AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 50,000 Max Cl/Cd: 34.63 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag03-il-50000-n5.txt Download as CSV file: xf-ag03-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5363 0.11084 0.10406 0.0110 1.0000 0.0873
-8.250 -0.5401 0.10831 0.10163 0.0064 1.0000 0.0906
-8.000 -0.5437 0.10553 0.09894 0.0005 1.0000 0.0914
-7.750 -0.5390 0.10149 0.09498 -0.0047 1.0000 0.0918
-7.500 -0.5289 0.09659 0.09011 -0.0044 1.0000 0.0923
-7.250 -0.5198 0.09218 0.08572 -0.0066 1.0000 0.0926
-7.000 -0.5015 0.08463 0.07805 -0.0071 1.0000 0.0470
-6.750 -0.4857 0.07734 0.07058 -0.0195 1.0000 0.0392
-6.500 -0.4756 0.07334 0.06662 -0.0194 1.0000 0.0383
-6.250 -0.4628 0.06894 0.06217 -0.0217 1.0000 0.0378
-6.000 -0.4480 0.06439 0.05753 -0.0244 1.0000 0.0375
-5.750 -0.4314 0.05980 0.05280 -0.0271 1.0000 0.0373
-5.500 -0.4130 0.05525 0.04805 -0.0295 1.0000 0.0373
-5.250 -0.3930 0.05081 0.04334 -0.0315 1.0000 0.0373
-5.000 -0.3718 0.04654 0.03875 -0.0331 1.0000 0.0373
-4.750 -0.3493 0.04250 0.03432 -0.0341 1.0000 0.0372
-4.500 -0.3258 0.03873 0.03014 -0.0347 1.0000 0.0369
-4.250 -0.3011 0.03522 0.02615 -0.0349 1.0000 0.0369
-4.000 -0.2755 0.03202 0.02235 -0.0348 1.0000 0.0373
-3.750 -0.2489 0.02920 0.01895 -0.0343 1.0000 0.0383
-3.500 -0.2241 0.02697 0.01648 -0.0340 1.0000 0.0426
-3.250 -0.1980 0.02514 0.01433 -0.0333 1.0000 0.0484
-3.000 -0.1715 0.02314 0.01199 -0.0322 1.0000 0.0531
-2.750 -0.1458 0.02176 0.01049 -0.0314 1.0000 0.0668
-2.500 -0.1199 0.02045 0.00911 -0.0307 1.0000 0.0881
-2.250 -0.0941 0.01918 0.00785 -0.0301 1.0000 0.1304
-2.000 -0.0690 0.01775 0.00687 -0.0298 1.0000 0.2177
-1.750 -0.0523 0.01533 0.00633 -0.0279 1.0000 0.5782
-1.500 -0.0137 0.01438 0.00570 -0.0282 1.0000 1.0000
-1.250 0.0095 0.01440 0.00534 -0.0274 1.0000 1.0000
-1.000 0.0324 0.01445 0.00504 -0.0267 1.0000 1.0000
-0.750 0.0552 0.01453 0.00487 -0.0260 1.0000 1.0000
-0.500 0.0778 0.01463 0.00477 -0.0253 1.0000 1.0000
-0.250 0.1001 0.01477 0.00473 -0.0247 1.0000 1.0000
0.000 0.1223 0.01496 0.00477 -0.0241 1.0000 1.0000
0.250 0.1443 0.01518 0.00486 -0.0237 1.0000 1.0000
0.500 0.1800 0.01545 0.00502 -0.0259 0.9891 1.0000
0.750 0.2300 0.01570 0.00518 -0.0308 0.9680 1.0000
1.000 0.2782 0.01587 0.00531 -0.0349 0.9449 1.0000
1.250 0.3220 0.01601 0.00543 -0.0380 0.9191 1.0000
1.500 0.3619 0.01611 0.00554 -0.0399 0.8907 1.0000
1.750 0.3980 0.01620 0.00567 -0.0409 0.8601 1.0000
2.000 0.4295 0.01631 0.00576 -0.0409 0.8268 1.0000
2.250 0.4583 0.01644 0.00586 -0.0401 0.7923 1.0000
2.500 0.4848 0.01660 0.00598 -0.0390 0.7564 1.0000
2.750 0.5101 0.01681 0.00611 -0.0375 0.7201 1.0000
3.000 0.5343 0.01707 0.00637 -0.0360 0.6816 1.0000
3.250 0.5582 0.01737 0.00659 -0.0345 0.6428 1.0000
3.500 0.5819 0.01772 0.00685 -0.0331 0.6033 1.0000
3.750 0.6055 0.01812 0.00716 -0.0317 0.5636 1.0000
4.000 0.6291 0.01856 0.00751 -0.0305 0.5237 1.0000
4.250 0.6525 0.01906 0.00800 -0.0293 0.4842 1.0000
4.500 0.6759 0.01961 0.00849 -0.0282 0.4449 1.0000
4.750 0.6997 0.02022 0.00905 -0.0274 0.4064 1.0000
5.000 0.7235 0.02089 0.00967 -0.0266 0.3693 1.0000
5.250 0.7470 0.02162 0.01041 -0.0259 0.3337 1.0000
5.500 0.7705 0.02241 0.01121 -0.0252 0.2987 1.0000
5.750 0.7935 0.02327 0.01204 -0.0245 0.2659 1.0000
6.000 0.8163 0.02421 0.01297 -0.0238 0.2355 1.0000
6.250 0.8389 0.02524 0.01404 -0.0232 0.2070 1.0000
6.500 0.8610 0.02637 0.01524 -0.0225 0.1818 1.0000
6.750 0.8833 0.02763 0.01663 -0.0218 0.1593 1.0000
7.000 0.9046 0.02895 0.01800 -0.0211 0.1396 1.0000
7.250 0.9266 0.03054 0.01975 -0.0202 0.1247 1.0000
7.500 0.9473 0.03207 0.02146 -0.0195 0.1093 1.0000
7.750 0.9680 0.03392 0.02350 -0.0186 0.0984 1.0000
8.000 0.9879 0.03587 0.02557 -0.0178 0.0893 1.0000
8.250 1.0062 0.03779 0.02786 -0.0170 0.0786 1.0000
8.500 1.0242 0.04073 0.03125 -0.0160 0.0722 1.0000
8.750 1.0405 0.04318 0.03393 -0.0151 0.0660 1.0000
9.000 1.0518 0.04644 0.03773 -0.0141 0.0596 1.0000
9.250 1.0620 0.04975 0.04142 -0.0132 0.0554 1.0000
9.500 1.0721 0.05305 0.04483 -0.0124 0.0525 1.0000
9.750 1.0677 0.05808 0.05053 -0.0116 0.0507 1.0000
10.000 1.0573 0.06319 0.05614 -0.0113 0.0493 1.0000
10.250 1.0416 0.06830 0.06159 -0.0116 0.0487 1.0000
10.500 1.0212 0.07369 0.06719 -0.0129 0.0491 1.0000
10.750 1.0001 0.08019 0.07382 -0.0166 0.0499 1.0000
11.000 0.9802 0.08777 0.08147 -0.0219 0.0508 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG03 (flat aft bottom) (ag03-il)