AG04 (ag04-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 500,000 Max Cl/Cd: 76.77 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag04-il-500000.txt Download as CSV file: xf-ag04-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4779 0.12715 0.12499 0.0144 1.0000 0.0125
-10.750 -0.4764 0.12340 0.12124 0.0134 1.0000 0.0125
-9.250 -0.5955 0.10821 0.10603 0.0202 1.0000 0.0129
-9.000 -0.5927 0.10443 0.10225 0.0191 1.0000 0.0132
-8.750 -0.5885 0.10098 0.09882 0.0178 1.0000 0.0134
-8.500 -0.5840 0.09753 0.09538 0.0164 1.0000 0.0137
-8.250 -0.5799 0.09396 0.09183 0.0147 1.0000 0.0140
-8.000 -0.5761 0.09022 0.08811 0.0126 1.0000 0.0143
-7.750 -0.5728 0.08631 0.08422 0.0100 1.0000 0.0146
-7.500 -0.5682 0.08203 0.07996 0.0062 1.0000 0.0149
-7.250 -0.5587 0.07700 0.07495 0.0004 1.0000 0.0153
-7.000 -0.5463 0.07141 0.06934 -0.0063 1.0000 0.0158
-6.750 -0.5305 0.06515 0.06305 -0.0138 1.0000 0.0164
-6.500 -0.5112 0.05808 0.05589 -0.0215 1.0000 0.0172
-6.250 -0.4818 0.05091 0.04854 -0.0282 1.0000 0.0191
-6.000 -0.4596 0.04441 0.04174 -0.0322 1.0000 0.0193
-5.750 -0.4396 0.03886 0.03584 -0.0346 1.0000 0.0194
-5.500 -0.4280 0.02299 0.01883 -0.0373 1.0000 0.0118
-5.250 -0.4035 0.01946 0.01479 -0.0372 1.0000 0.0118
-5.000 -0.3778 0.01729 0.01225 -0.0368 1.0000 0.0120
-4.750 -0.3522 0.01518 0.00974 -0.0365 1.0000 0.0131
-4.500 -0.3263 0.01340 0.00772 -0.0360 1.0000 0.0134
-4.250 -0.3003 0.01204 0.00620 -0.0354 1.0000 0.0136
-4.000 -0.2742 0.01095 0.00499 -0.0349 1.0000 0.0144
-3.750 -0.2480 0.01024 0.00422 -0.0344 1.0000 0.0162
-3.500 -0.2217 0.00972 0.00364 -0.0339 1.0000 0.0190
-3.250 -0.1955 0.00902 0.00289 -0.0335 1.0000 0.0278
-3.000 -0.1694 0.00846 0.00239 -0.0330 1.0000 0.0524
-2.750 -0.1436 0.00809 0.00217 -0.0327 1.0000 0.0849
-2.500 -0.1178 0.00781 0.00201 -0.0323 1.0000 0.1192
-2.250 -0.0920 0.00753 0.00187 -0.0320 1.0000 0.1606
-2.000 -0.0618 0.00722 0.00176 -0.0327 0.9981 0.2169
-1.750 -0.0228 0.00682 0.00165 -0.0353 0.9916 0.3002
-1.500 0.0156 0.00640 0.00156 -0.0378 0.9832 0.4003
-1.250 0.0514 0.00598 0.00147 -0.0395 0.9705 0.5102
-1.000 0.0837 0.00544 0.00142 -0.0404 0.9537 0.6544
-0.750 0.1042 0.00464 0.00142 -0.0378 0.9308 0.9122
-0.500 0.1436 0.00459 0.00130 -0.0399 0.9057 1.0000
-0.250 0.1686 0.00466 0.00122 -0.0388 0.8747 1.0000
0.000 0.1938 0.00476 0.00116 -0.0379 0.8423 1.0000
0.250 0.2195 0.00489 0.00112 -0.0371 0.8079 1.0000
0.500 0.2455 0.00504 0.00109 -0.0364 0.7739 1.0000
0.750 0.2719 0.00519 0.00108 -0.0359 0.7394 1.0000
1.000 0.2985 0.00536 0.00108 -0.0354 0.7053 1.0000
1.250 0.3253 0.00553 0.00110 -0.0350 0.6710 1.0000
1.500 0.3522 0.00572 0.00113 -0.0347 0.6368 1.0000
1.750 0.3791 0.00591 0.00118 -0.0344 0.6016 1.0000
2.000 0.4061 0.00612 0.00123 -0.0341 0.5661 1.0000
2.250 0.4332 0.00633 0.00130 -0.0339 0.5296 1.0000
2.500 0.4602 0.00656 0.00139 -0.0337 0.4931 1.0000
2.750 0.4872 0.00681 0.00151 -0.0335 0.4560 1.0000
3.000 0.5142 0.00706 0.00163 -0.0333 0.4197 1.0000
3.250 0.5412 0.00734 0.00177 -0.0332 0.3845 1.0000
3.500 0.5681 0.00761 0.00192 -0.0330 0.3503 1.0000
3.750 0.5951 0.00790 0.00211 -0.0329 0.3181 1.0000
4.000 0.6220 0.00820 0.00230 -0.0327 0.2874 1.0000
4.250 0.6489 0.00850 0.00251 -0.0326 0.2585 1.0000
4.500 0.6757 0.00882 0.00273 -0.0324 0.2303 1.0000
4.750 0.7024 0.00915 0.00300 -0.0323 0.2036 1.0000
5.000 0.7290 0.00951 0.00327 -0.0322 0.1778 1.0000
5.500 0.7819 0.01028 0.00388 -0.0318 0.1283 1.0000
5.750 0.8081 0.01071 0.00423 -0.0316 0.1050 1.0000
6.000 0.8340 0.01120 0.00466 -0.0314 0.0828 1.0000
6.250 0.8597 0.01176 0.00514 -0.0312 0.0631 1.0000
6.500 0.8852 0.01234 0.00569 -0.0309 0.0478 1.0000
6.750 0.9105 0.01300 0.00634 -0.0305 0.0364 1.0000
7.000 0.9350 0.01383 0.00719 -0.0301 0.0271 1.0000
7.250 0.9607 0.01432 0.00775 -0.0297 0.0225 1.0000
7.500 0.9841 0.01536 0.00889 -0.0292 0.0175 1.0000
7.750 1.0090 0.01600 0.00960 -0.0288 0.0146 1.0000
8.000 1.0277 0.01812 0.01191 -0.0276 0.0117 1.0000
8.250 1.0517 0.01891 0.01283 -0.0270 0.0108 1.0000
8.500 1.0736 0.02017 0.01426 -0.0262 0.0098 1.0000
8.750 1.0954 0.02135 0.01556 -0.0255 0.0090 1.0000
9.000 1.1167 0.02244 0.01674 -0.0249 0.0081 1.0000
9.250 1.1256 0.02651 0.02121 -0.0231 0.0072 1.0000
9.500 1.1445 0.02805 0.02297 -0.0222 0.0070 1.0000
9.750 1.1606 0.03004 0.02526 -0.0211 0.0068 1.0000
10.000 1.1733 0.03250 0.02802 -0.0199 0.0066 1.0000
10.250 1.1817 0.03542 0.03128 -0.0186 0.0064 1.0000
10.500 1.1850 0.03876 0.03496 -0.0171 0.0062 1.0000
10.750 1.1814 0.04251 0.03905 -0.0157 0.0060 1.0000
11.000 1.1688 0.04626 0.04308 -0.0140 0.0060 1.0000
11.250 1.1519 0.05075 0.04781 -0.0146 0.0060 1.0000
11.500 1.1346 0.05675 0.05403 -0.0185 0.0060 1.0000
11.750 1.1165 0.06469 0.06218 -0.0252 0.0061 1.0000
12.000 1.0974 0.07416 0.07182 -0.0332 0.0062 1.0000
12.250 1.0763 0.08454 0.08233 -0.0409 0.0064 1.0000
12.500 1.0520 0.09559 0.09348 -0.0479 0.0066 1.0000
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Polar data table (+)
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