AG10 (ag10-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG10 (ag10-il) Reynolds number: 100,000 Max Cl/Cd: 41.67 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag10-il-100000-n5.txt Download as CSV file: xf-ag10-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG10
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5971 0.10308 0.09814 0.0241 1.0000 0.0431
-7.750 -0.5918 0.09964 0.09474 0.0225 1.0000 0.0447
-7.500 -0.5871 0.09615 0.09127 0.0201 1.0000 0.0464
-7.250 -0.5793 0.09218 0.08732 0.0139 1.0000 0.0491
-7.000 -0.5624 0.08727 0.08238 0.0010 1.0000 0.0505
-6.750 -0.5445 0.08227 0.07726 -0.0062 1.0000 0.0507
-6.500 -0.5346 0.07681 0.07184 -0.0072 1.0000 0.0513
-6.000 -0.5014 0.06352 0.05834 -0.0126 1.0000 0.0309
-5.750 -0.4839 0.05933 0.05409 -0.0148 1.0000 0.0299
-5.500 -0.4617 0.05425 0.04885 -0.0183 1.0000 0.0289
-5.250 -0.4363 0.04862 0.04298 -0.0222 1.0000 0.0280
-5.000 -0.4089 0.04274 0.03676 -0.0256 1.0000 0.0273
-4.750 -0.3807 0.03741 0.03100 -0.0281 1.0000 0.0277
-4.500 -0.3516 0.03259 0.02561 -0.0298 1.0000 0.0295
-4.250 -0.3221 0.02813 0.02041 -0.0309 1.0000 0.0305
-4.000 -0.2927 0.02462 0.01617 -0.0313 1.0000 0.0312
-3.750 -0.2654 0.02246 0.01373 -0.0315 1.0000 0.0330
-3.500 -0.2380 0.02121 0.01227 -0.0315 1.0000 0.0366
-3.250 -0.2095 0.01940 0.01000 -0.0312 1.0000 0.0393
-3.000 -0.1822 0.01805 0.00856 -0.0310 1.0000 0.0430
-2.750 -0.1549 0.01710 0.00747 -0.0307 1.0000 0.0487
-2.500 -0.1279 0.01606 0.00640 -0.0304 1.0000 0.0543
-2.250 -0.1007 0.01533 0.00556 -0.0300 1.0000 0.0630
-2.000 -0.0740 0.01462 0.00492 -0.0297 1.0000 0.0750
-1.750 -0.0472 0.01400 0.00435 -0.0294 1.0000 0.0910
-1.500 -0.0207 0.01343 0.00390 -0.0291 1.0000 0.1140
-1.250 0.0059 0.01293 0.00352 -0.0287 1.0000 0.1492
-1.000 0.0321 0.01238 0.00327 -0.0285 1.0000 0.2120
-0.750 0.0582 0.01151 0.00308 -0.0284 1.0000 0.3882
-0.500 0.0811 0.00979 0.00289 -0.0263 1.0000 1.0000
-0.250 0.1073 0.00982 0.00276 -0.0259 1.0000 1.0000
0.000 0.1333 0.00985 0.00269 -0.0255 1.0000 1.0000
0.250 0.1592 0.00990 0.00268 -0.0250 1.0000 1.0000
0.500 0.1848 0.00997 0.00270 -0.0246 1.0000 1.0000
0.750 0.2151 0.01005 0.00276 -0.0252 0.9927 1.0000
1.000 0.2597 0.01012 0.00280 -0.0285 0.9530 1.0000
1.250 0.3017 0.01020 0.00283 -0.0310 0.8951 1.0000
1.500 0.3350 0.01036 0.00284 -0.0312 0.8173 1.0000
1.750 0.3600 0.01066 0.00284 -0.0295 0.7319 1.0000
2.000 0.3836 0.01106 0.00290 -0.0278 0.6476 1.0000
2.250 0.4081 0.01152 0.00301 -0.0267 0.5721 1.0000
2.500 0.4334 0.01198 0.00320 -0.0259 0.5089 1.0000
2.750 0.4593 0.01243 0.00341 -0.0253 0.4566 1.0000
3.000 0.4855 0.01287 0.00366 -0.0249 0.4127 1.0000
3.250 0.5118 0.01330 0.00394 -0.0245 0.3745 1.0000
3.500 0.5383 0.01372 0.00429 -0.0241 0.3393 1.0000
3.750 0.5648 0.01415 0.00463 -0.0238 0.3061 1.0000
4.000 0.5912 0.01460 0.00500 -0.0236 0.2746 1.0000
4.250 0.6176 0.01507 0.00544 -0.0233 0.2444 1.0000
4.500 0.6439 0.01557 0.00589 -0.0230 0.2149 1.0000
4.750 0.6702 0.01612 0.00638 -0.0228 0.1862 1.0000
5.000 0.6963 0.01671 0.00693 -0.0226 0.1584 1.0000
5.250 0.7222 0.01737 0.00759 -0.0224 0.1317 1.0000
5.500 0.7480 0.01811 0.00831 -0.0221 0.1066 1.0000
5.750 0.7733 0.01900 0.00915 -0.0219 0.0846 1.0000
6.000 0.7984 0.01998 0.01015 -0.0216 0.0664 1.0000
6.250 0.8230 0.02113 0.01134 -0.0212 0.0534 1.0000
6.500 0.8472 0.02237 0.01269 -0.0207 0.0444 1.0000
6.750 0.8709 0.02378 0.01424 -0.0202 0.0381 1.0000
7.000 0.8939 0.02525 0.01580 -0.0197 0.0340 1.0000
7.250 0.9169 0.02693 0.01775 -0.0191 0.0302 1.0000
7.500 0.9394 0.02862 0.01964 -0.0185 0.0277 1.0000
7.750 0.9602 0.03076 0.02190 -0.0180 0.0261 1.0000
8.000 0.9806 0.03346 0.02504 -0.0172 0.0250 1.0000
8.250 0.9995 0.03628 0.02840 -0.0165 0.0233 1.0000
8.500 1.0169 0.03880 0.03128 -0.0160 0.0218 1.0000
8.750 1.0325 0.04139 0.03415 -0.0157 0.0208 1.0000
9.000 1.0439 0.04492 0.03802 -0.0152 0.0203 1.0000
9.250 1.0492 0.04948 0.04306 -0.0150 0.0201 1.0000
9.500 1.0473 0.05475 0.04887 -0.0152 0.0200 1.0000
9.750 1.0387 0.06035 0.05489 -0.0163 0.0199 1.0000
10.000 1.0238 0.06598 0.06081 -0.0183 0.0200 1.0000
10.250 1.0058 0.07243 0.06744 -0.0232 0.0201 1.0000
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Polar data table (+)
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