AUGUST 160 (august160-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AUGUST 160 (august160-il) Reynolds number: 100,000 Max Cl/Cd: 34.71 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-august160-il-100000-n5.txt Download as CSV file: xf-august160-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AUGUST 160
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1558 0.09849 0.09237 -0.0442 0.5607 0.0624
-9.250 -0.1522 0.09532 0.08919 -0.0459 0.5534 0.0641
-9.000 -0.1635 0.09137 0.08528 -0.0504 0.5497 0.0663
-8.250 -0.1814 0.07249 0.06639 -0.0603 0.5385 0.0354
-8.000 -0.1822 0.06950 0.06338 -0.0607 0.5323 0.0347
-7.750 -0.1903 0.06618 0.05998 -0.0608 0.5280 0.0340
-7.500 -0.2196 0.05784 0.05135 -0.0625 0.5280 0.0310
-7.250 -0.2173 0.05493 0.04833 -0.0617 0.5221 0.0307
-7.000 -0.2139 0.05197 0.04520 -0.0608 0.5162 0.0304
-6.750 -0.2104 0.04874 0.04171 -0.0595 0.5112 0.0299
-6.500 -0.2059 0.04538 0.03799 -0.0579 0.5066 0.0295
-6.250 -0.1981 0.04222 0.03450 -0.0562 0.5008 0.0291
-6.000 -0.1881 0.03927 0.03114 -0.0543 0.4953 0.0288
-5.750 -0.1753 0.03665 0.02805 -0.0524 0.4904 0.0287
-5.500 -0.1595 0.03439 0.02536 -0.0506 0.4850 0.0286
-5.250 -0.1411 0.03243 0.02301 -0.0491 0.4791 0.0288
-5.000 -0.1208 0.03079 0.02099 -0.0477 0.4736 0.0291
-4.750 -0.0991 0.02938 0.01911 -0.0464 0.4690 0.0303
-4.500 -0.0758 0.02813 0.01755 -0.0453 0.4629 0.0313
-4.250 -0.0519 0.02728 0.01663 -0.0446 0.4574 0.0324
-4.000 -0.0271 0.02630 0.01542 -0.0437 0.4527 0.0332
-3.750 -0.0017 0.02542 0.01433 -0.0429 0.4485 0.0338
-3.500 0.0238 0.02461 0.01341 -0.0422 0.4434 0.0347
-3.250 0.0489 0.02390 0.01256 -0.0413 0.4387 0.0356
-3.000 0.0729 0.02330 0.01193 -0.0405 0.4347 0.0368
-2.750 0.0970 0.02283 0.01133 -0.0396 0.4312 0.0384
-2.500 0.1208 0.02243 0.01087 -0.0386 0.4267 0.0404
-2.250 0.1445 0.02207 0.01052 -0.0377 0.4223 0.0442
-2.000 0.1684 0.02175 0.01014 -0.0368 0.4185 0.0494
-1.750 0.1925 0.02141 0.00972 -0.0359 0.4154 0.0575
-1.500 0.2161 0.02093 0.00934 -0.0349 0.4128 0.0811
-1.250 0.2390 0.02036 0.00924 -0.0341 0.4095 0.1865
-1.000 0.3087 0.01861 0.01007 -0.0402 0.4046 0.9037
-0.750 0.3680 0.01910 0.01025 -0.0452 0.4006 0.9529
-0.500 0.4272 0.01931 0.01013 -0.0511 0.3972 0.9728
-0.250 0.5007 0.01941 0.00984 -0.0600 0.3939 0.9954
0.000 0.5335 0.01959 0.00994 -0.0614 0.3906 1.0000
0.250 0.5544 0.01980 0.01007 -0.0603 0.3877 1.0000
0.500 0.5755 0.02002 0.01019 -0.0592 0.3850 1.0000
0.750 0.5968 0.02024 0.01030 -0.0581 0.3825 1.0000
1.000 0.6183 0.02046 0.01040 -0.0571 0.3804 1.0000
1.250 0.6400 0.02070 0.01051 -0.0561 0.3785 1.0000
1.500 0.6619 0.02097 0.01064 -0.0551 0.3769 1.0000
1.750 0.6828 0.02133 0.01094 -0.0540 0.3750 1.0000
2.000 0.7025 0.02174 0.01138 -0.0528 0.3729 1.0000
2.250 0.7222 0.02217 0.01181 -0.0516 0.3707 1.0000
2.500 0.7420 0.02259 0.01222 -0.0503 0.3687 1.0000
2.750 0.7618 0.02301 0.01263 -0.0491 0.3668 1.0000
3.000 0.7819 0.02343 0.01301 -0.0479 0.3650 1.0000
3.250 0.8020 0.02384 0.01338 -0.0467 0.3634 1.0000
3.500 0.8226 0.02422 0.01371 -0.0456 0.3619 1.0000
3.750 0.8438 0.02458 0.01400 -0.0446 0.3604 1.0000
4.000 0.8656 0.02494 0.01427 -0.0436 0.3590 1.0000
4.250 0.8834 0.02553 0.01489 -0.0422 0.3572 1.0000
4.500 0.8980 0.02628 0.01576 -0.0404 0.3552 1.0000
4.750 0.9129 0.02705 0.01662 -0.0387 0.3534 1.0000
5.000 0.9279 0.02781 0.01745 -0.0370 0.3517 1.0000
5.250 0.9430 0.02857 0.01827 -0.0354 0.3500 1.0000
5.500 0.9588 0.02927 0.01900 -0.0338 0.3483 1.0000
5.750 0.9754 0.02991 0.01966 -0.0324 0.3467 1.0000
6.000 0.9934 0.03045 0.02021 -0.0311 0.3452 1.0000
6.250 1.0123 0.03098 0.02073 -0.0299 0.3439 1.0000
6.500 1.0322 0.03151 0.02124 -0.0289 0.3427 1.0000
6.750 1.0525 0.03209 0.02179 -0.0280 0.3417 1.0000
7.000 1.0609 0.03330 0.02313 -0.0259 0.3402 1.0000
7.250 1.0493 0.03551 0.02561 -0.0218 0.3376 1.0000
7.500 1.0323 0.03801 0.02832 -0.0176 0.3347 1.0000
7.750 1.0093 0.04073 0.03119 -0.0132 0.3318 1.0000
8.000 0.9775 0.04408 0.03465 -0.0089 0.3290 1.0000
8.250 0.9649 0.04699 0.03761 -0.0072 0.3269 1.0000
8.500 0.9730 0.04854 0.03917 -0.0065 0.3256 1.0000
8.750 0.9893 0.04947 0.04010 -0.0059 0.3247 1.0000
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Polar data table (+)
Polar graphs
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