0.07802 -0.0403 1.0000 0.0405
-8.000 -0.2713 0.07486 0.07190 -0.0386 1.0000 0.0416
-7.750 -0.2637 0.07168 0.06876 -0.0372 1.0000 0.0426
-7.500 -0.2620 0.06891 0.06605 -0.0363 1.0000 0.0437
-7.250 -0.2742 0.06743 0.06471 -0.0336 1.0000 0.0443
-7.000 -0.3570 0.07594 0.07304 -0.0424 1.0000 0.0413
-6.750 -0.3559 0.07384 0.07100 -0.0392 0.9977 0.0422
-6.500 -0.3270 0.06980 0.06694 -0.0438 0.9898 0.0441
-6.250 -0.2923 0.06430 0.06137 -0.0537 0.9798 0.0471
-6.000 -0.2352 0.05551 0.05197 -0.0765 0.9640 0.0524
-5.750 -0.2153 0.04957 0.04624 -0.0785 0.9563 0.0549
-5.500 -0.1851 0.04671 0.04331 -0.0817 0.9439 0.0601
-5.250 -0.1536 0.04074 0.03688 -0.0886 0.9282 0.0676
-5.000 -0.1298 0.03822 0.03430 -0.0894 0.9131 0.0707
-4.750 -0.1051 0.03475 0.03025 -0.0914 0.8964 0.0806
-4.500 -0.0839 0.03235 0.02783 -0.0911 0.8823 0.0834
-4.250 -0.0602 0.03008 0.02508 -0.0914 0.8687 0.0949
-4.000 -0.0274 0.02029 0.01380 -0.0897 0.8583 0.0346
-3.750 -0.0006 0.01802 0.01092 -0.0887 0.8466 0.0323
-3.500 0.0256 0.01663 0.00925 -0.0880 0.8358 0.0324
-3.250 0.0518 0.01553 0.00797 -0.0873 0.8260 0.0336
-3.000 0.0782 0.01494 0.00728 -0.0868 0.8152 0.0377
-2.750 0.1049 0.01430 0.00649 -0.0862 0.8055 0.0405
-2.500 0.1305 0.01327 0.00541 -0.0856 0.7973 0.0466
-2.250 0.1570 0.01231 0.00459 -0.0851 0.7876 0.0881
-2.000 0.1824 0.01149 0.00430 -0.0850 0.7796 0.2303
-1.750 0.2059 0.01064 0.00426 -0.0846 0.7712 0.4548
-1.500 0.2245 0.00983 0.00430 -0.0824 0.7634 0.7077
-1.250 0.2697 0.00923 0.00404 -0.0845 0.7563 0.9956
-1.000 0.2972 0.00934 0.00394 -0.0845 0.7485 1.0000
-0.750 0.3239 0.00945 0.00384 -0.0842 0.7413 1.0000
-0.500 0.3506 0.00958 0.00381 -0.0840 0.7339 1.0000
-0.250 0.3775 0.00970 0.00377 -0.0837 0.7269 1.0000
0.000 0.4044 0.00984 0.00378 -0.0835 0.7199 1.0000
0.250 0.4314 0.00997 0.00379 -0.0833 0.7132 1.0000
0.500 0.4584 0.01012 0.00384 -0.0831 0.7067 1.0000
0.750 0.4855 0.01025 0.00389 -0.0830 0.6998 1.0000
1.000 0.5127 0.01042 0.00395 -0.0828 0.6940 1.0000
1.250 0.5397 0.01057 0.00406 -0.0827 0.6868 1.0000
1.500 0.5671 0.01073 0.00412 -0.0825 0.6814 1.0000
1.750 0.5939 0.01090 0.00430 -0.0824 0.6742 1.0000
2.000 0.6213 0.01105 0.00439 -0.0822 0.6683 1.0000
2.250 0.6482 0.01124 0.00457 -0.0821 0.6617 1.0000
2.500 0.6753 0.01140 0.00470 -0.0819 0.6552 1.0000
2.750 0.7024 0.01158 0.00489 -0.0818 0.6488 1.0000
3.000 0.7292 0.01173 0.00504 -0.0816 0.6416 1.0000
3.250 0.7562 0.01190 0.00520 -0.0814 0.6348 1.0000
3.500 0.7829 0.01204 0.00536 -0.0811 0.6269 1.0000
3.750 0.8097 0.01219 0.00554 -0.0809 0.6191 1.0000
4.000 0.8365 0.01230 0.00565 -0.0805 0.6109 1.0000
4.250 0.8627 0.01244 0.00585 -0.0802 0.6019 1.0000
4.500 0.8899 0.01254 0.00591 -0.0799 0.5941 1.0000
4.750 0.9157 0.01263 0.00612 -0.0795 0.5836 1.0000
5.000 0.9417 0.01273 0.00628 -0.0791 0.5733 1.0000
5.250 0.9680 0.01280 0.00638 -0.0786 0.5630 1.0000
5.500 0.9940 0.01286 0.00648 -0.0781 0.5517 1.0000
5.750 1.0194 0.01292 0.00667 -0.0776 0.5388 1.0000
6.000 1.0445 0.01295 0.00675 -0.0769 0.5233 1.0000
6.250 1.0680 0.01292 0.00679 -0.0759 0.4989 1.0000
6.500 1.0908 0.01297 0.00684 -0.0748 0.4684 1.0000
6.750 1.1126 0.01319 0.00703 -0.0737 0.4294 1.0000
7.000 1.1332 0.01362 0.00735 -0.0725 0.3830 1.0000
7.250 1.1481 0.01457 0.00791 -0.0706 0.3037 1.0000
7.500 1.1588 0.01602 0.00888 -0.0685 0.2213 1.0000
7.750 1.1671 0.01774 0.01010 -0.0663 0.1415 1.0000
8.000 1.1667 0.02026 0.01192 -0.0629 0.0532 1.0000
8.250 1.1733 0.02205 0.01359 -0.0601 0.0365 1.0000
8.500 1.1835 0.02337 0.01504 -0.0577 0.0322 1.0000
8.750 1.1921 0.02463 0.01639 -0.0552 0.0299 1.0000
9.000 1.1958 0.02608 0.01791 -0.0522 0.0283 1.0000
9.250 1.1953 0.02801 0.01989 -0.0490 0.0271 1.0000
9.500 1.1998 0.02989 0.02185 -0.0465 0.0264 1.0000
9.750 1.2102 0.03144 0.02350 -0.0447 0.0257 1.0000
10.000 1.2222 0.03303 0.02522 -0.0432 0.0250 1.0000
10.250 1.2345 0.03455 0.02685 -0.0418 0.0236 1.0000
10.500 1.2495 0.03634 0.02875 -0.0405 0.0229 1.0000
10.750 1.2665 0.03831 0.03086 -0.0393 0.0224 1.0000
11.000 1.2846 0.04056 0.03329 -0.0383 0.0221 1.0000
11.250 1.3019 0.04321 0.03617 -0.0373 0.0220 1.0000
11.500 1.3147 0.04631 0.03958 -0.0360 0.0221 1.0000
11.750 1.3190 0.04991 0.04355 -0.0344 0.0224 1.0000
12.000 1.3154 0.05391 0.04796 -0.0325 0.0230 1.0000
12.250 1.3066 0.05809 0.05249 -0.0310 0.0235 1.0000
12.500 1.2946 0.06254 0.05725 -0.0300 0.0240 1.0000
12.750 1.2801 0.06729 0.06228 -0.0295 0.0245 1.0000
13.000 1.2639 0.07234 0.06757 -0.0297 0.0249 1.0000
13.250 1.2461 0.07779 0.07324 -0.0306 0.0253 1.0000
13.500 1.2269 0.08368 0.07933 -0.0321 0.0256 1.0000
13.750 1.2069 0.09018 0.08602 -0.0342 0.0260 1.0000
14.000 1.2096 0.09456 0.09051 -0.0347 0.0273 1.0000
14.250 1.1750 0.10244 0.09874 -0.0398 0.0283 1.0000
14.500 1.1416 0.11207 0.10858 -0.0461 0.0286 1.0000
14.750 1.1116 0.12263 0.11931 -0.0534 0.0287 1.0000
15.000 1.0142 0.16314 0.15995 -0.0792 0.0386 1.0000
15.250 1.0394 0.15676 0.15366 -0.0744 0.0366 1.0000
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