BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il) Reynolds number: 200,000 Max Cl/Cd: 70.35 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707d-il-200000.txt Download as CSV file: xf-b707d-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .54 SPAN 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4581 0.08848 0.08502 -0.0381 1.0000 0.0311
-8.500 -0.4663 0.08534 0.08187 -0.0395 1.0000 0.0311
-8.250 -0.4691 0.08226 0.07874 -0.0405 1.0000 0.0312
-8.000 -0.4709 0.07929 0.07571 -0.0408 1.0000 0.0313
-7.750 -0.4711 0.07637 0.07272 -0.0405 1.0000 0.0314
-7.500 -0.4716 0.07354 0.06978 -0.0396 1.0000 0.0314
-7.250 -0.4795 0.06616 0.06248 -0.0391 1.0000 0.0322
-7.000 -0.4790 0.06245 0.05883 -0.0374 1.0000 0.0329
-6.750 -0.4804 0.05979 0.05619 -0.0351 1.0000 0.0336
-6.500 -0.4842 0.05762 0.05400 -0.0321 1.0000 0.0341
-6.250 -0.4886 0.05561 0.05195 -0.0290 1.0000 0.0348
-6.000 -0.4915 0.05355 0.04984 -0.0261 1.0000 0.0357
-5.750 -0.4663 0.05003 0.04612 -0.0288 0.9959 0.0386
-5.500 -0.4225 0.04981 0.04515 -0.0317 0.9894 0.0437
-5.250 -0.3992 0.04271 0.03784 -0.0349 0.9845 0.0453
-5.000 -0.3731 0.03885 0.03398 -0.0372 0.9796 0.0474
-4.750 -0.3429 0.03615 0.03110 -0.0393 0.9739 0.0511
-4.500 -0.3044 0.03436 0.02863 -0.0413 0.9697 0.0589
-4.250 -0.2797 0.03097 0.02530 -0.0426 0.9631 0.0629
-4.000 -0.2456 0.02910 0.02303 -0.0443 0.9584 0.0742
-3.750 -0.2100 0.02692 0.02065 -0.0469 0.9556 0.0887
-3.500 -0.1839 0.02504 0.01873 -0.0477 0.9483 0.1056
-3.250 -0.1509 0.02341 0.01698 -0.0499 0.9443 0.1390
-3.000 -0.1177 0.02123 0.01473 -0.0521 0.9414 0.1752
-2.500 -0.0315 0.01873 0.01108 -0.0508 0.9313 0.0564
-2.250 0.0058 0.01670 0.00894 -0.0521 0.9281 0.0491
-2.000 0.0352 0.01575 0.00787 -0.0518 0.9213 0.0467
-1.750 0.0659 0.01484 0.00699 -0.0523 0.9157 0.0484
-1.500 0.0942 0.01419 0.00636 -0.0523 0.9096 0.0518
-1.250 0.1200 0.01360 0.00576 -0.0518 0.9022 0.0528
-1.000 0.1471 0.01312 0.00522 -0.0515 0.8963 0.0554
-0.750 0.1717 0.01276 0.00477 -0.0507 0.8884 0.0606
-0.500 0.1989 0.01238 0.00443 -0.0504 0.8827 0.0887
-0.250 0.2120 0.00993 0.00478 -0.0462 0.8760 0.9087
0.000 0.3169 0.01007 0.00481 -0.0607 0.8794 0.9836
0.250 0.3867 0.00987 0.00451 -0.0694 0.8737 1.0000
0.500 0.4023 0.00974 0.00431 -0.0670 0.8594 1.0000
0.750 0.4189 0.00961 0.00407 -0.0645 0.8439 1.0000
1.000 0.4368 0.00950 0.00387 -0.0623 0.8285 1.0000
1.250 0.4560 0.00946 0.00376 -0.0604 0.8148 1.0000
1.500 0.4761 0.00945 0.00369 -0.0587 0.8015 1.0000
1.750 0.4970 0.00945 0.00367 -0.0572 0.7887 1.0000
2.000 0.5177 0.00938 0.00351 -0.0554 0.7711 1.0000
2.250 0.5377 0.00934 0.00342 -0.0535 0.7502 1.0000
2.500 0.5591 0.00933 0.00336 -0.0519 0.7315 1.0000
2.750 0.5815 0.00936 0.00338 -0.0507 0.7153 1.0000
3.000 0.6038 0.00941 0.00342 -0.0494 0.6978 1.0000
3.250 0.6261 0.00947 0.00348 -0.0482 0.6782 1.0000
3.500 0.6485 0.00955 0.00353 -0.0469 0.6567 1.0000
3.750 0.6701 0.00966 0.00360 -0.0455 0.6280 1.0000
4.000 0.6908 0.00982 0.00370 -0.0439 0.5876 1.0000
4.250 0.7090 0.01013 0.00378 -0.0419 0.5182 1.0000
4.500 0.7209 0.01093 0.00400 -0.0389 0.4062 1.0000
4.750 0.7356 0.01172 0.00443 -0.0367 0.3319 1.0000
5.000 0.7533 0.01238 0.00487 -0.0350 0.2819 1.0000
5.250 0.7720 0.01298 0.00536 -0.0336 0.2403 1.0000
5.500 0.7901 0.01368 0.00588 -0.0321 0.1887 1.0000
5.750 0.7992 0.01533 0.00675 -0.0293 0.0707 1.0000
6.000 0.8143 0.01652 0.00794 -0.0271 0.0554 1.0000
6.250 0.8308 0.01752 0.00902 -0.0253 0.0469 1.0000
6.500 0.8457 0.01868 0.01018 -0.0233 0.0389 1.0000
6.750 0.8658 0.01936 0.01099 -0.0219 0.0335 1.0000
7.000 0.8799 0.02079 0.01239 -0.0198 0.0301 1.0000
7.250 0.8971 0.02246 0.01412 -0.0180 0.0286 1.0000
7.500 0.9187 0.02420 0.01594 -0.0168 0.0273 1.0000
7.750 0.9407 0.02570 0.01755 -0.0159 0.0255 1.0000
8.000 0.9608 0.02726 0.01917 -0.0150 0.0233 1.0000
8.250 0.9841 0.02972 0.02190 -0.0142 0.0233 1.0000
8.500 1.0061 0.03276 0.02532 -0.0129 0.0240 1.0000
8.750 1.0203 0.03737 0.03058 -0.0103 0.0266 1.0000
9.000 1.0299 0.04236 0.03590 -0.0084 0.0288 1.0000
14.000 0.6520 0.14881 0.14556 -0.0288 0.0528 1.0000
14.250 0.6633 0.15138 0.14815 -0.0280 0.0515 1.0000
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Polar data table (+)
Polar graphs
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