AUGUST 160 (august160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AUGUST 160 (august160-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.17 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-august160-il-1000000-n5.txt Download as CSV file: xf-august160-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4918 0.03717 0.03306 -0.0828 0.4648 0.0081
-10.500 -0.5099 0.03465 0.03036 -0.0784 0.4617 0.0082
-10.250 -0.5239 0.03193 0.02740 -0.0743 0.4573 0.0081
-10.000 -0.5288 0.02940 0.02458 -0.0708 0.4521 0.0082
-9.750 -0.5241 0.02759 0.02255 -0.0680 0.4467 0.0082
-9.500 -0.5162 0.02591 0.02063 -0.0655 0.4394 0.0082
-9.250 -0.5035 0.02466 0.01918 -0.0634 0.4330 0.0083
-9.000 -0.4875 0.02367 0.01802 -0.0617 0.4276 0.0083
-8.750 -0.4740 0.02225 0.01639 -0.0596 0.4220 0.0083
-8.500 -0.4616 0.02059 0.01448 -0.0573 0.4158 0.0085
-8.250 -0.4433 0.01959 0.01332 -0.0557 0.4110 0.0085
-8.000 -0.4231 0.01877 0.01237 -0.0543 0.4062 0.0086
-7.750 -0.4013 0.01818 0.01168 -0.0532 0.4010 0.0087
-7.500 -0.3800 0.01744 0.01080 -0.0519 0.3954 0.0087
-7.250 -0.3567 0.01697 0.01026 -0.0510 0.3914 0.0088
-7.000 -0.3336 0.01642 0.00960 -0.0499 0.3871 0.0089
-6.750 -0.3095 0.01604 0.00915 -0.0491 0.3825 0.0090
-6.500 -0.2850 0.01572 0.00875 -0.0483 0.3778 0.0092
-6.250 -0.2607 0.01529 0.00825 -0.0474 0.3745 0.0093
-6.000 -0.2361 0.01486 0.00774 -0.0466 0.3711 0.0095
-5.750 -0.2115 0.01444 0.00725 -0.0458 0.3674 0.0096
-5.500 -0.1869 0.01404 0.00677 -0.0449 0.3633 0.0097
-5.250 -0.1622 0.01367 0.00632 -0.0441 0.3594 0.0098
-5.000 -0.1371 0.01331 0.00591 -0.0433 0.3566 0.0099
-4.750 -0.1117 0.01299 0.00553 -0.0426 0.3537 0.0102
-4.500 -0.0863 0.01270 0.00519 -0.0419 0.3506 0.0103
-4.250 -0.0607 0.01245 0.00489 -0.0412 0.3473 0.0105
-4.000 -0.0351 0.01223 0.00462 -0.0405 0.3438 0.0106
-3.750 -0.0092 0.01204 0.00438 -0.0399 0.3406 0.0107
-3.500 0.0170 0.01186 0.00417 -0.0393 0.3384 0.0109
-3.250 0.0422 0.01156 0.00384 -0.0386 0.3357 0.0112
-3.000 0.0680 0.01134 0.00360 -0.0379 0.3330 0.0114
-2.750 0.0941 0.01120 0.00343 -0.0374 0.3305 0.0117
-2.500 0.1204 0.01107 0.00327 -0.0368 0.3279 0.0119
-2.250 0.1467 0.01096 0.00313 -0.0363 0.3252 0.0122
-2.000 0.1733 0.01085 0.00301 -0.0358 0.3236 0.0124
-1.750 0.2000 0.01075 0.00290 -0.0354 0.3222 0.0127
-1.500 0.2268 0.01066 0.00279 -0.0350 0.3207 0.0130
-1.250 0.2536 0.01059 0.00271 -0.0346 0.3189 0.0134
-1.000 0.2803 0.01052 0.00262 -0.0341 0.3171 0.0141
-0.750 0.3070 0.01046 0.00255 -0.0337 0.3152 0.0147
-0.500 0.3337 0.01042 0.00250 -0.0333 0.3134 0.0156
-0.250 0.3604 0.01040 0.00246 -0.0329 0.3114 0.0172
0.000 0.3862 0.01030 0.00243 -0.0323 0.3094 0.0384
0.250 0.4115 0.01016 0.00241 -0.0317 0.3078 0.0805
0.500 0.4381 0.01008 0.00240 -0.0314 0.3070 0.1093
0.750 0.4643 0.00999 0.00241 -0.0309 0.3059 0.1466
1.000 0.4896 0.00985 0.00242 -0.0304 0.3049 0.2014
1.250 0.5099 0.00936 0.00244 -0.0290 0.3036 0.3790
1.500 0.5274 0.00883 0.00246 -0.0270 0.3024 0.5685
1.750 0.5312 0.00801 0.00253 -0.0218 0.3013 0.8368
2.000 0.5571 0.00800 0.00266 -0.0210 0.3000 0.9030
2.250 0.5852 0.00808 0.00274 -0.0209 0.2984 0.9201
2.500 0.6144 0.00818 0.00283 -0.0211 0.2969 0.9333
2.750 0.6442 0.00830 0.00293 -0.0214 0.2953 0.9452
3.000 0.6715 0.00841 0.00302 -0.0212 0.2937 0.9537
3.250 0.7047 0.00855 0.00314 -0.0223 0.2921 0.9595
3.500 0.7320 0.00863 0.00321 -0.0221 0.2915 0.9654
3.750 0.7678 0.00874 0.00331 -0.0238 0.2904 0.9682
4.000 0.8011 0.00884 0.00340 -0.0250 0.2889 0.9715
4.250 0.8311 0.00894 0.00349 -0.0255 0.2877 0.9746
4.500 0.8633 0.00905 0.00358 -0.0265 0.2852 0.9771
4.750 0.8977 0.00918 0.00368 -0.0280 0.2833 0.9781
5.000 0.9293 0.00932 0.00379 -0.0289 0.2805 0.9789
5.250 0.9609 0.00948 0.00392 -0.0299 0.2778 0.9800
5.500 0.9921 0.00961 0.00404 -0.0308 0.2767 0.9811
5.750 1.0244 0.00973 0.00417 -0.0318 0.2757 0.9830
6.000 1.0552 0.00985 0.00429 -0.0326 0.2747 0.9852
6.250 1.0866 0.00998 0.00443 -0.0335 0.2738 0.9865
6.500 1.1196 0.01012 0.00458 -0.0348 0.2726 0.9875
6.750 1.1533 0.01027 0.00473 -0.0363 0.2717 0.9889
7.000 1.1839 0.01041 0.00488 -0.0371 0.2707 0.9900
7.250 1.2136 0.01056 0.00504 -0.0378 0.2696 0.9912
7.500 1.2428 0.01071 0.00520 -0.0384 0.2687 0.9925
7.750 1.2717 0.01087 0.00538 -0.0389 0.2677 0.9938
8.000 1.3000 0.01104 0.00556 -0.0394 0.2667 0.9959
8.250 1.3291 0.01124 0.00576 -0.0400 0.2650 0.9979
8.500 1.3587 0.01145 0.00597 -0.0408 0.2635 0.9991
8.750 1.3885 0.01162 0.00617 -0.0416 0.2619 1.0000
9.000 1.4083 0.01174 0.00633 -0.0403 0.2605 1.0000
9.250 1.4275 0.01188 0.00650 -0.0388 0.2591 1.0000
9.500 1.4469 0.01204 0.00669 -0.0375 0.2584 1.0000
9.750 1.4672 0.01221 0.00689 -0.0364 0.2568 1.0000
10.000 1.4880 0.01239 0.00710 -0.0354 0.2555 1.0000
10.250 1.5088 0.01260 0.00732 -0.0344 0.2533 1.0000
10.500 1.5292 0.01284 0.00757 -0.0334 0.2509 1.0000
10.750 1.5490 0.01312 0.00786 -0.0324 0.2485 1.0000
11.000 1.5712 0.01329 0.00809 -0.0317 0.2469 1.0000
11.250 1.5928 0.01350 0.00833 -0.0310 0.2448 1.0000
11.500 1.6137 0.01373 0.00860 -0.0302 0.2412 1.0000
11.750 1.6327 0.01405 0.00893 -0.0291 0.2368 1.0000
12.000 1.6498 0.01438 0.00927 -0.0277 0.2324 1.0000
12.250 1.6656 0.01472 0.00962 -0.0262 0.2255 1.0000
12.500 1.6780 0.01523 0.01012 -0.0242 0.2174 1.0000
12.750 1.6886 0.01587 0.01073 -0.0222 0.2095 1.0000
13.000 1.6922 0.01690 0.01172 -0.0196 0.1969 1.0000
13.250 1.6964 0.01802 0.01283 -0.0175 0.1854 1.0000
13.500 1.6870 0.02017 0.01493 -0.0149 0.1680 1.0000
13.750 1.6764 0.02292 0.01768 -0.0135 0.1565 1.0000
14.000 1.6663 0.02620 0.02100 -0.0133 0.1486 1.0000
14.250 1.6600 0.02944 0.02431 -0.0136 0.1423 1.0000
14.750 1.6210 0.03901 0.03403 -0.0147 0.1282 1.0000
15.000 1.5904 0.04504 0.04016 -0.0154 0.1228 1.0000
15.250 1.5501 0.05218 0.04740 -0.0162 0.1180 1.0000
15.500 1.5237 0.05789 0.05321 -0.0169 0.1159 1.0000
15.750 1.4852 0.06533 0.06073 -0.0182 0.1116 1.0000
16.000 1.4657 0.07067 0.06617 -0.0192 0.1099 1.0000
16.250 1.4474 0.07592 0.07150 -0.0203 0.1077 1.0000
16.500 1.4255 0.08172 0.07737 -0.0216 0.1048 1.0000
16.750 1.4019 0.08789 0.08360 -0.0230 0.1010 1.0000
17.000 1.3885 0.09277 0.08855 -0.0242 0.0970 1.0000
17.250 1.3677 0.09870 0.09450 -0.0258 0.0892 1.0000
17.500 1.3397 0.10576 0.10153 -0.0277 0.0790 1.0000
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