BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il) Reynolds number: 500,000 Max Cl/Cd: 62.27 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707d-il-500000-n5.txt Download as CSV file: xf-b707d-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4613 0.08562 0.08338 -0.0282 1.0000 0.0112
-8.750 -0.4672 0.08046 0.07825 -0.0314 1.0000 0.0106
-8.500 -0.4655 0.07801 0.07583 -0.0327 1.0000 0.0117
-8.250 -0.4811 0.07309 0.07094 -0.0364 1.0000 0.0111
-8.000 -0.4842 0.06980 0.06764 -0.0375 1.0000 0.0116
-7.750 -0.4896 0.06561 0.06341 -0.0384 1.0000 0.0113
-7.500 -0.4819 0.06190 0.05963 -0.0404 0.9935 0.0123
-7.250 -0.4608 0.05664 0.05419 -0.0451 0.9829 0.0135
-6.750 -0.4062 0.04854 0.04561 -0.0511 0.9620 0.0145
-6.500 -0.3836 0.04416 0.04099 -0.0532 0.9501 0.0145
-6.250 -0.3719 0.03862 0.03524 -0.0549 0.9352 0.0133
-6.000 -0.3520 0.03503 0.03137 -0.0548 0.9209 0.0132
-5.750 -0.3330 0.03201 0.02806 -0.0540 0.9071 0.0132
-5.500 -0.3133 0.02929 0.02504 -0.0528 0.8942 0.0133
-5.250 -0.2931 0.02684 0.02231 -0.0516 0.8825 0.0134
-5.000 -0.2692 0.02526 0.02047 -0.0505 0.8723 0.0141
-4.750 -0.2485 0.02298 0.01791 -0.0494 0.8628 0.0140
-4.500 -0.2270 0.02081 0.01544 -0.0483 0.8533 0.0137
-4.250 -0.2039 0.01889 0.01324 -0.0473 0.8446 0.0135
-4.000 -0.1798 0.01723 0.01132 -0.0465 0.8364 0.0133
-3.750 -0.1547 0.01571 0.00957 -0.0458 0.8285 0.0134
-3.500 -0.1292 0.01447 0.00812 -0.0451 0.8215 0.0135
-3.250 -0.1033 0.01350 0.00698 -0.0446 0.8139 0.0139
-3.000 -0.0775 0.01280 0.00615 -0.0441 0.8069 0.0142
-2.750 -0.0515 0.01226 0.00553 -0.0437 0.7996 0.0145
-2.500 -0.0271 0.01133 0.00451 -0.0430 0.7931 0.0150
-2.250 -0.0028 0.01066 0.00380 -0.0424 0.7863 0.0156
-2.000 0.0228 0.01038 0.00349 -0.0421 0.7796 0.0166
-1.750 0.0484 0.01006 0.00315 -0.0417 0.7732 0.0174
-1.500 0.0737 0.00969 0.00274 -0.0412 0.7667 0.0176
-1.250 0.0993 0.00938 0.00237 -0.0408 0.7607 0.0181
-1.000 0.1253 0.00913 0.00208 -0.0404 0.7541 0.0189
-0.750 0.1515 0.00894 0.00184 -0.0401 0.7473 0.0204
-0.500 0.1768 0.00884 0.00163 -0.0395 0.7260 0.0218
-0.250 0.2000 0.00879 0.00134 -0.0384 0.6814 0.0263
0.000 0.2242 0.00882 0.00120 -0.0376 0.6412 0.0322
0.250 0.2467 0.00855 0.00110 -0.0368 0.6010 0.1731
0.500 0.2569 0.00714 0.00105 -0.0340 0.5512 0.6792
0.750 0.2753 0.00734 0.00112 -0.0321 0.4602 0.7453
1.000 0.2908 0.00803 0.00137 -0.0300 0.3091 0.7982
1.250 0.3080 0.00861 0.00163 -0.0280 0.1839 0.8648
1.500 0.3397 0.00932 0.00198 -0.0291 0.0505 0.9416
1.750 0.3812 0.00951 0.00210 -0.0323 0.0383 0.9645
2.000 0.4148 0.00973 0.00219 -0.0337 0.0223 0.9725
2.250 0.4484 0.00987 0.00229 -0.0352 0.0205 0.9791
2.500 0.4809 0.01003 0.00242 -0.0364 0.0198 0.9856
2.750 0.5144 0.01018 0.00257 -0.0379 0.0197 0.9908
3.000 0.5469 0.01036 0.00272 -0.0392 0.0196 0.9962
3.250 0.5797 0.01054 0.00290 -0.0406 0.0194 1.0000
3.500 0.6024 0.01071 0.00307 -0.0397 0.0194 1.0000
3.750 0.6253 0.01088 0.00327 -0.0388 0.0195 1.0000
4.000 0.6482 0.01107 0.00348 -0.0379 0.0195 1.0000
4.250 0.6711 0.01127 0.00370 -0.0371 0.0194 1.0000
4.500 0.6939 0.01151 0.00397 -0.0362 0.0186 1.0000
4.750 0.7165 0.01176 0.00428 -0.0353 0.0177 1.0000
5.000 0.7391 0.01203 0.00458 -0.0345 0.0171 1.0000
5.250 0.7616 0.01232 0.00489 -0.0336 0.0164 1.0000
5.500 0.7841 0.01262 0.00524 -0.0327 0.0157 1.0000
5.750 0.8064 0.01295 0.00563 -0.0318 0.0147 1.0000
6.000 0.8276 0.01340 0.00612 -0.0308 0.0130 1.0000
6.500 0.8727 0.01406 0.00690 -0.0292 0.0099 1.0000
6.750 0.8946 0.01447 0.00740 -0.0282 0.0076 1.0000
7.000 0.9173 0.01477 0.00768 -0.0276 0.0070 1.0000
7.250 0.9391 0.01518 0.00810 -0.0267 0.0065 1.0000
7.500 0.9599 0.01570 0.00867 -0.0257 0.0060 1.0000
7.750 0.9786 0.01643 0.00948 -0.0243 0.0056 1.0000
8.000 0.9962 0.01725 0.01041 -0.0228 0.0054 1.0000
8.250 1.0136 0.01807 0.01135 -0.0213 0.0052 1.0000
8.500 1.0295 0.01903 0.01242 -0.0195 0.0050 1.0000
8.750 1.0463 0.01989 0.01339 -0.0180 0.0046 1.0000
9.000 1.0613 0.02092 0.01457 -0.0162 0.0044 1.0000
9.250 1.0759 0.02199 0.01578 -0.0145 0.0043 1.0000
9.500 1.0896 0.02316 0.01708 -0.0126 0.0042 1.0000
9.750 1.1025 0.02437 0.01843 -0.0107 0.0040 1.0000
10.000 1.1128 0.02568 0.01990 -0.0084 0.0039 1.0000
10.250 1.1214 0.02701 0.02138 -0.0059 0.0039 1.0000
10.500 1.1292 0.02825 0.02276 -0.0035 0.0037 1.0000
10.750 1.1338 0.02987 0.02456 -0.0009 0.0036 1.0000
11.000 1.1357 0.03182 0.02670 0.0017 0.0035 1.0000
11.250 1.1304 0.03457 0.02972 0.0046 0.0034 1.0000
11.750 1.1091 0.04120 0.03692 0.0096 0.0033 1.0000
12.000 1.1005 0.04431 0.04024 0.0110 0.0033 1.0000
12.250 1.0877 0.04816 0.04433 0.0118 0.0033 1.0000
12.500 1.0765 0.05197 0.04833 0.0119 0.0033 1.0000
12.750 1.0613 0.05667 0.05324 0.0111 0.0033 1.0000
13.000 1.0429 0.06238 0.05918 0.0093 0.0032 1.0000
13.250 1.0241 0.06861 0.06555 0.0063 0.0033 1.0000
13.500 1.0049 0.07590 0.07304 0.0022 0.0033 1.0000
13.750 0.9841 0.08460 0.08189 -0.0034 0.0033 1.0000
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Polar data table (+)
Polar graphs
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