BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il) Reynolds number: 50,000 Max Cl/Cd: 35.82 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707d-il-50000-n5.txt Download as CSV file: xf-b707d-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4801 0.09798 0.09129 -0.0266 1.0000 0.1318
-8.500 -0.4728 0.09392 0.08728 -0.0259 1.0000 0.1379
-8.250 -0.4808 0.09099 0.08442 -0.0276 1.0000 0.1451
-8.000 -0.5097 0.08887 0.08242 -0.0329 1.0000 0.1477
-7.750 -0.4893 0.08441 0.07800 -0.0294 1.0000 0.1598
-7.500 -0.4860 0.08090 0.07455 -0.0285 1.0000 0.1696
-7.000 -0.4915 0.07482 0.06860 -0.0276 1.0000 0.1971
-6.000 -0.4942 0.06451 0.05860 -0.0178 1.0000 0.2885
-5.500 -0.4550 0.05358 0.04555 -0.0291 1.0000 0.0760
-5.250 -0.4442 0.04968 0.04180 -0.0276 1.0000 0.0699
-5.000 -0.4299 0.04794 0.03928 -0.0252 1.0000 0.0607
-4.750 -0.4189 0.04477 0.03608 -0.0237 1.0000 0.0588
-4.500 -0.4063 0.04244 0.03350 -0.0220 1.0000 0.0579
-4.250 -0.3919 0.04044 0.03117 -0.0203 1.0000 0.0583
-4.000 -0.3762 0.03858 0.02894 -0.0187 1.0000 0.0587
-3.750 -0.3592 0.03673 0.02673 -0.0173 1.0000 0.0586
-3.500 -0.3392 0.03485 0.02454 -0.0163 0.9992 0.0575
-3.250 -0.3053 0.03279 0.02208 -0.0176 0.9936 0.0562
-3.000 -0.2711 0.03104 0.01997 -0.0188 0.9878 0.0553
-2.750 -0.2372 0.02951 0.01812 -0.0199 0.9821 0.0549
-2.500 -0.2020 0.02816 0.01646 -0.0211 0.9771 0.0548
-2.250 -0.1690 0.02703 0.01516 -0.0217 0.9713 0.0553
-2.000 -0.1340 0.02615 0.01408 -0.0228 0.9663 0.0580
-1.750 -0.1016 0.02546 0.01321 -0.0237 0.9601 0.0619
-1.500 -0.0703 0.02461 0.01225 -0.0246 0.9544 0.0657
-1.250 -0.0397 0.02403 0.01151 -0.0255 0.9477 0.0693
-1.000 -0.0098 0.02361 0.01089 -0.0262 0.9410 0.0739
-0.750 0.0231 0.02314 0.01033 -0.0276 0.9348 0.0883
-0.250 0.1270 0.01995 0.00994 -0.0360 0.9321 1.0000
0.000 0.1553 0.02017 0.00987 -0.0367 0.9236 1.0000
0.250 0.1848 0.02041 0.00988 -0.0376 0.9159 1.0000
0.500 0.2172 0.02065 0.00995 -0.0391 0.9087 1.0000
0.750 0.2443 0.02092 0.01009 -0.0395 0.9002 1.0000
1.000 0.2791 0.02115 0.01024 -0.0413 0.8936 1.0000
1.250 0.3045 0.02145 0.01047 -0.0413 0.8844 1.0000
1.500 0.3410 0.02165 0.01065 -0.0432 0.8780 1.0000
1.750 0.3646 0.02196 0.01094 -0.0428 0.8675 1.0000
2.000 0.3929 0.02220 0.01122 -0.0431 0.8576 1.0000
2.250 0.4264 0.02229 0.01135 -0.0441 0.8463 1.0000
2.500 0.4592 0.02224 0.01136 -0.0444 0.8313 1.0000
2.750 0.4909 0.02211 0.01131 -0.0444 0.8147 1.0000
3.000 0.5213 0.02200 0.01133 -0.0441 0.7986 1.0000
3.250 0.5498 0.02194 0.01138 -0.0436 0.7832 1.0000
3.500 0.5773 0.02189 0.01147 -0.0428 0.7676 1.0000
3.750 0.6047 0.02182 0.01154 -0.0420 0.7514 1.0000
4.000 0.6307 0.02174 0.01167 -0.0408 0.7336 1.0000
4.250 0.6528 0.02175 0.01186 -0.0391 0.7128 1.0000
4.500 0.6785 0.02155 0.01184 -0.0376 0.6900 1.0000
4.750 0.6998 0.02139 0.01184 -0.0353 0.6589 1.0000
5.000 0.7196 0.02114 0.01173 -0.0325 0.6135 1.0000
5.250 0.7378 0.02101 0.01158 -0.0295 0.5509 1.0000
5.500 0.7573 0.02114 0.01150 -0.0269 0.4749 1.0000
5.750 0.7737 0.02177 0.01171 -0.0243 0.3996 1.0000
6.000 0.7855 0.02286 0.01236 -0.0217 0.3295 1.0000
6.250 0.7986 0.02396 0.01328 -0.0197 0.2763 1.0000
6.500 0.8084 0.02535 0.01438 -0.0174 0.2028 1.0000
6.750 0.8186 0.02694 0.01560 -0.0153 0.1233 1.0000
7.000 0.8294 0.02880 0.01711 -0.0132 0.0830 1.0000
7.250 0.8416 0.03060 0.01881 -0.0112 0.0711 1.0000
7.500 0.8541 0.03247 0.02073 -0.0092 0.0644 1.0000
7.750 0.8698 0.03441 0.02285 -0.0075 0.0570 1.0000
8.000 0.8861 0.03663 0.02511 -0.0063 0.0488 1.0000
8.250 0.9076 0.03865 0.02742 -0.0052 0.0433 1.0000
8.500 0.9292 0.04125 0.03014 -0.0046 0.0396 1.0000
8.750 0.9484 0.04346 0.03283 -0.0034 0.0361 1.0000
9.000 0.9645 0.04595 0.03559 -0.0022 0.0335 1.0000
9.250 0.9795 0.04888 0.03878 -0.0011 0.0324 1.0000
9.500 0.9911 0.05214 0.04230 0.0001 0.0316 1.0000
9.750 0.9965 0.05558 0.04610 0.0019 0.0313 1.0000
10.000 0.9962 0.05895 0.04988 0.0039 0.0311 1.0000
10.250 0.9905 0.06226 0.05353 0.0062 0.0310 1.0000
10.500 0.9805 0.06562 0.05718 0.0084 0.0310 1.0000
10.750 0.9680 0.06920 0.06101 0.0099 0.0310 1.0000
11.000 0.9540 0.07306 0.06509 0.0106 0.0311 1.0000
11.250 0.9380 0.07738 0.06961 0.0104 0.0311 1.0000
11.500 0.9215 0.08218 0.07458 0.0092 0.0312 1.0000
11.750 0.9050 0.08745 0.07999 0.0070 0.0314 1.0000
12.000 0.8871 0.09341 0.08614 0.0037 0.0317 1.0000
12.250 0.8504 0.10431 0.09723 -0.0047 0.0326 1.0000
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Polar data table (+)
Polar graphs
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