DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Reynolds number: 500,000 Max Cl/Cd: 96.3 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-corrected-il-500000.txt Download as CSV file: xf-davis-corrected-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.8957 0.10452 0.10129 -0.0299 1.0000 0.0246
-17.750 -0.9308 0.09398 0.09055 -0.0365 1.0000 0.0246
-17.500 -0.9624 0.08467 0.08104 -0.0423 1.0000 0.0247
-17.250 -0.9801 0.07795 0.07418 -0.0465 1.0000 0.0248
-17.000 -0.9966 0.07168 0.06776 -0.0505 1.0000 0.0251
-16.750 -1.0109 0.06601 0.06194 -0.0540 1.0000 0.0252
-16.500 -1.0229 0.06093 0.05671 -0.0569 1.0000 0.0254
-16.250 -1.0326 0.05635 0.05199 -0.0595 1.0000 0.0256
-16.000 -1.0404 0.05223 0.04772 -0.0616 1.0000 0.0258
-15.750 -1.0471 0.04842 0.04374 -0.0635 1.0000 0.0261
-15.500 -1.0512 0.04514 0.04031 -0.0647 1.0000 0.0263
-15.250 -1.0546 0.04214 0.03717 -0.0655 1.0000 0.0265
-15.000 -1.0564 0.03940 0.03435 -0.0655 1.0000 0.0269
-14.750 -1.0546 0.03719 0.03209 -0.0654 1.0000 0.0272
-14.500 -1.0514 0.03524 0.03009 -0.0650 1.0000 0.0275
-14.250 -1.0464 0.03362 0.02843 -0.0645 1.0000 0.0280
-14.000 -1.0417 0.03204 0.02677 -0.0637 1.0000 0.0284
-13.750 -1.0363 0.03060 0.02525 -0.0625 1.0000 0.0288
-13.500 -1.0305 0.02929 0.02385 -0.0612 1.0000 0.0294
-13.250 -1.0233 0.02822 0.02266 -0.0596 1.0000 0.0300
-13.000 -1.0159 0.02712 0.02145 -0.0578 1.0000 0.0303
-12.750 -1.0105 0.02581 0.02009 -0.0556 1.0000 0.0310
-12.500 -1.0030 0.02481 0.01907 -0.0534 1.0000 0.0316
-12.250 -0.9935 0.02406 0.01831 -0.0512 1.0000 0.0322
-12.000 -0.9837 0.02337 0.01758 -0.0487 1.0000 0.0329
-11.750 -0.9743 0.02271 0.01686 -0.0461 1.0000 0.0336
-11.500 -0.9648 0.02210 0.01618 -0.0432 1.0000 0.0343
-11.250 -0.9525 0.02159 0.01557 -0.0407 1.0000 0.0350
-11.000 -0.9443 0.02058 0.01458 -0.0379 1.0000 0.0359
-10.750 -0.9313 0.02001 0.01402 -0.0356 1.0000 0.0368
-10.500 -0.9168 0.01955 0.01354 -0.0334 1.0000 0.0379
-10.250 -0.9024 0.01909 0.01304 -0.0311 1.0000 0.0390
-10.000 -0.8766 0.01850 0.01238 -0.0312 0.9907 0.0402
-9.750 -0.8376 0.01751 0.01142 -0.0342 0.9729 0.0422
-9.500 -0.7905 0.01685 0.01070 -0.0385 0.9496 0.0444
-9.250 -0.7478 0.01607 0.00984 -0.0420 0.9144 0.0470
-9.000 -0.7221 0.01570 0.00934 -0.0417 0.8727 0.0491
-8.750 -0.7013 0.01545 0.00892 -0.0402 0.8396 0.0512
-8.250 -0.6624 0.01473 0.00799 -0.0371 0.7912 0.0559
-8.000 -0.6398 0.01453 0.00766 -0.0360 0.7714 0.0587
-7.750 -0.6198 0.01410 0.00718 -0.0345 0.7538 0.0620
-7.500 -0.5970 0.01386 0.00685 -0.0335 0.7381 0.0655
-7.250 -0.5749 0.01353 0.00646 -0.0324 0.7234 0.0695
-7.000 -0.5514 0.01327 0.00616 -0.0315 0.7096 0.0742
-6.750 -0.5285 0.01296 0.00580 -0.0305 0.6969 0.0794
-6.500 -0.5045 0.01276 0.00553 -0.0297 0.6850 0.0852
-6.250 -0.4810 0.01244 0.00523 -0.0289 0.6739 0.0925
-6.000 -0.4568 0.01222 0.00495 -0.0281 0.6635 0.1003
-5.750 -0.4321 0.01199 0.00471 -0.0274 0.6528 0.1096
-5.500 -0.4080 0.01173 0.00447 -0.0267 0.6434 0.1212
-5.250 -0.3834 0.01149 0.00424 -0.0260 0.6340 0.1344
-5.000 -0.3587 0.01127 0.00404 -0.0253 0.6256 0.1495
-4.750 -0.3338 0.01104 0.00385 -0.0247 0.6167 0.1670
-4.500 -0.3091 0.01084 0.00367 -0.0241 0.6086 0.1868
-4.250 -0.2841 0.01059 0.00350 -0.0235 0.6003 0.2100
-4.000 -0.2592 0.01042 0.00335 -0.0228 0.5930 0.2349
-3.750 -0.2342 0.01017 0.00322 -0.0222 0.5856 0.2634
-3.500 -0.2093 0.00997 0.00309 -0.0216 0.5781 0.2931
-3.250 -0.1844 0.00979 0.00298 -0.0210 0.5713 0.3254
-3.000 -0.1593 0.00958 0.00288 -0.0204 0.5643 0.3595
-2.750 -0.1345 0.00942 0.00279 -0.0197 0.5579 0.3951
-2.500 -0.1096 0.00924 0.00272 -0.0191 0.5518 0.4319
-2.250 -0.0848 0.00906 0.00265 -0.0184 0.5451 0.4696
-2.000 -0.0603 0.00893 0.00260 -0.0176 0.5390 0.5071
-1.750 -0.0354 0.00878 0.00256 -0.0169 0.5332 0.5444
-1.500 -0.0106 0.00864 0.00254 -0.0161 0.5274 0.5819
-1.250 0.0139 0.00855 0.00252 -0.0153 0.5219 0.6184
-1.000 0.0390 0.00845 0.00252 -0.0145 0.5164 0.6534
-0.750 0.0641 0.00836 0.00252 -0.0138 0.5107 0.6874
-0.500 0.0889 0.00830 0.00253 -0.0129 0.5053 0.7202
-0.250 0.1143 0.00827 0.00257 -0.0122 0.5004 0.7506
0.000 0.1403 0.00822 0.00261 -0.0115 0.4953 0.7797
0.250 0.1665 0.00820 0.00265 -0.0109 0.4901 0.8061
0.500 0.1928 0.00827 0.00272 -0.0103 0.4848 0.8313
0.750 0.2199 0.00826 0.00278 -0.0099 0.4801 0.8544
1.000 0.2481 0.00830 0.00286 -0.0097 0.4753 0.8745
1.250 0.2767 0.00839 0.00294 -0.0095 0.4705 0.8928
1.500 0.3056 0.00851 0.00304 -0.0095 0.4659 0.9093
1.750 0.3390 0.00860 0.00316 -0.0104 0.4609 0.9218
2.000 0.3727 0.00872 0.00327 -0.0114 0.4560 0.9324
2.250 0.4035 0.00890 0.00338 -0.0118 0.4515 0.9435
2.500 0.4426 0.00906 0.00354 -0.0140 0.4469 0.9489
2.750 0.4744 0.00918 0.00367 -0.0147 0.4423 0.9575
3.000 0.5169 0.00935 0.00379 -0.0177 0.4372 0.9600
3.250 0.5570 0.00957 0.00394 -0.0202 0.4325 0.9631
3.500 0.5929 0.00969 0.00408 -0.0218 0.4284 0.9686
3.750 0.6311 0.00981 0.00420 -0.0239 0.4238 0.9722
4.000 0.6710 0.00996 0.00431 -0.0264 0.4191 0.9751
4.250 0.7080 0.01013 0.00446 -0.0284 0.4146 0.9792
4.500 0.7444 0.01023 0.00459 -0.0302 0.4105 0.9834
4.750 0.7843 0.01032 0.00468 -0.0328 0.4059 0.9860
5.000 0.8222 0.01046 0.00478 -0.0350 0.4015 0.9893
5.250 0.8583 0.01062 0.00495 -0.0369 0.3974 0.9930
5.500 0.8975 0.01067 0.00505 -0.0394 0.3931 0.9957
5.750 0.9359 0.01074 0.00513 -0.0418 0.3886 0.9986
6.000 0.9661 0.01089 0.00524 -0.0425 0.3846 1.0000
6.250 0.9870 0.01102 0.00540 -0.0413 0.3810 1.0000
6.500 1.0076 0.01106 0.00549 -0.0401 0.3755 1.0000
6.750 1.0273 0.01115 0.00554 -0.0386 0.3682 1.0000
7.000 1.0474 0.01121 0.00566 -0.0372 0.3606 1.0000
7.250 1.0671 0.01132 0.00576 -0.0358 0.3536 1.0000
7.500 1.0868 0.01149 0.00593 -0.0344 0.3479 1.0000
7.750 1.1074 0.01160 0.00610 -0.0331 0.3420 1.0000
8.000 1.1265 0.01179 0.00627 -0.0316 0.3360 1.0000
8.250 1.1466 0.01195 0.00647 -0.0302 0.3301 1.0000
8.500 1.1662 0.01211 0.00667 -0.0287 0.3233 1.0000
8.750 1.1847 0.01234 0.00689 -0.0271 0.3167 1.0000
9.000 1.2044 0.01251 0.00711 -0.0257 0.3088 1.0000
9.250 1.2220 0.01278 0.00736 -0.0240 0.3008 1.0000
9.500 1.2402 0.01301 0.00762 -0.0223 0.2907 1.0000
9.750 1.2574 0.01330 0.00792 -0.0206 0.2802 1.0000
10.000 1.2725 0.01366 0.00825 -0.0185 0.2668 1.0000
10.250 1.2856 0.01410 0.00865 -0.0162 0.2510 1.0000
10.500 1.2948 0.01467 0.00915 -0.0132 0.2306 1.0000
10.750 1.2975 0.01546 0.00981 -0.0094 0.2058 1.0000
11.000 1.2890 0.01641 0.01062 -0.0037 0.1805 1.0000
11.250 1.2791 0.01767 0.01174 0.0014 0.1555 1.0000
11.500 1.2707 0.01920 0.01316 0.0053 0.1333 1.0000
11.750 1.2632 0.02105 0.01493 0.0083 0.1163 1.0000
12.000 1.2587 0.02305 0.01690 0.0103 0.1026 1.0000
12.250 1.2548 0.02529 0.01912 0.0117 0.0919 1.0000
12.500 1.2518 0.02768 0.02151 0.0126 0.0834 1.0000
12.750 1.2503 0.03008 0.02393 0.0132 0.0765 1.0000
13.000 1.2467 0.03280 0.02667 0.0136 0.0714 1.0000
13.250 1.2444 0.03547 0.02938 0.0139 0.0667 1.0000
13.500 1.2386 0.03854 0.03248 0.0140 0.0631 1.0000
13.750 1.2372 0.04122 0.03523 0.0141 0.0598 1.0000
14.000 1.2312 0.04443 0.03847 0.0141 0.0573 1.0000
14.250 1.2248 0.04772 0.04181 0.0140 0.0549 1.0000
14.500 1.2233 0.05059 0.04475 0.0138 0.0525 1.0000
14.750 1.2182 0.05396 0.04815 0.0134 0.0504 1.0000
15.000 1.2090 0.05783 0.05206 0.0129 0.0487 1.0000
15.250 1.2099 0.06061 0.05492 0.0126 0.0467 1.0000
15.500 1.2076 0.06383 0.05820 0.0120 0.0452 1.0000
15.750 1.2027 0.06738 0.06177 0.0114 0.0437 1.0000
16.000 1.1948 0.07133 0.06576 0.0106 0.0424 1.0000
16.250 1.1964 0.07419 0.06871 0.0101 0.0411 1.0000
16.500 1.1954 0.07738 0.07196 0.0094 0.0398 1.0000
16.750 1.1933 0.08074 0.07536 0.0087 0.0387 1.0000
17.000 1.1882 0.08451 0.07914 0.0078 0.0375 1.0000
17.250 1.1869 0.08778 0.08247 0.0070 0.0364 1.0000
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