DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Reynolds number: 200,000 Max Cl/Cd: 63.87 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-corrected-il-200000.txt Download as CSV file: xf-davis-corrected-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6560 0.08673 0.08274 -0.0423 1.0000 0.0513
-13.500 -0.7365 0.06896 0.06472 -0.0552 1.0000 0.0493
-13.250 -0.8183 0.05632 0.05161 -0.0632 1.0000 0.0478
-13.000 -0.8597 0.05060 0.04555 -0.0640 1.0000 0.0474
-12.750 -0.8763 0.04749 0.04225 -0.0627 1.0000 0.0476
-12.500 -0.8802 0.04564 0.04031 -0.0610 1.0000 0.0484
-12.250 -0.8913 0.04343 0.03792 -0.0582 1.0000 0.0489
-12.000 -0.9017 0.04152 0.03582 -0.0546 1.0000 0.0496
-11.750 -0.9101 0.03951 0.03355 -0.0509 1.0000 0.0503
-11.500 -0.9144 0.03750 0.03124 -0.0474 1.0000 0.0511
-11.250 -0.9169 0.03579 0.02916 -0.0438 1.0000 0.0519
-11.000 -0.9028 0.03363 0.02698 -0.0426 1.0000 0.0530
-10.750 -0.8881 0.03243 0.02576 -0.0411 1.0000 0.0541
-10.500 -0.8747 0.03134 0.02460 -0.0392 1.0000 0.0555
-10.250 -0.8632 0.03025 0.02337 -0.0370 1.0000 0.0571
-10.000 -0.8542 0.02917 0.02205 -0.0341 1.0000 0.0586
-9.750 -0.8396 0.02769 0.02054 -0.0324 1.0000 0.0603
-9.500 -0.8260 0.02684 0.01976 -0.0304 1.0000 0.0618
-9.250 -0.8190 0.02620 0.01910 -0.0273 0.9993 0.0634
-9.000 -0.7759 0.02507 0.01769 -0.0309 0.9857 0.0669
-8.750 -0.7329 0.02351 0.01625 -0.0346 0.9732 0.0705
-8.500 -0.6893 0.02250 0.01512 -0.0380 0.9573 0.0748
-8.250 -0.6465 0.02123 0.01385 -0.0414 0.9390 0.0795
-8.000 -0.6079 0.02045 0.01295 -0.0436 0.9146 0.0848
-7.750 -0.5765 0.01951 0.01198 -0.0444 0.8887 0.0899
-7.500 -0.5520 0.01905 0.01140 -0.0437 0.8631 0.0955
-7.250 -0.5307 0.01839 0.01068 -0.0423 0.8403 0.1011
-7.000 -0.5093 0.01804 0.01021 -0.0410 0.8204 0.1078
-6.750 -0.4888 0.01747 0.00962 -0.0396 0.8026 0.1150
-6.500 -0.4667 0.01716 0.00916 -0.0383 0.7862 0.1237
-6.250 -0.4460 0.01666 0.00868 -0.0370 0.7717 0.1337
-6.000 -0.4247 0.01623 0.00822 -0.0357 0.7585 0.1452
-5.750 -0.4031 0.01581 0.00781 -0.0345 0.7447 0.1590
-5.500 -0.3812 0.01544 0.00745 -0.0333 0.7324 0.1754
-5.250 -0.3591 0.01510 0.00709 -0.0322 0.7216 0.1951
-5.000 -0.3366 0.01476 0.00679 -0.0312 0.7099 0.2184
-4.750 -0.3149 0.01440 0.00652 -0.0300 0.7002 0.2449
-4.500 -0.2927 0.01407 0.00627 -0.0289 0.6895 0.2756
-4.250 -0.2704 0.01378 0.00607 -0.0278 0.6804 0.3099
-4.000 -0.2482 0.01349 0.00589 -0.0267 0.6709 0.3473
-3.750 -0.2259 0.01325 0.00575 -0.0256 0.6627 0.3873
-3.500 -0.2035 0.01301 0.00563 -0.0244 0.6535 0.4289
-3.250 -0.1810 0.01283 0.00552 -0.0232 0.6461 0.4709
-3.000 -0.1585 0.01262 0.00547 -0.0220 0.6373 0.5130
-2.750 -0.1354 0.01247 0.00540 -0.0208 0.6304 0.5553
-2.500 -0.1123 0.01235 0.00541 -0.0196 0.6226 0.5967
-2.250 -0.0886 0.01223 0.00539 -0.0184 0.6151 0.6364
-2.000 -0.0643 0.01219 0.00541 -0.0173 0.6086 0.6745
-1.750 -0.0398 0.01213 0.00547 -0.0162 0.6009 0.7110
-1.500 -0.0143 0.01214 0.00550 -0.0152 0.5947 0.7455
-1.250 0.0120 0.01219 0.00561 -0.0144 0.5882 0.7772
-1.000 0.0394 0.01224 0.00571 -0.0138 0.5810 0.8059
-0.750 0.0680 0.01237 0.00579 -0.0133 0.5753 0.8328
-0.500 0.0974 0.01253 0.00598 -0.0131 0.5688 0.8563
-0.250 0.1304 0.01273 0.00614 -0.0135 0.5623 0.8761
0.000 0.1646 0.01297 0.00628 -0.0142 0.5568 0.8935
0.250 0.1982 0.01321 0.00651 -0.0149 0.5500 0.9094
0.500 0.2441 0.01348 0.00671 -0.0180 0.5434 0.9177
0.750 0.2837 0.01377 0.00686 -0.0200 0.5384 0.9288
1.000 0.3322 0.01401 0.00711 -0.0239 0.5313 0.9354
1.250 0.3730 0.01419 0.00722 -0.0262 0.5251 0.9448
1.500 0.4196 0.01443 0.00731 -0.0298 0.5199 0.9516
1.750 0.4608 0.01458 0.00751 -0.0326 0.5136 0.9603
2.000 0.5036 0.01470 0.00758 -0.0356 0.5079 0.9684
2.250 0.5485 0.01483 0.00758 -0.0391 0.5029 0.9749
2.500 0.5897 0.01494 0.00775 -0.0420 0.4967 0.9831
2.750 0.6352 0.01495 0.00775 -0.0458 0.4911 0.9895
3.000 0.6791 0.01498 0.00768 -0.0493 0.4864 0.9959
3.250 0.7147 0.01504 0.00778 -0.0513 0.4810 1.0000
3.500 0.7343 0.01512 0.00790 -0.0502 0.4761 1.0000
3.750 0.7550 0.01521 0.00796 -0.0491 0.4720 1.0000
4.000 0.7767 0.01536 0.00804 -0.0482 0.4685 1.0000
4.250 0.7961 0.01556 0.00831 -0.0470 0.4640 1.0000
4.500 0.8157 0.01572 0.00854 -0.0457 0.4592 1.0000
4.750 0.8367 0.01587 0.00868 -0.0446 0.4550 1.0000
5.000 0.8589 0.01607 0.00882 -0.0437 0.4516 1.0000
5.250 0.8786 0.01637 0.00918 -0.0424 0.4475 1.0000
5.500 0.8977 0.01660 0.00952 -0.0410 0.4427 1.0000
5.750 0.9187 0.01680 0.00973 -0.0399 0.4385 1.0000
6.000 0.9413 0.01703 0.00992 -0.0390 0.4351 1.0000
6.250 0.9620 0.01738 0.01031 -0.0378 0.4313 1.0000
6.500 0.9800 0.01769 0.01075 -0.0363 0.4264 1.0000
6.750 1.0007 0.01795 0.01104 -0.0351 0.4222 1.0000
7.000 1.0239 0.01817 0.01123 -0.0342 0.4186 1.0000
7.250 1.0455 0.01853 0.01162 -0.0332 0.4147 1.0000
7.500 1.0620 0.01875 0.01199 -0.0313 0.4083 1.0000
7.750 1.0862 0.01852 0.01163 -0.0304 0.4008 1.0000
8.000 1.1018 0.01856 0.01178 -0.0282 0.3920 1.0000
8.250 1.1239 0.01848 0.01165 -0.0270 0.3849 1.0000
8.500 1.1420 0.01871 0.01195 -0.0254 0.3786 1.0000
8.750 1.1606 0.01882 0.01215 -0.0238 0.3719 1.0000
9.000 1.1831 0.01893 0.01218 -0.0228 0.3658 1.0000
9.250 1.1973 0.01914 0.01257 -0.0206 0.3584 1.0000
9.500 1.2172 0.01921 0.01261 -0.0192 0.3514 1.0000
9.750 1.2317 0.01944 0.01298 -0.0170 0.3435 1.0000
10.000 1.2486 0.01955 0.01309 -0.0152 0.3355 1.0000
10.250 1.2612 0.01980 0.01348 -0.0127 0.3266 1.0000
10.500 1.2753 0.01998 0.01364 -0.0105 0.3175 1.0000
10.750 1.2841 0.02029 0.01408 -0.0076 0.3066 1.0000
11.000 1.2918 0.02065 0.01451 -0.0045 0.2951 1.0000
11.250 1.2941 0.02109 0.01496 -0.0006 0.2831 1.0000
11.500 1.2924 0.02170 0.01559 0.0035 0.2693 1.0000
11.750 1.2890 0.02261 0.01653 0.0072 0.2516 1.0000
12.000 1.2810 0.02404 0.01790 0.0106 0.2299 1.0000
12.250 1.2676 0.02620 0.01996 0.0134 0.2043 1.0000
12.500 1.2491 0.02921 0.02285 0.0155 0.1793 1.0000
12.750 1.2283 0.03290 0.02641 0.0169 0.1579 1.0000
13.000 1.2081 0.03689 0.03031 0.0176 0.1422 1.0000
13.250 1.1891 0.04102 0.03437 0.0179 0.1294 1.0000
13.500 1.1737 0.04495 0.03827 0.0181 0.1190 1.0000
13.750 1.1603 0.04877 0.04208 0.0181 0.1105 1.0000
14.000 1.1462 0.05278 0.04601 0.0180 0.1043 1.0000
14.250 1.1402 0.05611 0.04939 0.0178 0.0973 1.0000
14.500 1.1317 0.05968 0.05287 0.0176 0.0921 1.0000
14.750 1.1297 0.06270 0.05596 0.0173 0.0868 1.0000
15.000 1.1261 0.06574 0.05892 0.0172 0.0827 1.0000
15.250 1.1268 0.06852 0.06177 0.0170 0.0783 1.0000
15.500 1.1272 0.07131 0.06456 0.0166 0.0748 1.0000
15.750 1.1306 0.07350 0.06669 0.0168 0.0714 1.0000
16.000 1.1331 0.07618 0.06945 0.0164 0.0682 1.0000
16.250 1.1364 0.07866 0.07192 0.0161 0.0655 1.0000
16.500 1.1441 0.08029 0.07350 0.0166 0.0627 1.0000
16.750 1.1474 0.08293 0.07625 0.0161 0.0604 1.0000
17.000 1.1527 0.08520 0.07854 0.0159 0.0582 1.0000
17.250 1.1672 0.08572 0.07890 0.0169 0.0557 1.0000
17.500 1.1680 0.08886 0.08222 0.0161 0.0543 1.0000
17.750 1.1708 0.09166 0.08512 0.0154 0.0525 1.0000
18.000 1.1766 0.09390 0.08739 0.0151 0.0508 1.0000
18.250 1.1907 0.09467 0.08807 0.0157 0.0491 1.0000
18.500 1.1947 0.09724 0.09076 0.0153 0.0480 1.0000
18.750 1.1930 0.10083 0.09452 0.0141 0.0468 1.0000
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Polar data table (+)
Polar graphs
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