AG17 (ag17-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 100,000 Max Cl/Cd: 48.43 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag17-il-100000-n5.txt Download as CSV file: xf-ag17-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG17
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5295 0.09129 0.08654 0.0033 1.0000 0.0323
-7.500 -0.5301 0.08368 0.07903 -0.0050 1.0000 0.0267
-7.250 -0.5189 0.07903 0.07436 -0.0089 1.0000 0.0244
-7.000 -0.5092 0.07409 0.06944 -0.0133 1.0000 0.0237
-6.750 -0.4965 0.06840 0.06374 -0.0192 1.0000 0.0231
-6.500 -0.4804 0.06189 0.05717 -0.0262 1.0000 0.0225
-6.250 -0.4615 0.05461 0.04974 -0.0334 1.0000 0.0218
-6.000 -0.4405 0.04724 0.04208 -0.0396 1.0000 0.0212
-5.750 -0.4176 0.04049 0.03487 -0.0442 1.0000 0.0207
-5.500 -0.3928 0.03474 0.02853 -0.0472 1.0000 0.0204
-5.250 -0.3668 0.03018 0.02332 -0.0488 1.0000 0.0205
-5.000 -0.3400 0.02664 0.01916 -0.0495 1.0000 0.0209
-4.750 -0.3130 0.02386 0.01585 -0.0496 1.0000 0.0216
-4.500 -0.2860 0.02193 0.01349 -0.0494 1.0000 0.0240
-4.250 -0.2596 0.02006 0.01135 -0.0492 1.0000 0.0271
-4.000 -0.2335 0.01856 0.00972 -0.0489 1.0000 0.0298
-3.750 -0.2071 0.01727 0.00823 -0.0484 1.0000 0.0337
-3.500 -0.1810 0.01625 0.00714 -0.0482 1.0000 0.0426
-3.250 -0.1543 0.01522 0.00605 -0.0479 1.0000 0.0556
-3.000 -0.1278 0.01432 0.00526 -0.0477 1.0000 0.0900
-2.750 -0.1017 0.01348 0.00473 -0.0477 1.0000 0.1565
-2.500 -0.0759 0.01283 0.00442 -0.0476 1.0000 0.2438
-2.250 -0.0503 0.01236 0.00416 -0.0474 1.0000 0.3271
-2.000 -0.0250 0.01199 0.00400 -0.0470 1.0000 0.4055
-1.750 0.0004 0.01164 0.00387 -0.0465 1.0000 0.4841
-1.500 0.0255 0.01129 0.00376 -0.0459 1.0000 0.5673
-1.250 0.0489 0.01088 0.00365 -0.0448 1.0000 0.6686
-1.000 0.0682 0.01023 0.00355 -0.0421 1.0000 0.8706
-0.750 0.1016 0.01021 0.00342 -0.0435 0.9940 1.0000
-0.500 0.1447 0.01029 0.00333 -0.0468 0.9789 1.0000
-0.250 0.1856 0.01035 0.00324 -0.0495 0.9612 1.0000
0.000 0.2254 0.01040 0.00318 -0.0518 0.9421 1.0000
0.250 0.2620 0.01044 0.00314 -0.0533 0.9192 1.0000
0.500 0.2966 0.01049 0.00310 -0.0543 0.8943 1.0000
0.750 0.3283 0.01055 0.00307 -0.0546 0.8666 1.0000
1.000 0.3576 0.01063 0.00306 -0.0543 0.8368 1.0000
1.250 0.3851 0.01074 0.00307 -0.0536 0.8054 1.0000
1.500 0.4116 0.01088 0.00310 -0.0528 0.7726 1.0000
1.750 0.4377 0.01105 0.00317 -0.0519 0.7387 1.0000
2.000 0.4639 0.01124 0.00325 -0.0510 0.7039 1.0000
2.250 0.4898 0.01147 0.00335 -0.0502 0.6679 1.0000
2.500 0.5157 0.01172 0.00348 -0.0494 0.6306 1.0000
2.750 0.5414 0.01201 0.00368 -0.0487 0.5926 1.0000
3.000 0.5671 0.01232 0.00386 -0.0480 0.5539 1.0000
3.250 0.5927 0.01267 0.00408 -0.0473 0.5149 1.0000
3.500 0.6183 0.01304 0.00434 -0.0467 0.4755 1.0000
3.750 0.6438 0.01345 0.00463 -0.0461 0.4364 1.0000
4.000 0.6694 0.01389 0.00501 -0.0456 0.3980 1.0000
4.250 0.6948 0.01436 0.00539 -0.0451 0.3608 1.0000
4.500 0.7201 0.01487 0.00581 -0.0447 0.3245 1.0000
4.750 0.7454 0.01539 0.00627 -0.0443 0.2896 1.0000
5.000 0.7705 0.01597 0.00678 -0.0439 0.2559 1.0000
5.250 0.7956 0.01658 0.00740 -0.0435 0.2237 1.0000
5.500 0.8205 0.01723 0.00803 -0.0431 0.1930 1.0000
5.750 0.8451 0.01795 0.00871 -0.0427 0.1639 1.0000
6.000 0.8694 0.01874 0.00948 -0.0423 0.1369 1.0000
6.250 0.8934 0.01960 0.01035 -0.0419 0.1128 1.0000
6.500 0.9168 0.02060 0.01132 -0.0414 0.0915 1.0000
6.750 0.9400 0.02167 0.01252 -0.0408 0.0734 1.0000
7.000 0.9623 0.02289 0.01376 -0.0403 0.0582 1.0000
7.250 0.9840 0.02427 0.01526 -0.0395 0.0473 1.0000
7.500 1.0050 0.02578 0.01692 -0.0387 0.0382 1.0000
7.750 1.0241 0.02763 0.01886 -0.0378 0.0322 1.0000
8.000 1.0444 0.02942 0.02094 -0.0367 0.0273 1.0000
8.250 1.0611 0.03154 0.02315 -0.0359 0.0230 1.0000
8.500 1.0794 0.03394 0.02592 -0.0347 0.0211 1.0000
8.750 1.0954 0.03688 0.02927 -0.0334 0.0195 1.0000
9.000 1.1093 0.03983 0.03270 -0.0322 0.0180 1.0000
9.250 1.1216 0.04218 0.03533 -0.0313 0.0163 1.0000
9.500 1.1289 0.04511 0.03847 -0.0305 0.0150 1.0000
9.750 1.1287 0.04937 0.04314 -0.0293 0.0143 1.0000
10.000 1.1260 0.05339 0.04761 -0.0283 0.0140 1.0000
10.250 1.1159 0.05761 0.05219 -0.0275 0.0139 1.0000
10.500 1.1006 0.06206 0.05692 -0.0276 0.0138 1.0000
10.750 1.0838 0.06743 0.06253 -0.0301 0.0139 1.0000
11.000 1.0664 0.07409 0.06938 -0.0349 0.0140 1.0000
11.250 1.0486 0.08210 0.07755 -0.0414 0.0141 1.0000
11.500 1.0303 0.09115 0.08671 -0.0482 0.0143 1.0000
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Polar data table (+)
Polar graphs
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