NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=100,000 Ncrit=5
Details | Polar file |
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Airfoil: NACA 747A315 (naca747a315-il) Reynolds number: 100,000 Max Cl/Cd: 46.4 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a315-il-100000-n5.txt Download as CSV file: xf-naca747a315-il-100000-n5.csv |
XFOIL Version 6.96 Calculated polar for: NACA 747A315 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.4840 0.09445 0.08963 -0.0384 1.0000 0.0382 -11.250 -0.4988 0.08556 0.08079 -0.0447 1.0000 0.0380 -11.000 -0.5266 0.07520 0.07039 -0.0528 1.0000 0.0370 -10.750 -0.5599 0.06760 0.06266 -0.0571 1.0000 0.0364 -10.500 -0.5847 0.06248 0.05738 -0.0586 0.9718 0.0363 -10.250 -0.6005 0.05748 0.05204 -0.0600 0.9342 0.0362 -10.000 -0.6146 0.05426 0.04851 -0.0577 0.9088 0.0363 -9.750 -0.6257 0.05128 0.04520 -0.0547 0.8903 0.0365 -9.500 -0.6325 0.04833 0.04189 -0.0516 0.8749 0.0366 -9.250 -0.6342 0.04554 0.03872 -0.0487 0.8614 0.0368 -9.000 -0.6318 0.04288 0.03566 -0.0461 0.8496 0.0371 -8.750 -0.6258 0.04040 0.03277 -0.0435 0.8396 0.0376 -8.500 -0.6158 0.03811 0.03005 -0.0414 0.8288 0.0384 -8.250 -0.6041 0.03600 0.02740 -0.0391 0.8197 0.0396 -8.000 -0.5876 0.03414 0.02519 -0.0377 0.8107 0.0406 -7.750 -0.5676 0.03267 0.02357 -0.0368 0.8024 0.0415 -7.500 -0.5463 0.03123 0.02193 -0.0359 0.7940 0.0424 -7.250 -0.5238 0.02986 0.02034 -0.0351 0.7866 0.0436 -7.000 -0.4995 0.02855 0.01881 -0.0346 0.7786 0.0449 -6.750 -0.4756 0.02745 0.01742 -0.0337 0.7725 0.0471 -6.500 -0.4502 0.02633 0.01625 -0.0336 0.7647 0.0492 -6.250 -0.4258 0.02541 0.01527 -0.0331 0.7583 0.0512 -6.000 -0.4006 0.02451 0.01427 -0.0327 0.7519 0.0535 -5.750 -0.3755 0.02376 0.01336 -0.0322 0.7449 0.0566 -5.500 -0.3534 0.02294 0.01258 -0.0313 0.7393 0.0601 -5.250 -0.3304 0.02230 0.01188 -0.0306 0.7326 0.0642 -5.000 -0.3086 0.02164 0.01117 -0.0297 0.7264 0.0688 -4.750 -0.2872 0.02108 0.01056 -0.0286 0.7216 0.0752 -4.500 -0.2654 0.02053 0.01000 -0.0277 0.7154 0.0830 -4.250 -0.2434 0.02003 0.00949 -0.0268 0.7099 0.0948 -4.000 -0.2218 0.01945 0.00899 -0.0258 0.7055 0.1145 -3.750 -0.2008 0.01878 0.00859 -0.0249 0.7004 0.1642 -3.500 -0.1854 0.01768 0.00826 -0.0233 0.6951 0.3121 -3.250 -0.1774 0.01641 0.00811 -0.0196 0.6907 0.5385 -3.000 -0.1333 0.01730 0.00965 -0.0192 0.6874 0.7459 -2.750 -0.1186 0.01764 0.00989 -0.0163 0.6817 0.7844 -2.500 -0.0930 0.01836 0.01051 -0.0145 0.6769 0.8166 -2.000 -0.0008 0.02036 0.01216 -0.0168 0.6703 0.8728 -1.750 0.0436 0.02052 0.01219 -0.0199 0.6656 0.8790 -1.500 0.0601 0.02053 0.01212 -0.0180 0.6615 0.8879 -1.250 0.0986 0.02049 0.01194 -0.0202 0.6580 0.8909 -1.000 0.1334 0.02046 0.01177 -0.0216 0.6551 0.8955 -0.750 0.1526 0.02053 0.01176 -0.0202 0.6518 0.9041 -0.500 0.1920 0.02055 0.01173 -0.0228 0.6475 0.9074 -0.250 0.2242 0.02054 0.01166 -0.0240 0.6438 0.9115 0.000 0.2486 0.02053 0.01158 -0.0236 0.6407 0.9164 0.250 0.2720 0.02051 0.01148 -0.0231 0.6383 0.9207 0.500 0.3037 0.02053 0.01147 -0.0243 0.6353 0.9230 0.750 0.3328 0.02063 0.01158 -0.0252 0.6318 0.9258 1.000 0.3588 0.02072 0.01167 -0.0254 0.6287 0.9290 1.250 0.3802 0.02079 0.01172 -0.0246 0.6258 0.9328 1.500 0.4048 0.02081 0.01172 -0.0243 0.6232 0.9358 1.750 0.4353 0.02080 0.01168 -0.0252 0.6210 0.9376 2.000 0.4632 0.02101 0.01195 -0.0259 0.6178 0.9401 2.250 0.4887 0.02125 0.01225 -0.0263 0.6145 0.9429 2.500 0.5115 0.02143 0.01248 -0.0259 0.6113 0.9459 2.750 0.5320 0.02157 0.01265 -0.0249 0.6085 0.9494 3.000 0.5623 0.02164 0.01274 -0.0258 0.6062 0.9510 3.250 0.5915 0.02169 0.01281 -0.0264 0.6042 0.9527 3.500 0.6157 0.02213 0.01339 -0.0268 0.5995 0.9555 3.750 0.6391 0.02243 0.01379 -0.0267 0.5956 0.9585 4.000 0.6608 0.02261 0.01402 -0.0260 0.5923 0.9613 4.250 0.6878 0.02267 0.01414 -0.0262 0.5895 0.9632 4.500 0.7181 0.02274 0.01426 -0.0270 0.5870 0.9650 4.750 0.7402 0.02338 0.01511 -0.0273 0.5812 0.9681 5.000 0.7642 0.02362 0.01547 -0.0272 0.5769 0.9707 5.250 0.7892 0.02367 0.01558 -0.0269 0.5736 0.9731 5.500 0.8168 0.02369 0.01570 -0.0271 0.5699 0.9750 5.750 0.8399 0.02414 0.01635 -0.0273 0.5618 0.9779 6.000 0.8722 0.02369 0.01595 -0.0277 0.5563 0.9798 6.250 0.8930 0.02400 0.01644 -0.0273 0.5477 0.9835 6.500 0.9258 0.02318 0.01565 -0.0273 0.5392 0.9851 6.750 0.9513 0.02296 0.01557 -0.0272 0.5254 0.9878 7.000 0.9772 0.02251 0.01522 -0.0268 0.5094 0.9907 7.250 1.0006 0.02210 0.01489 -0.0261 0.4885 0.9942 7.500 1.0223 0.02203 0.01493 -0.0256 0.4595 0.9986 7.750 1.0246 0.02250 0.01555 -0.0222 0.4346 1.0000 8.000 1.0191 0.02293 0.01603 -0.0171 0.4085 1.0000 8.250 1.0122 0.02302 0.01591 -0.0113 0.3679 1.0000 8.500 0.9900 0.02344 0.01612 -0.0035 0.3417 1.0000 8.750 0.9641 0.02418 0.01670 0.0042 0.3218 1.0000 9.000 0.9475 0.02554 0.01782 0.0092 0.2901 1.0000 9.250 0.9334 0.02749 0.01953 0.0128 0.2534 1.0000 9.500 0.9213 0.02980 0.02161 0.0154 0.2189 1.0000 9.750 0.9115 0.03225 0.02385 0.0174 0.1861 1.0000 10.000 0.9037 0.03475 0.02613 0.0191 0.1543 1.0000 10.250 0.8983 0.03719 0.02837 0.0204 0.1244 1.0000 10.500 0.8964 0.03944 0.03046 0.0215 0.1015 1.0000 10.750 0.8964 0.04160 0.03249 0.0225 0.0844 1.0000 11.000 0.8982 0.04366 0.03448 0.0234 0.0725 1.0000 11.250 0.9010 0.04568 0.03646 0.0241 0.0643 1.0000 11.500 0.9066 0.04752 0.03833 0.0248 0.0583 1.0000 12.000 0.9169 0.05142 0.04227 0.0258 0.0503 1.0000 12.250 0.9222 0.05342 0.04429 0.0262 0.0472 1.0000 12.500 0.9285 0.05534 0.04625 0.0265 0.0447 1.0000 12.750 0.9366 0.05713 0.04812 0.0269 0.0423 1.0000 13.000 0.9442 0.05898 0.05001 0.0272 0.0404 1.0000 13.250 0.9521 0.06079 0.05182 0.0276 0.0391 1.0000 13.500 0.9630 0.06237 0.05348 0.0281 0.0375 1.0000 13.750 0.9737 0.06403 0.05527 0.0284 0.0359 1.0000 14.000 0.9831 0.06588 0.05718 0.0286 0.0344 1.0000 14.250 0.9926 0.06770 0.05901 0.0287 0.0332 1.0000 14.500 1.0054 0.06924 0.06054 0.0292 0.0322 1.0000 14.750 1.0170 0.07109 0.06258 0.0295 0.0316 1.0000 15.000 1.0265 0.07328 0.06497 0.0296 0.0309 1.0000 15.250 1.0343 0.07571 0.06759 0.0296 0.0302 1.0000 15.500 1.0394 0.07850 0.07057 0.0294 0.0297 1.0000 15.750 1.0421 0.08158 0.07384 0.0289 0.0292 1.0000 16.000 1.0425 0.08497 0.07740 0.0282 0.0288 1.0000 16.250 1.0411 0.08863 0.08124 0.0272 0.0283 1.0000 16.500 1.0385 0.09248 0.08525 0.0260 0.0279 1.0000 16.750 1.0340 0.09669 0.08962 0.0245 0.0277 1.0000 17.000 1.0296 0.10094 0.09401 0.0229 0.0273 1.0000 17.250 1.0236 0.10554 0.09877 0.0210 0.0270 1.0000 17.500 1.0124 0.11119 0.10459 0.0184 0.0268 1.0000 17.750 0.9925 0.11857 0.11223 0.0144 0.0267 1.0000 18.000 0.9747 0.12602 0.11990 0.0102 0.0267 1.0000 18.250 0.9563 0.13405 0.12811 0.0055 0.0268 1.0000 |
Polar data table (+)
Polar graphs
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