AG38 (ag38-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 200,000 Max Cl/Cd: 59.33 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag38-il-200000-n5.txt Download as CSV file: xf-ag38-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5325 0.11262 0.10894 0.0047 1.0000 0.0232
-10.250 -0.5305 0.10872 0.10507 0.0012 1.0000 0.0237
-10.000 -0.5275 0.10477 0.10115 -0.0018 1.0000 0.0239
-9.750 -0.5245 0.10078 0.09718 -0.0046 1.0000 0.0240
-9.500 -0.5218 0.09672 0.09316 -0.0073 1.0000 0.0240
-9.250 -0.5193 0.09269 0.08917 -0.0100 1.0000 0.0241
-9.000 -0.5165 0.08845 0.08495 -0.0135 1.0000 0.0241
-8.750 -0.5097 0.08362 0.08013 -0.0182 1.0000 0.0241
-8.500 -0.5012 0.07859 0.07506 -0.0227 1.0000 0.0241
-8.250 -0.4916 0.07347 0.06991 -0.0268 1.0000 0.0241
-8.000 -0.4941 0.06764 0.06409 -0.0258 1.0000 0.0167
-7.750 -0.4835 0.06285 0.05924 -0.0291 1.0000 0.0161
-7.500 -0.4708 0.05744 0.05372 -0.0326 1.0000 0.0156
-7.250 -0.4563 0.05169 0.04780 -0.0356 1.0000 0.0151
-7.000 -0.4402 0.04585 0.04171 -0.0378 1.0000 0.0148
-6.750 -0.4221 0.04093 0.03650 -0.0389 1.0000 0.0153
-6.500 -0.4022 0.03578 0.03094 -0.0394 1.0000 0.0163
-6.250 -0.3816 0.03135 0.02607 -0.0394 1.0000 0.0164
-6.000 -0.3599 0.02751 0.02175 -0.0391 1.0000 0.0162
-5.750 -0.3368 0.02426 0.01801 -0.0385 1.0000 0.0162
-5.500 -0.3128 0.02166 0.01493 -0.0378 1.0000 0.0165
-5.250 -0.2882 0.01965 0.01248 -0.0370 1.0000 0.0169
-5.000 -0.2634 0.01816 0.01065 -0.0362 1.0000 0.0174
-4.750 -0.2389 0.01676 0.00909 -0.0355 1.0000 0.0185
-4.500 -0.2146 0.01617 0.00848 -0.0349 1.0000 0.0203
-4.250 -0.1896 0.01534 0.00754 -0.0343 1.0000 0.0218
-4.000 -0.1643 0.01450 0.00659 -0.0336 1.0000 0.0230
-3.750 -0.1389 0.01386 0.00587 -0.0330 1.0000 0.0242
-3.500 -0.1039 0.01304 0.00508 -0.0347 0.9965 0.0279
-3.250 -0.0669 0.01255 0.00453 -0.0367 0.9919 0.0324
-3.000 -0.0297 0.01197 0.00393 -0.0387 0.9866 0.0393
-2.750 0.0081 0.01152 0.00350 -0.0408 0.9810 0.0564
-2.500 0.0445 0.01085 0.00319 -0.0428 0.9739 0.1369
-2.250 0.0789 0.00988 0.00301 -0.0448 0.9658 0.3536
-2.000 0.1065 0.00848 0.00299 -0.0448 0.9567 0.7212
-1.750 0.1466 0.00794 0.00290 -0.0461 0.9449 1.0000
-1.500 0.1805 0.00789 0.00271 -0.0472 0.9278 1.0000
-1.250 0.2111 0.00785 0.00255 -0.0475 0.9018 1.0000
-1.000 0.2425 0.00779 0.00236 -0.0478 0.8605 1.0000
-0.750 0.2727 0.00779 0.00214 -0.0476 0.8214 1.0000
-0.500 0.2993 0.00791 0.00204 -0.0469 0.7832 1.0000
-0.250 0.3252 0.00809 0.00201 -0.0462 0.7452 1.0000
0.000 0.3511 0.00828 0.00201 -0.0455 0.7052 1.0000
0.250 0.3769 0.00850 0.00201 -0.0449 0.6583 1.0000
0.500 0.4024 0.00877 0.00203 -0.0443 0.6193 1.0000
0.750 0.4285 0.00903 0.00210 -0.0438 0.5909 1.0000
1.000 0.4550 0.00928 0.00221 -0.0435 0.5672 1.0000
1.250 0.4818 0.00951 0.00233 -0.0433 0.5455 1.0000
1.500 0.5085 0.00974 0.00247 -0.0431 0.5249 1.0000
1.750 0.5355 0.00995 0.00261 -0.0429 0.5035 1.0000
2.000 0.5623 0.01017 0.00278 -0.0427 0.4812 1.0000
2.250 0.5891 0.01038 0.00294 -0.0426 0.4550 1.0000
2.500 0.6157 0.01062 0.00309 -0.0424 0.4236 1.0000
2.750 0.6419 0.01091 0.00326 -0.0422 0.3876 1.0000
3.000 0.6678 0.01127 0.00350 -0.0419 0.3495 1.0000
3.250 0.6935 0.01169 0.00375 -0.0417 0.3104 1.0000
3.500 0.7191 0.01212 0.00404 -0.0415 0.2722 1.0000
3.750 0.7446 0.01259 0.00437 -0.0413 0.2367 1.0000
4.000 0.7701 0.01307 0.00475 -0.0412 0.2032 1.0000
4.250 0.7954 0.01358 0.00514 -0.0410 0.1725 1.0000
4.500 0.8206 0.01411 0.00557 -0.0408 0.1438 1.0000
4.750 0.8457 0.01466 0.00604 -0.0406 0.1183 1.0000
5.000 0.8705 0.01526 0.00658 -0.0403 0.0955 1.0000
5.250 0.8950 0.01589 0.00716 -0.0401 0.0781 1.0000
5.500 0.9193 0.01655 0.00779 -0.0397 0.0647 1.0000
5.750 0.9436 0.01719 0.00845 -0.0394 0.0550 1.0000
6.000 0.9675 0.01788 0.00924 -0.0390 0.0487 1.0000
6.250 0.9909 0.01863 0.01003 -0.0385 0.0432 1.0000
6.500 1.0138 0.01944 0.01092 -0.0380 0.0389 1.0000
6.750 1.0369 0.02020 0.01179 -0.0374 0.0354 1.0000
7.000 1.0585 0.02115 0.01281 -0.0368 0.0328 1.0000
7.250 1.0787 0.02233 0.01411 -0.0359 0.0306 1.0000
7.500 1.1005 0.02321 0.01516 -0.0352 0.0285 1.0000
7.750 1.1216 0.02416 0.01623 -0.0345 0.0264 1.0000
8.000 1.1415 0.02526 0.01745 -0.0337 0.0250 1.0000
8.250 1.1589 0.02676 0.01903 -0.0326 0.0236 1.0000
8.500 1.1762 0.02834 0.02082 -0.0315 0.0226 1.0000
8.750 1.1947 0.02961 0.02232 -0.0305 0.0213 1.0000
9.000 1.2118 0.03097 0.02390 -0.0295 0.0200 1.0000
9.250 1.2272 0.03253 0.02564 -0.0283 0.0191 1.0000
9.500 1.2412 0.03412 0.02741 -0.0270 0.0183 1.0000
9.750 1.2531 0.03583 0.02928 -0.0256 0.0177 1.0000
10.000 1.2605 0.03809 0.03171 -0.0239 0.0170 1.0000
10.250 1.2646 0.04059 0.03450 -0.0219 0.0164 1.0000
10.500 1.2662 0.04279 0.03705 -0.0196 0.0159 1.0000
10.750 1.2619 0.04521 0.03976 -0.0169 0.0154 1.0000
11.000 1.2547 0.04807 0.04289 -0.0149 0.0150 1.0000
11.250 1.2445 0.05153 0.04662 -0.0139 0.0147 1.0000
11.500 1.2317 0.05579 0.05114 -0.0142 0.0146 1.0000
11.750 1.2168 0.06097 0.05657 -0.0161 0.0144 1.0000
12.000 1.1993 0.06733 0.06318 -0.0196 0.0144 1.0000
12.250 1.1790 0.07504 0.07112 -0.0246 0.0144 1.0000
12.500 1.1549 0.08414 0.08043 -0.0306 0.0145 1.0000
12.750 1.1256 0.09505 0.09153 -0.0378 0.0148 1.0000
13.000 1.0889 0.10860 0.10520 -0.0461 0.0153 1.0000
13.250 1.0463 0.12437 0.12106 -0.0548 0.0161 1.0000
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Polar data table (+)
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