AUGUST 160 (august160-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AUGUST 160 (august160-il) Reynolds number: 500,000 Max Cl/Cd: 90.31 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-august160-il-500000-n5.txt Download as CSV file: xf-august160-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2075 0.07147 0.06701 -0.0615 0.4425 0.0108
-9.250 -0.2248 0.06495 0.06054 -0.0656 0.4421 0.0108
-9.000 -0.2498 0.05772 0.05334 -0.0715 0.4418 0.0107
-8.500 -0.3803 0.03394 0.02860 -0.0654 0.4498 0.0107
-8.250 -0.3822 0.03069 0.02497 -0.0623 0.4460 0.0107
-8.000 -0.3764 0.02818 0.02206 -0.0596 0.4409 0.0108
-7.750 -0.3644 0.02643 0.01999 -0.0574 0.4355 0.0109
-7.500 -0.3508 0.02471 0.01797 -0.0553 0.4305 0.0109
-7.250 -0.3345 0.02324 0.01632 -0.0537 0.4250 0.0112
-7.000 -0.3149 0.02222 0.01514 -0.0523 0.4191 0.0113
-6.750 -0.2936 0.02156 0.01435 -0.0512 0.4137 0.0115
-6.500 -0.2713 0.02093 0.01362 -0.0502 0.4089 0.0118
-6.250 -0.2490 0.02014 0.01268 -0.0491 0.4041 0.0119
-6.000 -0.2266 0.01929 0.01164 -0.0480 0.3993 0.0121
-5.500 -0.1798 0.01778 0.00980 -0.0460 0.3909 0.0123
-5.250 -0.1557 0.01711 0.00901 -0.0451 0.3869 0.0124
-5.000 -0.1312 0.01655 0.00834 -0.0442 0.3827 0.0126
-4.750 -0.1068 0.01604 0.00770 -0.0434 0.3786 0.0129
-4.500 -0.0820 0.01560 0.00718 -0.0425 0.3752 0.0130
-4.250 -0.0569 0.01518 0.00669 -0.0418 0.3722 0.0132
-4.000 -0.0318 0.01482 0.00626 -0.0410 0.3687 0.0135
-3.750 -0.0066 0.01452 0.00589 -0.0403 0.3653 0.0136
-3.500 0.0176 0.01412 0.00546 -0.0394 0.3620 0.0139
-3.250 0.0422 0.01383 0.00513 -0.0386 0.3587 0.0142
-3.000 0.0676 0.01357 0.00485 -0.0379 0.3564 0.0146
-2.750 0.0933 0.01335 0.00461 -0.0373 0.3537 0.0150
-2.500 0.1190 0.01316 0.00439 -0.0366 0.3509 0.0153
-2.250 0.1448 0.01299 0.00418 -0.0360 0.3480 0.0158
-2.000 0.1707 0.01288 0.00402 -0.0354 0.3450 0.0164
-1.750 0.1961 0.01275 0.00385 -0.0348 0.3422 0.0172
-1.500 0.2222 0.01262 0.00371 -0.0342 0.3400 0.0180
-1.250 0.2485 0.01252 0.00359 -0.0337 0.3380 0.0187
-1.000 0.2749 0.01244 0.00348 -0.0332 0.3360 0.0199
-0.750 0.3011 0.01236 0.00339 -0.0327 0.3339 0.0220
-0.500 0.3268 0.01224 0.00332 -0.0321 0.3318 0.0346
-0.250 0.3510 0.01200 0.00327 -0.0314 0.3298 0.0928
0.000 0.3759 0.01187 0.00325 -0.0307 0.3278 0.1388
0.250 0.3998 0.01169 0.00325 -0.0300 0.3259 0.2082
0.500 0.4204 0.01126 0.00326 -0.0287 0.3242 0.3568
0.750 0.4345 0.01051 0.00326 -0.0261 0.3231 0.5857
1.000 0.4490 0.00974 0.00349 -0.0227 0.3220 0.8764
1.250 0.4848 0.00990 0.00368 -0.0239 0.3202 0.9264
1.500 0.5175 0.01004 0.00380 -0.0247 0.3186 0.9424
1.750 0.5489 0.01019 0.00390 -0.0252 0.3169 0.9540
2.000 0.5878 0.01037 0.00402 -0.0273 0.3152 0.9617
2.250 0.6256 0.01055 0.00414 -0.0293 0.3134 0.9674
2.500 0.6651 0.01073 0.00425 -0.0317 0.3118 0.9706
2.750 0.6984 0.01091 0.00438 -0.0328 0.3102 0.9760
3.000 0.7359 0.01111 0.00451 -0.0349 0.3084 0.9780
3.250 0.7709 0.01125 0.00463 -0.0364 0.3073 0.9798
3.500 0.8029 0.01136 0.00473 -0.0374 0.3064 0.9816
3.750 0.8329 0.01147 0.00483 -0.0379 0.3051 0.9835
4.000 0.8632 0.01159 0.00495 -0.0385 0.3037 0.9861
4.250 0.8961 0.01172 0.00506 -0.0397 0.3024 0.9873
4.500 0.9293 0.01186 0.00520 -0.0410 0.3011 0.9888
4.750 0.9641 0.01201 0.00534 -0.0426 0.2999 0.9911
5.000 0.9938 0.01217 0.00548 -0.0432 0.2987 0.9927
5.250 1.0261 0.01233 0.00564 -0.0443 0.2974 0.9950
5.500 1.0560 0.01249 0.00578 -0.0450 0.2960 0.9966
5.750 1.0851 0.01267 0.00595 -0.0455 0.2945 0.9981
6.000 1.1141 0.01288 0.00614 -0.0461 0.2932 0.9993
6.250 1.1400 0.01309 0.00635 -0.0460 0.2919 1.0000
6.500 1.1608 0.01321 0.00652 -0.0448 0.2908 1.0000
6.750 1.1811 0.01337 0.00671 -0.0435 0.2899 1.0000
7.000 1.2012 0.01352 0.00689 -0.0422 0.2887 1.0000
7.250 1.2211 0.01365 0.00706 -0.0409 0.2867 1.0000
7.500 1.2406 0.01382 0.00725 -0.0395 0.2853 1.0000
7.750 1.2598 0.01400 0.00745 -0.0381 0.2840 1.0000
8.000 1.2788 0.01417 0.00764 -0.0366 0.2823 1.0000
8.250 1.2977 0.01437 0.00785 -0.0352 0.2811 1.0000
8.500 1.3169 0.01459 0.00809 -0.0338 0.2802 1.0000
8.750 1.3361 0.01483 0.00834 -0.0325 0.2792 1.0000
9.000 1.3554 0.01509 0.00862 -0.0312 0.2781 1.0000
9.250 1.3749 0.01537 0.00892 -0.0300 0.2771 1.0000
9.500 1.3955 0.01557 0.00919 -0.0290 0.2761 1.0000
9.750 1.4158 0.01580 0.00948 -0.0280 0.2749 1.0000
10.000 1.4359 0.01602 0.00976 -0.0270 0.2733 1.0000
10.250 1.4555 0.01626 0.01006 -0.0259 0.2715 1.0000
10.500 1.4746 0.01652 0.01036 -0.0248 0.2700 1.0000
10.750 1.4930 0.01680 0.01068 -0.0235 0.2682 1.0000
11.000 1.5091 0.01710 0.01102 -0.0219 0.2668 1.0000
11.250 1.5236 0.01742 0.01137 -0.0201 0.2651 1.0000
11.500 1.5380 0.01779 0.01177 -0.0183 0.2635 1.0000
11.750 1.5534 0.01817 0.01221 -0.0169 0.2615 1.0000
12.000 1.5701 0.01854 0.01267 -0.0157 0.2597 1.0000
12.250 1.5861 0.01895 0.01317 -0.0145 0.2576 1.0000
12.500 1.6009 0.01944 0.01373 -0.0134 0.2548 1.0000
12.750 1.6140 0.02005 0.01438 -0.0122 0.2518 1.0000
13.000 1.6255 0.02081 0.01518 -0.0111 0.2493 1.0000
13.250 1.6389 0.02156 0.01601 -0.0103 0.2470 1.0000
13.500 1.6529 0.02236 0.01692 -0.0098 0.2442 1.0000
13.750 1.6647 0.02335 0.01800 -0.0093 0.2407 1.0000
14.000 1.6736 0.02464 0.01936 -0.0089 0.2371 1.0000
14.250 1.6809 0.02618 0.02097 -0.0087 0.2330 1.0000
14.500 1.6899 0.02766 0.02256 -0.0087 0.2294 1.0000
14.750 1.6882 0.03025 0.02519 -0.0089 0.2218 1.0000
15.000 1.6879 0.03279 0.02781 -0.0092 0.2160 1.0000
15.250 1.6732 0.03689 0.03195 -0.0097 0.2089 1.0000
15.500 1.6617 0.04070 0.03585 -0.0102 0.2034 1.0000
15.750 1.6348 0.04618 0.04139 -0.0109 0.1971 1.0000
16.000 1.6133 0.05112 0.04642 -0.0115 0.1916 1.0000
16.250 1.5819 0.05736 0.05274 -0.0125 0.1849 1.0000
16.500 1.5462 0.06435 0.05979 -0.0138 0.1761 1.0000
16.750 1.5075 0.07194 0.06743 -0.0154 0.1684 1.0000
17.000 1.4629 0.08049 0.07600 -0.0173 0.1602 1.0000
17.250 1.4349 0.08709 0.08264 -0.0189 0.1541 1.0000
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