AUGUST 160 (august160-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AUGUST 160 (august160-il) Reynolds number: 500,000 Max Cl/Cd: 82.08 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-august160-il-500000.txt Download as CSV file: xf-august160-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1619 0.08963 0.08545 -0.0564 0.5063 0.0232
-9.750 -0.1642 0.08495 0.08079 -0.0592 0.5016 0.0232
-9.500 -0.1610 0.08184 0.07767 -0.0597 0.4944 0.0234
-9.250 -0.1533 0.07994 0.07573 -0.0596 0.4876 0.0236
-9.000 -0.1489 0.07725 0.07306 -0.0604 0.4822 0.0237
-8.750 -0.1465 0.07436 0.07017 -0.0615 0.4769 0.0240
-8.500 -0.1445 0.07165 0.06745 -0.0625 0.4712 0.0245
-8.250 -0.1520 0.06738 0.06321 -0.0654 0.4683 0.0245
-8.000 -0.1685 0.06276 0.05860 -0.0681 0.4657 0.0247
-7.750 -0.1828 0.05928 0.05510 -0.0676 0.4629 0.0251
-7.500 -0.1904 0.05533 0.05107 -0.0676 0.4594 0.0251
-7.250 -0.2269 0.04526 0.04056 -0.0662 0.4610 0.0273
-7.000 -0.2162 0.04360 0.03884 -0.0649 0.4553 0.0275
-6.750 -0.2038 0.04234 0.03749 -0.0637 0.4496 0.0279
-6.500 -0.2152 0.03753 0.03197 -0.0592 0.4478 0.0313
-6.250 -0.1962 0.03550 0.03002 -0.0587 0.4423 0.0316
-6.000 -0.1787 0.03416 0.02864 -0.0577 0.4368 0.0320
-5.750 -0.1615 0.03297 0.02733 -0.0565 0.4312 0.0328
-5.500 -0.1527 0.03012 0.02399 -0.0534 0.4280 0.0363
-5.250 -0.1316 0.02887 0.02275 -0.0526 0.4231 0.0370
-5.000 -0.1177 0.02754 0.02088 -0.0498 0.4189 0.0411
-4.750 -0.0957 0.02590 0.01924 -0.0492 0.4140 0.0418
-4.500 -0.0795 0.01941 0.01145 -0.0440 0.4116 0.0233
-4.250 -0.0536 0.01797 0.01000 -0.0434 0.4078 0.0227
-4.000 -0.0280 0.01691 0.00883 -0.0427 0.4034 0.0222
-3.750 -0.0026 0.01614 0.00793 -0.0418 0.3993 0.0220
-3.500 0.0224 0.01555 0.00720 -0.0410 0.3949 0.0220
-3.250 0.0479 0.01500 0.00661 -0.0402 0.3917 0.0222
-3.000 0.0732 0.01454 0.00611 -0.0394 0.3885 0.0226
-2.750 0.0985 0.01420 0.00571 -0.0386 0.3849 0.0231
-2.500 0.1232 0.01388 0.00534 -0.0377 0.3815 0.0233
-2.250 0.1466 0.01352 0.00494 -0.0367 0.3779 0.0240
-2.000 0.1716 0.01331 0.00472 -0.0359 0.3749 0.0247
-1.750 0.1975 0.01311 0.00452 -0.0353 0.3724 0.0259
-1.500 0.2233 0.01294 0.00433 -0.0346 0.3698 0.0272
-1.250 0.2489 0.01277 0.00416 -0.0340 0.3671 0.0290
-1.000 0.2747 0.01266 0.00401 -0.0333 0.3645 0.0315
-0.750 0.3002 0.01257 0.00390 -0.0327 0.3618 0.0381
-0.500 0.3213 0.01212 0.00383 -0.0314 0.3590 0.1533
-0.250 0.3409 0.01151 0.00382 -0.0300 0.3572 0.3278
0.000 0.3516 0.01054 0.00379 -0.0267 0.3557 0.6031
0.250 0.3690 0.00985 0.00404 -0.0238 0.3539 0.8797
0.500 0.4052 0.01006 0.00427 -0.0248 0.3516 0.9323
0.750 0.4537 0.01040 0.00454 -0.0284 0.3490 0.9578
1.000 0.5263 0.01084 0.00483 -0.0371 0.3462 0.9697
1.250 0.5670 0.01110 0.00497 -0.0396 0.3437 0.9766
1.500 0.6171 0.01139 0.00515 -0.0442 0.3409 0.9799
1.750 0.6619 0.01152 0.00525 -0.0476 0.3394 0.9857
2.000 0.7061 0.01161 0.00529 -0.0509 0.3378 0.9885
2.250 0.7523 0.01171 0.00535 -0.0548 0.3359 0.9931
2.500 0.7986 0.01177 0.00536 -0.0587 0.3339 0.9973
2.750 0.8378 0.01183 0.00538 -0.0611 0.3321 1.0000
3.000 0.8604 0.01194 0.00545 -0.0602 0.3305 1.0000
3.250 0.8830 0.01207 0.00555 -0.0593 0.3292 1.0000
3.500 0.9056 0.01223 0.00568 -0.0584 0.3279 1.0000
3.750 0.9280 0.01246 0.00587 -0.0575 0.3263 1.0000
4.000 0.9505 0.01281 0.00618 -0.0566 0.3244 1.0000
4.250 0.9728 0.01292 0.00631 -0.0557 0.3237 1.0000
4.500 0.9950 0.01304 0.00645 -0.0547 0.3227 1.0000
4.750 1.0170 0.01317 0.00660 -0.0537 0.3215 1.0000
5.000 1.0388 0.01332 0.00677 -0.0526 0.3203 1.0000
5.250 1.0605 0.01348 0.00696 -0.0516 0.3190 1.0000
5.500 1.0822 0.01366 0.00715 -0.0505 0.3179 1.0000
5.750 1.1037 0.01386 0.00735 -0.0495 0.3169 1.0000
6.000 1.1250 0.01406 0.00757 -0.0484 0.3159 1.0000
6.250 1.1462 0.01426 0.00778 -0.0473 0.3148 1.0000
6.500 1.1672 0.01442 0.00794 -0.0462 0.3133 1.0000
6.750 1.1880 0.01464 0.00815 -0.0450 0.3122 1.0000
7.000 1.2087 0.01489 0.00840 -0.0439 0.3107 1.0000
7.250 1.2296 0.01543 0.00890 -0.0430 0.3080 1.0000
7.500 1.2491 0.01557 0.00909 -0.0415 0.3073 1.0000
7.750 1.2683 0.01573 0.00931 -0.0401 0.3063 1.0000
8.000 1.2874 0.01589 0.00953 -0.0387 0.3052 1.0000
8.250 1.3069 0.01612 0.00981 -0.0374 0.3042 1.0000
8.500 1.3266 0.01638 0.01012 -0.0361 0.3033 1.0000
8.750 1.3466 0.01663 0.01042 -0.0350 0.3022 1.0000
9.000 1.3669 0.01688 0.01071 -0.0339 0.3011 1.0000
9.250 1.3877 0.01715 0.01102 -0.0329 0.3001 1.0000
9.500 1.4086 0.01732 0.01121 -0.0319 0.2986 1.0000
9.750 1.4299 0.01749 0.01140 -0.0310 0.2971 1.0000
10.000 1.4512 0.01768 0.01159 -0.0302 0.2954 1.0000
10.250 1.4730 0.01803 0.01193 -0.0295 0.2936 1.0000
10.500 1.4946 0.01855 0.01248 -0.0289 0.2919 1.0000
10.750 1.5130 0.01876 0.01279 -0.0277 0.2910 1.0000
11.000 1.5317 0.01904 0.01316 -0.0265 0.2900 1.0000
11.250 1.5493 0.01927 0.01348 -0.0252 0.2885 1.0000
11.500 1.5671 0.01950 0.01378 -0.0239 0.2868 1.0000
11.750 1.5845 0.01966 0.01401 -0.0226 0.2848 1.0000
12.000 1.6024 0.01987 0.01426 -0.0214 0.2830 1.0000
12.250 1.6182 0.02006 0.01448 -0.0198 0.2812 1.0000
12.500 1.6337 0.02030 0.01472 -0.0182 0.2791 1.0000
12.750 1.6502 0.02075 0.01519 -0.0170 0.2768 1.0000
13.000 1.6598 0.02114 0.01571 -0.0148 0.2753 1.0000
13.250 1.6707 0.02160 0.01628 -0.0131 0.2736 1.0000
13.500 1.6827 0.02211 0.01690 -0.0117 0.2716 1.0000
13.750 1.6949 0.02266 0.01752 -0.0105 0.2694 1.0000
14.000 1.7070 0.02326 0.01819 -0.0095 0.2673 1.0000
14.250 1.7192 0.02394 0.01888 -0.0087 0.2647 1.0000
14.500 1.7334 0.02471 0.01968 -0.0081 0.2625 1.0000
14.750 1.7377 0.02605 0.02120 -0.0074 0.2603 1.0000
15.000 1.7441 0.02745 0.02273 -0.0071 0.2579 1.0000
15.250 1.7495 0.02904 0.02444 -0.0070 0.2545 1.0000
15.500 1.7555 0.03068 0.02614 -0.0071 0.2515 1.0000
15.750 1.7600 0.03248 0.02795 -0.0071 0.2482 1.0000
16.000 1.7576 0.03519 0.03086 -0.0076 0.2449 1.0000
16.250 1.7534 0.03815 0.03396 -0.0082 0.2403 1.0000
16.500 1.7469 0.04133 0.03719 -0.0087 0.2362 1.0000
16.750 1.7346 0.04524 0.04123 -0.0094 0.2314 1.0000
17.000 1.7159 0.04991 0.04602 -0.0103 0.2261 1.0000
17.250 1.6914 0.05537 0.05154 -0.0115 0.2204 1.0000
17.500 1.6642 0.06131 0.05759 -0.0127 0.2147 1.0000
17.750 1.6320 0.06796 0.06427 -0.0142 0.2088 1.0000
18.000 1.5975 0.07509 0.07150 -0.0159 0.2027 1.0000
18.250 1.5667 0.08185 0.07826 -0.0175 0.1962 1.0000
18.500 1.5314 0.08939 0.08591 -0.0194 0.1887 1.0000
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