DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Reynolds number: 100,000 Max Cl/Cd: 36.43 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-corrected-il-100000.txt Download as CSV file: xf-davis-corrected-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5724 0.08069 0.07547 -0.0481 1.0000 0.0970
-11.250 -0.5914 0.07374 0.06851 -0.0515 1.0000 0.0962
-11.000 -0.6222 0.06681 0.06153 -0.0547 1.0000 0.0946
-10.750 -0.6666 0.06063 0.05521 -0.0553 1.0000 0.0926
-10.500 -0.7061 0.05632 0.05073 -0.0521 1.0000 0.0916
-10.250 -0.7347 0.05224 0.04638 -0.0487 1.0000 0.0910
-10.000 -0.7482 0.04903 0.04293 -0.0455 1.0000 0.0916
-9.750 -0.7573 0.04605 0.03969 -0.0422 1.0000 0.0926
-9.500 -0.7635 0.04329 0.03662 -0.0387 1.0000 0.0935
-9.250 -0.7685 0.04082 0.03386 -0.0349 1.0000 0.0947
-9.000 -0.7752 0.03891 0.03164 -0.0304 1.0000 0.0961
-8.750 -0.7892 0.03782 0.03030 -0.0247 1.0000 0.0970
-8.500 -0.7960 0.03648 0.02885 -0.0207 0.9987 0.0984
-8.250 -0.7481 0.03448 0.02689 -0.0257 0.9869 0.1036
-8.000 -0.7067 0.03226 0.02408 -0.0293 0.9732 0.1093
-7.750 -0.6603 0.03026 0.02214 -0.0337 0.9614 0.1161
-7.500 -0.6137 0.02841 0.01994 -0.0377 0.9503 0.1245
-7.250 -0.5660 0.02692 0.01846 -0.0417 0.9390 0.1342
-7.000 -0.5248 0.02550 0.01704 -0.0444 0.9242 0.1445
-6.750 -0.4878 0.02430 0.01574 -0.0461 0.9083 0.1563
-6.500 -0.4554 0.02339 0.01472 -0.0468 0.8917 0.1697
-6.250 -0.4273 0.02266 0.01394 -0.0467 0.8749 0.1845
-6.000 -0.4018 0.02194 0.01324 -0.0460 0.8586 0.2009
-5.750 -0.3780 0.02123 0.01263 -0.0451 0.8433 0.2196
-5.500 -0.3557 0.02064 0.01213 -0.0438 0.8294 0.2411
-5.250 -0.3349 0.02015 0.01168 -0.0422 0.8153 0.2670
-5.000 -0.3152 0.01968 0.01136 -0.0406 0.8014 0.2954
-4.750 -0.2953 0.01925 0.01105 -0.0389 0.7892 0.3295
-4.500 -0.2754 0.01885 0.01078 -0.0371 0.7780 0.3682
-4.250 -0.2564 0.01856 0.01064 -0.0353 0.7657 0.4103
-4.000 -0.2363 0.01827 0.01051 -0.0334 0.7561 0.4549
-3.750 -0.2167 0.01807 0.01047 -0.0315 0.7448 0.5013
-3.500 -0.1960 0.01792 0.01049 -0.0296 0.7352 0.5474
-3.250 -0.1749 0.01784 0.01051 -0.0277 0.7254 0.5941
-3.000 -0.1524 0.01784 0.01064 -0.0259 0.7165 0.6380
-2.750 -0.1289 0.01788 0.01078 -0.0242 0.7072 0.6805
-2.500 -0.1043 0.01802 0.01095 -0.0226 0.6989 0.7208
-2.250 -0.0779 0.01823 0.01121 -0.0213 0.6897 0.7576
-2.000 -0.0471 0.01852 0.01145 -0.0205 0.6827 0.7905
-1.750 -0.0175 0.01891 0.01184 -0.0199 0.6731 0.8205
-1.500 0.0236 0.01933 0.01210 -0.0208 0.6663 0.8446
-1.250 0.0639 0.01989 0.01262 -0.0223 0.6566 0.8664
-1.000 0.1134 0.02032 0.01288 -0.0252 0.6493 0.8842
-0.750 0.1666 0.02083 0.01329 -0.0294 0.6404 0.8997
-0.500 0.2190 0.02111 0.01342 -0.0334 0.6323 0.9150
-0.250 0.2685 0.02141 0.01361 -0.0373 0.6249 0.9306
0.000 0.3185 0.02162 0.01374 -0.0416 0.6166 0.9459
0.250 0.3701 0.02164 0.01356 -0.0460 0.6105 0.9602
0.500 0.4213 0.02179 0.01375 -0.0513 0.6012 0.9746
0.750 0.4744 0.02163 0.01345 -0.0566 0.5947 0.9879
1.000 0.5252 0.02156 0.01336 -0.0620 0.5873 1.0000
1.250 0.5414 0.02172 0.01352 -0.0609 0.5808 1.0000
1.500 0.5594 0.02177 0.01347 -0.0597 0.5760 1.0000
1.750 0.5756 0.02212 0.01385 -0.0586 0.5704 1.0000
2.000 0.5916 0.02248 0.01425 -0.0574 0.5642 1.0000
2.250 0.6100 0.02263 0.01435 -0.0561 0.5593 1.0000
2.500 0.6287 0.02289 0.01453 -0.0549 0.5550 1.0000
2.750 0.6415 0.02358 0.01536 -0.0533 0.5479 1.0000
3.000 0.6591 0.02393 0.01570 -0.0520 0.5431 1.0000
3.250 0.6793 0.02414 0.01583 -0.0507 0.5393 1.0000
3.500 0.6908 0.02504 0.01685 -0.0489 0.5331 1.0000
3.750 0.7054 0.02566 0.01752 -0.0472 0.5273 1.0000
4.000 0.7254 0.02594 0.01776 -0.0459 0.5233 1.0000
4.250 0.7477 0.02623 0.01797 -0.0448 0.5202 1.0000
4.500 0.7482 0.02789 0.01987 -0.0420 0.5126 1.0000
4.750 0.7652 0.02842 0.02041 -0.0404 0.5078 1.0000
5.000 0.7890 0.02855 0.02048 -0.0394 0.5043 1.0000
5.250 0.7943 0.03005 0.02211 -0.0369 0.4989 1.0000
5.500 0.7970 0.03160 0.02378 -0.0342 0.4924 1.0000
5.750 0.8201 0.03181 0.02398 -0.0331 0.4885 1.0000
6.000 0.8494 0.03175 0.02386 -0.0326 0.4857 1.0000
6.250 0.8171 0.03576 0.02812 -0.0273 0.4766 1.0000
6.500 0.8340 0.03643 0.02883 -0.0257 0.4721 1.0000
6.750 0.8702 0.03589 0.02825 -0.0257 0.4694 1.0000
7.000 0.7776 0.04418 0.03673 -0.0171 0.4566 1.0000
7.250 0.8126 0.04364 0.03621 -0.0167 0.4537 1.0000
7.500 0.8660 0.04187 0.03447 -0.0175 0.4520 1.0000
7.750 0.9228 0.04008 0.03266 -0.0189 0.4504 1.0000
8.000 0.7446 0.05551 0.04809 -0.0087 0.4323 1.0000
8.250 0.8281 0.05045 0.04315 -0.0086 0.4327 1.0000
9.250 0.6512 0.07750 0.07011 -0.0066 0.3915 1.0000
9.500 0.6871 0.07661 0.06929 -0.0054 0.3856 1.0000
9.750 0.7521 0.07256 0.06535 -0.0032 0.3823 1.0000
10.250 1.1280 0.03895 0.03210 -0.0041 0.3808 1.0000
10.750 1.1793 0.03708 0.03034 -0.0014 0.3632 1.0000
11.000 1.2039 0.03601 0.02931 0.0000 0.3531 1.0000
11.250 1.2035 0.03642 0.02982 0.0037 0.3443 1.0000
11.500 1.2453 0.03418 0.02753 0.0039 0.3318 1.0000
11.750 1.2299 0.03522 0.02868 0.0088 0.3226 1.0000
12.000 1.2271 0.03576 0.02929 0.0119 0.3115 1.0000
12.250 1.2283 0.03612 0.02967 0.0144 0.2981 1.0000
12.500 1.2212 0.03738 0.03096 0.0167 0.2838 1.0000
12.750 1.2062 0.03972 0.03334 0.0184 0.2681 1.0000
13.000 1.1871 0.04294 0.03658 0.0193 0.2501 1.0000
13.250 1.1739 0.04581 0.03929 0.0200 0.2278 1.0000
13.500 1.1540 0.04985 0.04321 0.0202 0.2066 1.0000
13.750 1.1385 0.05355 0.04667 0.0204 0.1867 1.0000
14.000 1.1289 0.05667 0.04948 0.0209 0.1695 1.0000
14.250 1.1207 0.05993 0.05256 0.0211 0.1549 1.0000
14.500 1.1202 0.06234 0.05476 0.0217 0.1422 1.0000
14.750 1.1173 0.06539 0.05782 0.0217 0.1324 1.0000
15.000 1.1218 0.06749 0.05985 0.0223 0.1234 1.0000
15.250 1.1345 0.06856 0.06074 0.0234 0.1148 1.0000
15.500 1.1372 0.07116 0.06342 0.0234 0.1089 1.0000
15.750 1.1540 0.07201 0.06413 0.0246 0.1025 1.0000
16.000 1.1548 0.07496 0.06723 0.0244 0.0981 1.0000
16.250 1.1828 0.07479 0.06683 0.0262 0.0922 1.0000
16.500 1.1757 0.07873 0.07103 0.0253 0.0897 1.0000
16.750 1.1742 0.08209 0.07455 0.0247 0.0868 1.0000
17.000 1.2092 0.08152 0.07372 0.0268 0.0820 1.0000
17.250 1.1939 0.08646 0.07896 0.0252 0.0808 1.0000
17.500 1.1801 0.09150 0.08427 0.0236 0.0797 1.0000
17.750 1.1638 0.09705 0.09007 0.0215 0.0784 1.0000
18.000 1.1463 0.10301 0.09625 0.0190 0.0774 1.0000
18.250 1.1220 0.11023 0.10372 0.0156 0.0769 1.0000
18.500 1.0682 0.12301 0.11686 0.0086 0.0783 1.0000
18.750 0.9784 0.14486 0.13902 -0.0040 0.0812 1.0000
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Polar data table (+)
Polar graphs
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