AG08 (ag08-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 100,000 Max Cl/Cd: 45.62 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag08-il-100000.txt Download as CSV file: xf-ag08-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5762 0.11263 0.10781 0.0154 1.0000 0.0737
-8.500 -0.5820 0.11040 0.10567 0.0090 1.0000 0.0745
-8.250 -0.5836 0.10728 0.10261 0.0006 1.0000 0.0748
-8.000 -0.5624 0.10032 0.09561 0.0117 1.0000 0.0781
-7.750 -0.5554 0.09679 0.09211 0.0111 1.0000 0.0810
-7.500 -0.5520 0.09329 0.08865 0.0083 1.0000 0.0843
-7.250 -0.5463 0.08915 0.08453 -0.0079 1.0000 0.0880
-7.000 -0.5383 0.08371 0.07913 -0.0082 1.0000 0.0895
-6.750 -0.5278 0.08032 0.07573 -0.0039 1.0000 0.0925
-6.500 -0.5142 0.07623 0.07163 -0.0083 1.0000 0.0987
-6.250 -0.4993 0.07068 0.06602 -0.0160 1.0000 0.1041
-6.000 -0.4762 0.06633 0.06134 -0.0265 1.0000 0.1159
-5.750 -0.4684 0.06292 0.05821 -0.0194 1.0000 0.1202
-5.500 -0.4470 0.05806 0.05318 -0.0253 1.0000 0.1315
-5.250 -0.4250 0.05399 0.04891 -0.0291 1.0000 0.1444
-5.000 -0.4083 0.05067 0.04567 -0.0276 1.0000 0.1504
-4.750 -0.3596 0.03572 0.02914 -0.0387 1.0000 0.0764
-4.500 -0.3337 0.03118 0.02424 -0.0391 1.0000 0.0692
-4.250 -0.3061 0.02765 0.02007 -0.0393 1.0000 0.0715
-4.000 -0.2781 0.02440 0.01619 -0.0391 1.0000 0.0722
-3.750 -0.2496 0.02199 0.01311 -0.0385 1.0000 0.0746
-3.500 -0.2238 0.02015 0.01117 -0.0382 1.0000 0.0852
-3.250 -0.1968 0.01826 0.00909 -0.0376 1.0000 0.0936
-3.000 -0.1705 0.01710 0.00786 -0.0370 1.0000 0.1113
-2.750 -0.1443 0.01581 0.00656 -0.0364 1.0000 0.1319
-2.500 -0.1187 0.01479 0.00572 -0.0358 1.0000 0.1645
-2.250 -0.0934 0.01381 0.00495 -0.0353 1.0000 0.2150
-2.000 -0.0684 0.01266 0.00438 -0.0348 1.0000 0.3139
-1.750 -0.0476 0.01090 0.00402 -0.0332 1.0000 0.6122
-1.500 -0.0149 0.00997 0.00362 -0.0326 1.0000 1.0000
-1.250 0.0104 0.00998 0.00335 -0.0321 1.0000 1.0000
-1.000 0.0355 0.01001 0.00318 -0.0316 1.0000 1.0000
-0.750 0.0606 0.01006 0.00307 -0.0311 1.0000 1.0000
-0.500 0.0854 0.01012 0.00301 -0.0307 1.0000 1.0000
-0.250 0.1102 0.01021 0.00299 -0.0302 1.0000 1.0000
0.000 0.1348 0.01031 0.00301 -0.0298 1.0000 1.0000
0.250 0.1593 0.01045 0.00309 -0.0294 1.0000 1.0000
0.500 0.1837 0.01061 0.00323 -0.0292 1.0000 1.0000
0.750 0.2078 0.01083 0.00343 -0.0290 1.0000 1.0000
1.000 0.2315 0.01109 0.00371 -0.0289 1.0000 1.0000
1.250 0.2547 0.01144 0.00408 -0.0290 1.0000 1.0000
1.500 0.3192 0.01159 0.00431 -0.0367 0.9753 1.0000
1.750 0.3797 0.01155 0.00441 -0.0429 0.9477 1.0000
2.000 0.4279 0.01142 0.00438 -0.0461 0.9127 1.0000
2.250 0.4621 0.01135 0.00434 -0.0460 0.8672 1.0000
2.500 0.4887 0.01139 0.00432 -0.0442 0.8166 1.0000
2.750 0.5119 0.01156 0.00439 -0.0418 0.7608 1.0000
3.000 0.5345 0.01185 0.00450 -0.0396 0.7022 1.0000
3.250 0.5574 0.01225 0.00468 -0.0378 0.6430 1.0000
3.500 0.5807 0.01273 0.00492 -0.0362 0.5862 1.0000
3.750 0.6044 0.01327 0.00526 -0.0350 0.5330 1.0000
4.000 0.6285 0.01385 0.00563 -0.0339 0.4835 1.0000
4.250 0.6527 0.01446 0.00606 -0.0330 0.4377 1.0000
4.500 0.6772 0.01509 0.00655 -0.0322 0.3940 1.0000
4.750 0.7016 0.01575 0.00708 -0.0314 0.3523 1.0000
5.000 0.7259 0.01644 0.00770 -0.0307 0.3115 1.0000
5.250 0.7500 0.01718 0.00833 -0.0300 0.2707 1.0000
5.500 0.7738 0.01800 0.00904 -0.0294 0.2291 1.0000
5.750 0.7972 0.01895 0.00990 -0.0287 0.1862 1.0000
6.000 0.8201 0.02012 0.01094 -0.0279 0.1443 1.0000
6.250 0.8421 0.02163 0.01228 -0.0272 0.1095 1.0000
6.500 0.8649 0.02335 0.01399 -0.0262 0.0850 1.0000
6.750 0.8875 0.02579 0.01637 -0.0253 0.0706 1.0000
7.000 0.9112 0.02751 0.01835 -0.0244 0.0603 1.0000
7.250 0.9341 0.03049 0.02167 -0.0233 0.0549 1.0000
7.500 0.9561 0.03365 0.02533 -0.0221 0.0519 1.0000
7.750 0.9761 0.03665 0.02866 -0.0211 0.0490 1.0000
8.000 0.9900 0.04149 0.03380 -0.0205 0.0460 1.0000
8.250 1.0026 0.04520 0.03823 -0.0192 0.0451 1.0000
8.500 1.0105 0.05040 0.04395 -0.0182 0.0454 1.0000
8.750 1.0149 0.05666 0.05054 -0.0177 0.0461 1.0000
9.000 0.9974 0.06371 0.05873 -0.0178 0.0502 1.0000
9.250 0.9760 0.07159 0.06697 -0.0201 0.0528 1.0000
9.500 0.8752 0.06516 0.06075 -0.0118 0.0517 1.0000
9.750 0.8411 0.07330 0.06898 -0.0167 0.0537 1.0000
10.000 0.8198 0.08127 0.07697 -0.0208 0.0558 1.0000
10.250 0.8065 0.08822 0.08389 -0.0232 0.0570 1.0000
10.500 0.7977 0.09445 0.09011 -0.0245 0.0578 1.0000
10.750 0.8597 0.13307 0.12839 -0.0635 0.1162 1.0000
11.000 0.7308 0.12776 0.12335 -0.0419 0.1231 1.0000
11.250 0.7287 0.13310 0.12867 -0.0428 0.1220 1.0000
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Polar data table (+)
Polar graphs
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