AG38 (ag38-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 500,000 Max Cl/Cd: 81.29 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag38-il-500000.txt Download as CSV file: xf-ag38-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG38
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4192 0.08200 0.07985 -0.0141 1.0000 0.0175
-9.250 -0.4203 0.07767 0.07554 -0.0158 1.0000 0.0176
-9.000 -0.4224 0.07330 0.07118 -0.0177 1.0000 0.0176
-8.750 -0.4261 0.06891 0.06682 -0.0198 1.0000 0.0176
-8.500 -0.4313 0.06428 0.06221 -0.0233 1.0000 0.0176
-8.250 -0.4306 0.05878 0.05668 -0.0279 1.0000 0.0176
-8.000 -0.4281 0.05317 0.05102 -0.0315 1.0000 0.0176
-7.750 -0.4385 0.04523 0.04304 -0.0336 1.0000 0.0182
-7.500 -0.4332 0.04158 0.03935 -0.0338 1.0000 0.0185
-7.250 -0.4257 0.03788 0.03559 -0.0342 1.0000 0.0188
-7.000 -0.4166 0.03437 0.03201 -0.0344 1.0000 0.0193
-6.750 -0.4058 0.03073 0.02824 -0.0346 1.0000 0.0198
-6.500 -0.3930 0.02705 0.02441 -0.0348 1.0000 0.0206
-6.250 -0.3776 0.02325 0.02039 -0.0348 1.0000 0.0220
-6.000 -0.3541 0.02133 0.01804 -0.0338 1.0000 0.0242
-5.750 -0.3428 0.01454 0.01080 -0.0343 1.0000 0.0255
-5.500 -0.3241 0.01296 0.00916 -0.0337 1.0000 0.0265
-5.250 -0.3041 0.01150 0.00756 -0.0329 1.0000 0.0280
-5.000 -0.2825 0.00996 0.00579 -0.0320 1.0000 0.0303
-4.750 -0.2514 0.01759 0.01232 -0.0342 1.0000 0.0261
-4.500 -0.2219 0.01366 0.00782 -0.0333 1.0000 0.0192
-4.250 -0.1961 0.01265 0.00671 -0.0327 1.0000 0.0197
-4.000 -0.1702 0.01192 0.00590 -0.0322 1.0000 0.0208
-3.750 -0.1333 0.01116 0.00508 -0.0340 0.9980 0.0222
-3.500 -0.0937 0.01077 0.00465 -0.0364 0.9954 0.0244
-3.250 -0.0558 0.00972 0.00356 -0.0385 0.9928 0.0280
-3.000 -0.0172 0.00930 0.00312 -0.0407 0.9889 0.0322
-2.750 0.0230 0.00880 0.00263 -0.0433 0.9855 0.0430
-2.500 0.0634 0.00798 0.00223 -0.0462 0.9824 0.1550
-2.250 0.0991 0.00692 0.00208 -0.0485 0.9760 0.4220
-2.000 0.1312 0.00562 0.00204 -0.0495 0.9698 0.7821
-1.750 0.1669 0.00516 0.00197 -0.0501 0.9587 1.0000
-1.500 0.1971 0.00509 0.00182 -0.0503 0.9426 1.0000
-1.250 0.2236 0.00504 0.00169 -0.0496 0.9192 1.0000
-1.000 0.2489 0.00501 0.00155 -0.0486 0.8772 1.0000
-0.750 0.2729 0.00512 0.00137 -0.0472 0.8273 1.0000
-0.500 0.2983 0.00533 0.00135 -0.0464 0.7862 1.0000
-0.250 0.3244 0.00553 0.00135 -0.0459 0.7465 1.0000
0.000 0.3507 0.00573 0.00136 -0.0454 0.7025 1.0000
0.250 0.3769 0.00598 0.00136 -0.0450 0.6465 1.0000
0.500 0.4033 0.00625 0.00141 -0.0447 0.6088 1.0000
0.750 0.4304 0.00648 0.00149 -0.0445 0.5835 1.0000
1.000 0.4578 0.00666 0.00158 -0.0444 0.5623 1.0000
1.250 0.4853 0.00684 0.00167 -0.0443 0.5431 1.0000
1.500 0.5128 0.00701 0.00176 -0.0443 0.5242 1.0000
1.750 0.5404 0.00716 0.00186 -0.0443 0.5044 1.0000
2.000 0.5679 0.00734 0.00197 -0.0442 0.4834 1.0000
2.250 0.5954 0.00750 0.00207 -0.0442 0.4579 1.0000
2.500 0.6226 0.00771 0.00216 -0.0442 0.4248 1.0000
2.750 0.6495 0.00799 0.00229 -0.0441 0.3844 1.0000
3.000 0.6761 0.00832 0.00248 -0.0440 0.3440 1.0000
3.250 0.7026 0.00869 0.00268 -0.0439 0.3044 1.0000
3.500 0.7290 0.00908 0.00291 -0.0439 0.2673 1.0000
3.750 0.7554 0.00946 0.00316 -0.0438 0.2325 1.0000
4.250 0.8078 0.01031 0.00375 -0.0437 0.1668 1.0000
4.500 0.8337 0.01077 0.00408 -0.0436 0.1354 1.0000
4.750 0.8594 0.01127 0.00445 -0.0435 0.1072 1.0000
5.000 0.8849 0.01180 0.00488 -0.0433 0.0828 1.0000
5.250 0.9099 0.01242 0.00539 -0.0431 0.0638 1.0000
5.500 0.9350 0.01303 0.00596 -0.0428 0.0520 1.0000
5.750 0.9606 0.01348 0.00644 -0.0426 0.0458 1.0000
6.000 0.9848 0.01421 0.00723 -0.0422 0.0401 1.0000
6.250 1.0101 0.01468 0.00775 -0.0419 0.0364 1.0000
6.500 1.0331 0.01555 0.00865 -0.0414 0.0323 1.0000
6.750 1.0563 0.01636 0.00957 -0.0408 0.0303 1.0000
7.000 1.0803 0.01698 0.01029 -0.0403 0.0285 1.0000
7.250 1.1041 0.01760 0.01097 -0.0399 0.0265 1.0000
7.500 1.1260 0.01850 0.01192 -0.0393 0.0245 1.0000
7.750 1.1429 0.02035 0.01392 -0.0379 0.0229 1.0000
8.000 1.1658 0.02106 0.01475 -0.0373 0.0221 1.0000
8.250 1.1876 0.02191 0.01574 -0.0366 0.0210 1.0000
8.500 1.2092 0.02272 0.01664 -0.0360 0.0198 1.0000
8.750 1.2302 0.02352 0.01751 -0.0353 0.0187 1.0000
9.000 1.2480 0.02484 0.01893 -0.0343 0.0177 1.0000
9.250 1.2552 0.02845 0.02283 -0.0320 0.0167 1.0000
9.500 1.2737 0.02941 0.02397 -0.0310 0.0163 1.0000
9.750 1.2900 0.03067 0.02542 -0.0298 0.0157 1.0000
10.000 1.3046 0.03201 0.02695 -0.0285 0.0150 1.0000
10.250 1.3179 0.03331 0.02841 -0.0271 0.0143 1.0000
10.500 1.3292 0.03467 0.02992 -0.0256 0.0137 1.0000
10.750 1.3377 0.03618 0.03156 -0.0238 0.0133 1.0000
11.000 1.3410 0.03783 0.03333 -0.0215 0.0129 1.0000
11.250 1.3361 0.04010 0.03576 -0.0185 0.0126 1.0000
11.500 1.3243 0.04334 0.03920 -0.0158 0.0124 1.0000
11.750 1.3065 0.04761 0.04373 -0.0142 0.0122 1.0000
12.000 1.2865 0.05277 0.04914 -0.0145 0.0121 1.0000
12.250 1.2665 0.05873 0.05534 -0.0166 0.0121 1.0000
12.500 1.2477 0.06537 0.06221 -0.0203 0.0121 1.0000
12.750 1.2298 0.07257 0.06960 -0.0249 0.0121 1.0000
13.000 1.2123 0.08012 0.07731 -0.0299 0.0121 1.0000
13.250 1.1949 0.08798 0.08532 -0.0349 0.0121 1.0000
13.500 1.1776 0.09622 0.09371 -0.0402 0.0122 1.0000
13.750 1.1589 0.10518 0.10280 -0.0457 0.0123 1.0000
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Polar data table (+)
Polar graphs
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