BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il) Reynolds number: 200,000 Max Cl/Cd: 67.69 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707e-il-200000.txt Download as CSV file: xf-b707e-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .99 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4570 0.08637 0.08291 -0.0329 1.0000 0.0340
-8.250 -0.4664 0.08242 0.07901 -0.0370 1.0000 0.0343
-8.000 -0.4758 0.07934 0.07591 -0.0384 1.0000 0.0347
-7.750 -0.4816 0.07677 0.07324 -0.0394 1.0000 0.0351
-7.500 -0.4839 0.07427 0.07063 -0.0391 1.0000 0.0353
-7.250 -0.4840 0.07182 0.06804 -0.0380 1.0000 0.0354
-7.000 -0.4829 0.06926 0.06534 -0.0366 1.0000 0.0355
-6.750 -0.4890 0.06100 0.05725 -0.0360 1.0000 0.0368
-6.500 -0.4857 0.05800 0.05432 -0.0343 1.0000 0.0379
-6.250 -0.4847 0.05563 0.05195 -0.0321 1.0000 0.0392
-6.000 -0.4888 0.05375 0.05003 -0.0288 1.0000 0.0402
-5.750 -0.4938 0.05200 0.04822 -0.0253 0.9998 0.0412
-5.500 -0.4606 0.04819 0.04409 -0.0292 0.9947 0.0450
-5.250 -0.4174 0.04905 0.04409 -0.0315 0.9872 0.0485
-5.000 -0.3972 0.04043 0.03561 -0.0351 0.9834 0.0511
-4.750 -0.3699 0.03751 0.03258 -0.0369 0.9770 0.0544
-4.500 -0.3313 0.03720 0.03147 -0.0384 0.9711 0.0627
-4.250 -0.3066 0.03223 0.02670 -0.0407 0.9663 0.0669
-4.000 -0.2756 0.03051 0.02455 -0.0418 0.9598 0.0783
-3.750 -0.2409 0.02828 0.02226 -0.0442 0.9564 0.0863
-3.500 -0.2133 0.02627 0.02008 -0.0451 0.9494 0.0986
-2.250 -0.0256 0.01889 0.01113 -0.0502 0.9283 0.0624
-2.000 0.0046 0.01700 0.00923 -0.0506 0.9216 0.0596
-1.750 0.0391 0.01568 0.00785 -0.0514 0.9169 0.0538
-1.500 0.0734 0.01501 0.00707 -0.0523 0.9121 0.0500
-1.250 0.1022 0.01465 0.00670 -0.0523 0.9045 0.0487
-1.000 0.1336 0.01377 0.00584 -0.0529 0.8998 0.0480
-0.750 0.1570 0.01327 0.00535 -0.0520 0.8912 0.0479
-0.500 0.1866 0.01277 0.00482 -0.0523 0.8859 0.0483
-0.250 0.2101 0.01247 0.00445 -0.0514 0.8774 0.0499
0.000 0.2396 0.01218 0.00406 -0.0515 0.8717 0.0560
0.250 0.2592 0.01140 0.00388 -0.0501 0.8621 0.2835
0.500 0.3602 0.00958 0.00421 -0.0625 0.8587 0.9846
0.750 0.4180 0.00939 0.00380 -0.0679 0.8321 1.0000
1.000 0.4329 0.00933 0.00360 -0.0651 0.8089 1.0000
1.250 0.4504 0.00930 0.00343 -0.0628 0.7889 1.0000
1.500 0.4691 0.00929 0.00333 -0.0608 0.7722 1.0000
1.750 0.4885 0.00928 0.00329 -0.0591 0.7560 1.0000
2.000 0.5089 0.00927 0.00324 -0.0575 0.7404 1.0000
2.250 0.5298 0.00927 0.00321 -0.0560 0.7243 1.0000
2.500 0.5514 0.00928 0.00320 -0.0547 0.7082 1.0000
2.750 0.5734 0.00932 0.00324 -0.0534 0.6925 1.0000
3.000 0.5951 0.00936 0.00325 -0.0520 0.6722 1.0000
3.250 0.6159 0.00943 0.00324 -0.0503 0.6428 1.0000
3.500 0.6370 0.00955 0.00330 -0.0489 0.6133 1.0000
3.750 0.6578 0.00973 0.00338 -0.0473 0.5772 1.0000
4.000 0.6769 0.01000 0.00351 -0.0454 0.5185 1.0000
4.250 0.6903 0.01063 0.00368 -0.0426 0.4235 1.0000
4.500 0.7033 0.01145 0.00406 -0.0400 0.3358 1.0000
4.750 0.7192 0.01215 0.00447 -0.0379 0.2759 1.0000
5.000 0.7367 0.01278 0.00490 -0.0362 0.2291 1.0000
5.250 0.7531 0.01353 0.00533 -0.0344 0.1662 1.0000
5.500 0.7667 0.01458 0.00593 -0.0322 0.0863 1.0000
5.750 0.7859 0.01519 0.00648 -0.0308 0.0690 1.0000
6.000 0.8058 0.01574 0.00702 -0.0295 0.0592 1.0000
6.250 0.8251 0.01637 0.00764 -0.0281 0.0513 1.0000
6.500 0.8439 0.01706 0.00843 -0.0265 0.0464 1.0000
6.750 0.8577 0.01824 0.00973 -0.0242 0.0391 1.0000
7.000 0.8624 0.02059 0.01212 -0.0205 0.0323 1.0000
7.250 0.8811 0.02168 0.01331 -0.0188 0.0291 1.0000
7.500 0.8990 0.02290 0.01454 -0.0174 0.0251 1.0000
7.750 0.9193 0.02549 0.01706 -0.0166 0.0228 1.0000
8.000 0.9413 0.02678 0.01857 -0.0154 0.0218 1.0000
8.250 0.9634 0.02867 0.02069 -0.0143 0.0209 1.0000
8.500 0.9840 0.03094 0.02324 -0.0131 0.0207 1.0000
8.750 1.0016 0.03364 0.02632 -0.0114 0.0207 1.0000
9.000 1.0154 0.03666 0.02970 -0.0095 0.0210 1.0000
9.250 1.0252 0.04009 0.03349 -0.0072 0.0215 1.0000
9.500 1.0304 0.04437 0.03810 -0.0049 0.0223 1.0000
9.750 0.9734 0.03886 0.03376 0.0040 0.0278 1.0000
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Polar data table (+)
Polar graphs
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