DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Reynolds number: 50,000 Max Cl/Cd: 12.52 at α=-0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-corrected-il-50000.txt Download as CSV file: xf-davis-corrected-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DAVIS BASIC B-24 WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3610 0.10914 0.10205 -0.0106 1.0000 0.3587
-9.500 -0.5340 0.07657 0.06974 -0.0419 1.0000 0.1850
-9.250 -0.5505 0.07173 0.06491 -0.0417 1.0000 0.1831
-9.000 -0.5705 0.06706 0.06026 -0.0409 1.0000 0.1817
-8.750 -0.5941 0.06254 0.05572 -0.0393 1.0000 0.1801
-8.500 -0.6184 0.05854 0.05163 -0.0366 1.0000 0.1789
-8.250 -0.6420 0.05532 0.04832 -0.0328 1.0000 0.1785
-8.000 -0.6663 0.05306 0.04597 -0.0278 1.0000 0.1782
-7.750 -0.6898 0.05129 0.04407 -0.0226 1.0000 0.1783
-7.500 -0.7077 0.04944 0.04202 -0.0181 1.0000 0.1791
-7.250 -0.7208 0.04743 0.03973 -0.0142 1.0000 0.1807
-7.000 -0.7304 0.04533 0.03721 -0.0107 1.0000 0.1832
-6.750 -0.7296 0.04349 0.03522 -0.0082 1.0000 0.1869
-6.500 -0.7149 0.04215 0.03386 -0.0075 0.9975 0.1932
-6.250 -0.6764 0.03958 0.03082 -0.0114 0.9840 0.2047
-6.000 -0.6364 0.03769 0.02856 -0.0149 0.9706 0.2192
-5.750 -0.5963 0.03617 0.02688 -0.0180 0.9570 0.2362
-5.500 -0.5579 0.03491 0.02561 -0.0206 0.9438 0.2556
-5.250 -0.5200 0.03388 0.02462 -0.0230 0.9309 0.2796
-5.000 -0.4784 0.03283 0.02360 -0.0258 0.9190 0.3104
-4.750 -0.4440 0.03203 0.02288 -0.0272 0.9065 0.3451
-4.500 -0.4156 0.03145 0.02248 -0.0274 0.8941 0.3829
-4.250 -0.3767 0.03083 0.02209 -0.0290 0.8835 0.4357
-4.000 -0.3494 0.03048 0.02198 -0.0285 0.8717 0.4884
-3.750 -0.3263 0.03037 0.02213 -0.0270 0.8604 0.5431
-3.500 -0.2852 0.03030 0.02233 -0.0275 0.8511 0.6140
-3.250 -0.2671 0.03072 0.02296 -0.0245 0.8394 0.6645
-3.000 -0.2064 0.03137 0.02371 -0.0262 0.8317 0.7335
-2.750 -0.1829 0.03231 0.02464 -0.0239 0.8198 0.7785
-2.500 -0.0603 0.03374 0.02574 -0.0346 0.8117 0.8331
-2.250 0.0444 0.03458 0.02627 -0.0454 0.8005 0.8731
-2.000 0.1505 0.03459 0.02596 -0.0576 0.7904 0.9089
-1.750 0.2389 0.03408 0.02520 -0.0681 0.7796 0.9416
-1.500 0.3150 0.03354 0.02449 -0.0782 0.7679 0.9721
-1.250 0.3992 0.03209 0.02280 -0.0893 0.7583 1.0000
-1.000 0.4019 0.03291 0.02362 -0.0883 0.7476 1.0000
-0.750 0.4142 0.03309 0.02368 -0.0870 0.7404 1.0000
-0.500 0.4132 0.03423 0.02482 -0.0854 0.7305 1.0000
-0.250 0.4236 0.03466 0.02516 -0.0838 0.7233 1.0000
0.000 0.4191 0.03603 0.02651 -0.0815 0.7149 1.0000
0.250 0.4215 0.03697 0.02741 -0.0793 0.7074 1.0000
0.500 0.4292 0.03774 0.02810 -0.0773 0.7011 1.0000
0.750 0.4026 0.03996 0.03032 -0.0726 0.6931 1.0000
1.000 0.4074 0.04089 0.03119 -0.0701 0.6872 1.0000
1.250 0.3963 0.04251 0.03275 -0.0663 0.6817 1.0000
1.500 0.3458 0.04511 0.03530 -0.0584 0.6765 1.0000
1.750 0.3194 0.04682 0.03692 -0.0524 0.6723 1.0000
2.000 0.3262 0.04803 0.03805 -0.0503 0.6681 1.0000
2.250 0.3271 0.04953 0.03945 -0.0476 0.6646 1.0000
2.500 0.2951 0.05160 0.04142 -0.0418 0.6633 1.0000
2.750 0.2805 0.05347 0.04321 -0.0382 0.6625 1.0000
3.000 0.2769 0.05537 0.04503 -0.0360 0.6632 1.0000
3.250 0.2799 0.05731 0.04691 -0.0347 0.6644 1.0000
3.500 0.0965 0.06081 0.05048 -0.0220 0.8387 1.0000
3.750 0.1272 0.06373 0.05332 -0.0242 0.8310 1.0000
4.000 0.1405 0.06465 0.05419 -0.0234 0.8161 1.0000
4.250 0.1514 0.06581 0.05529 -0.0224 0.8028 1.0000
4.500 0.1850 0.06908 0.05851 -0.0249 0.7945 1.0000
4.750 0.1918 0.06962 0.05902 -0.0233 0.7803 1.0000
5.000 0.2022 0.07104 0.06041 -0.0224 0.7692 1.0000
5.250 0.2355 0.07412 0.06346 -0.0246 0.7592 1.0000
5.500 0.2371 0.07464 0.06395 -0.0225 0.7459 1.0000
5.750 0.2710 0.07837 0.06767 -0.0249 0.7394 1.0000
6.000 0.2718 0.07860 0.06789 -0.0227 0.7252 1.0000
6.250 0.2818 0.08030 0.06957 -0.0221 0.7152 1.0000
6.500 0.3081 0.08293 0.07222 -0.0232 0.7049 1.0000
6.750 0.3095 0.08400 0.07327 -0.0216 0.6943 1.0000
7.000 0.3423 0.08745 0.07676 -0.0235 0.6853 1.0000
7.250 0.3386 0.08797 0.07727 -0.0214 0.6732 1.0000
7.500 0.3752 0.09216 0.08150 -0.0238 0.6661 1.0000
7.750 0.3667 0.09217 0.08151 -0.0214 0.6533 1.0000
8.000 0.4019 0.09662 0.08601 -0.0236 0.6468 1.0000
8.250 0.3953 0.09660 0.08601 -0.0214 0.6333 1.0000
8.500 0.4125 0.09966 0.08910 -0.0219 0.6265 1.0000
8.750 0.4238 0.10134 0.09082 -0.0216 0.6136 1.0000
9.000 0.4278 0.10325 0.09277 -0.0210 0.6044 1.0000
9.250 0.4537 0.10653 0.09612 -0.0220 0.5940 1.0000
9.500 0.4498 0.10773 0.09734 -0.0208 0.5830 1.0000
9.750 0.4881 0.11270 0.10242 -0.0229 0.5743 1.0000
10.000 0.4753 0.11272 0.10245 -0.0211 0.5614 1.0000
10.250 0.4893 0.11592 0.10572 -0.0215 0.5529 1.0000
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Polar data table (+)
Polar graphs
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