E176 (8.83%) (e176-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 200,000 Max Cl/Cd: 81.15 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e176-il-200000.txt Download as CSV file: xf-e176-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4095 0.10752 0.10406 -0.0172 1.0000 0.0392
-9.250 -0.4095 0.10475 0.10134 -0.0211 1.0000 0.0399
-9.000 -0.4083 0.10156 0.09821 -0.0243 1.0000 0.0401
-8.750 -0.4060 0.09826 0.09495 -0.0271 1.0000 0.0402
-8.500 -0.4049 0.09473 0.09148 -0.0301 1.0000 0.0403
-8.250 -0.3964 0.08862 0.08538 -0.0266 1.0000 0.0419
-8.000 -0.3879 0.08572 0.08251 -0.0263 1.0000 0.0430
-7.750 -0.3832 0.08279 0.07962 -0.0272 1.0000 0.0440
-7.500 -0.3811 0.07982 0.07670 -0.0282 1.0000 0.0456
-7.250 -0.3799 0.07657 0.07352 -0.0305 1.0000 0.0469
-7.000 -0.3758 0.07277 0.06977 -0.0345 1.0000 0.0485
-6.750 -0.3711 0.06842 0.06546 -0.0402 1.0000 0.0505
-6.500 -0.3631 0.06323 0.06002 -0.0516 0.9943 0.0525
-6.250 -0.3414 0.05590 0.05275 -0.0563 0.9852 0.0543
-6.000 -0.3121 0.05354 0.05042 -0.0583 0.9752 0.0580
-5.750 -0.2717 0.04573 0.04195 -0.0707 0.9589 0.0668
-5.500 -0.2441 0.04233 0.03862 -0.0727 0.9457 0.0690
-5.250 -0.2168 0.03947 0.03560 -0.0747 0.9301 0.0734
-5.000 -0.1940 0.03564 0.03129 -0.0765 0.9131 0.0818
-4.750 -0.1733 0.03351 0.02907 -0.0761 0.8974 0.0853
-4.500 -0.1522 0.03102 0.02616 -0.0760 0.8829 0.0959
-4.250 -0.1207 0.02185 0.01542 -0.0737 0.8724 0.0385
-4.000 -0.0962 0.01959 0.01275 -0.0728 0.8602 0.0372
-3.750 -0.0706 0.01797 0.01076 -0.0719 0.8491 0.0370
-3.500 -0.0445 0.01716 0.00967 -0.0711 0.8389 0.0391
-3.250 -0.0184 0.01617 0.00846 -0.0703 0.8294 0.0399
-3.000 0.0079 0.01517 0.00735 -0.0697 0.8193 0.0404
-2.750 0.0328 0.01390 0.00603 -0.0689 0.8107 0.0428
-2.500 0.0588 0.01329 0.00535 -0.0683 0.8020 0.0474
-2.250 0.0853 0.01268 0.00470 -0.0679 0.7933 0.0596
-2.000 0.1092 0.01138 0.00419 -0.0675 0.7861 0.2513
-1.750 0.1325 0.01057 0.00414 -0.0670 0.7774 0.4620
-1.500 0.1503 0.00971 0.00414 -0.0645 0.7709 0.7146
-1.250 0.2090 0.00912 0.00392 -0.0696 0.7633 1.0000
-1.000 0.2343 0.00923 0.00380 -0.0690 0.7567 1.0000
-0.750 0.2603 0.00933 0.00375 -0.0687 0.7486 1.0000
-0.500 0.2863 0.00945 0.00368 -0.0682 0.7424 1.0000
-0.250 0.3127 0.00956 0.00369 -0.0680 0.7345 1.0000
0.000 0.3390 0.00969 0.00365 -0.0675 0.7288 1.0000
0.250 0.3656 0.00981 0.00371 -0.0674 0.7211 1.0000
0.500 0.3923 0.00995 0.00371 -0.0670 0.7153 1.0000
0.750 0.4191 0.01009 0.00381 -0.0669 0.7081 1.0000
1.000 0.4459 0.01022 0.00385 -0.0666 0.7020 1.0000
1.250 0.4727 0.01038 0.00397 -0.0664 0.6954 1.0000
1.500 0.4996 0.01052 0.00405 -0.0662 0.6890 1.0000
1.750 0.5266 0.01069 0.00417 -0.0660 0.6829 1.0000
2.000 0.5535 0.01084 0.00431 -0.0658 0.6760 1.0000
2.250 0.5805 0.01100 0.00442 -0.0656 0.6702 1.0000
2.500 0.6073 0.01115 0.00459 -0.0654 0.6624 1.0000
2.750 0.6343 0.01129 0.00468 -0.0651 0.6561 1.0000
3.000 0.6609 0.01142 0.00487 -0.0649 0.6477 1.0000
3.250 0.6877 0.01156 0.00499 -0.0646 0.6404 1.0000
3.500 0.7144 0.01166 0.00510 -0.0642 0.6317 1.0000
3.750 0.7409 0.01177 0.00525 -0.0639 0.6227 1.0000
4.000 0.7679 0.01186 0.00533 -0.0635 0.6148 1.0000
4.250 0.7941 0.01195 0.00551 -0.0632 0.6044 1.0000
4.500 0.8205 0.01204 0.00565 -0.0628 0.5944 1.0000
4.750 0.8470 0.01209 0.00572 -0.0624 0.5841 1.0000
5.000 0.8733 0.01213 0.00581 -0.0619 0.5726 1.0000
5.250 0.8993 0.01217 0.00594 -0.0614 0.5595 1.0000
5.500 0.9251 0.01221 0.00605 -0.0608 0.5452 1.0000
5.750 0.9504 0.01223 0.00615 -0.0602 0.5274 1.0000
6.000 0.9748 0.01221 0.00618 -0.0593 0.5008 1.0000
6.250 0.9981 0.01230 0.00626 -0.0583 0.4626 1.0000
6.500 1.0197 0.01264 0.00645 -0.0572 0.4068 1.0000
6.750 1.0360 0.01358 0.00691 -0.0556 0.3114 1.0000
7.000 1.0489 0.01507 0.00784 -0.0540 0.2156 1.0000
7.250 1.0618 0.01663 0.00895 -0.0524 0.1354 1.0000
7.500 1.0645 0.01934 0.01087 -0.0496 0.0406 1.0000
7.750 1.0767 0.02092 0.01250 -0.0474 0.0306 1.0000
8.000 1.0925 0.02200 0.01368 -0.0459 0.0266 1.0000
8.250 1.1033 0.02345 0.01519 -0.0439 0.0236 1.0000
8.500 1.1101 0.02527 0.01709 -0.0413 0.0224 1.0000
8.750 1.1219 0.02666 0.01859 -0.0393 0.0218 1.0000
9.000 1.1331 0.02815 0.02018 -0.0372 0.0212 1.0000
9.250 1.1465 0.02984 0.02200 -0.0353 0.0206 1.0000
9.500 1.1639 0.03175 0.02402 -0.0340 0.0203 1.0000
9.750 1.1848 0.03400 0.02645 -0.0332 0.0201 1.0000
10.000 1.2065 0.03671 0.02940 -0.0325 0.0201 1.0000
10.250 1.2241 0.03981 0.03280 -0.0315 0.0205 1.0000
10.500 1.2356 0.04327 0.03660 -0.0300 0.0209 1.0000
10.750 1.2403 0.04709 0.04075 -0.0281 0.0214 1.0000
11.000 1.2388 0.05109 0.04506 -0.0259 0.0219 1.0000
11.250 1.2323 0.05505 0.04929 -0.0236 0.0222 1.0000
11.500 1.2294 0.06061 0.05510 -0.0224 0.0227 1.0000
11.750 1.2240 0.06258 0.05724 -0.0205 0.0229 1.0000
12.000 1.2150 0.06510 0.06000 -0.0192 0.0231 1.0000
12.250 1.1974 0.06953 0.06466 -0.0188 0.0230 1.0000
12.500 1.1840 0.07316 0.06849 -0.0189 0.0232 1.0000
12.750 1.0371 0.07706 0.07314 -0.0175 0.0251 1.0000
13.000 1.0006 0.08540 0.08174 -0.0208 0.0257 1.0000
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Polar data table (+)
Polar graphs
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