BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il) Reynolds number: 50,000 Max Cl/Cd: 35.7 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707e-il-50000-n5.txt Download as CSV file: xf-b707e-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4697 0.09920 0.09236 -0.0253 1.0000 0.1234
-8.500 -0.4749 0.09629 0.08953 -0.0270 1.0000 0.1300
-8.250 -0.4977 0.09366 0.08707 -0.0311 1.0000 0.1321
-8.000 -0.4832 0.08975 0.08318 -0.0284 1.0000 0.1436
-7.750 -0.4852 0.08632 0.07984 -0.0282 1.0000 0.1522
-7.250 -0.5042 0.08049 0.07413 -0.0302 1.0000 0.1739
-5.750 -0.4981 0.06425 0.05835 -0.0147 1.0000 0.3136
-5.250 -0.4541 0.05157 0.04389 -0.0288 1.0000 0.0846
-5.000 -0.4417 0.04868 0.04062 -0.0269 1.0000 0.0717
-4.750 -0.4311 0.04598 0.03760 -0.0249 1.0000 0.0664
-4.500 -0.4166 0.04417 0.03525 -0.0226 1.0000 0.0607
-4.250 -0.4043 0.04173 0.03262 -0.0209 1.0000 0.0591
-4.000 -0.3903 0.03971 0.03030 -0.0191 1.0000 0.0587
-3.750 -0.3749 0.03796 0.02821 -0.0175 1.0000 0.0591
-3.500 -0.3581 0.03637 0.02624 -0.0159 1.0000 0.0599
-3.250 -0.3283 0.03434 0.02380 -0.0166 0.9954 0.0593
-3.000 -0.2954 0.03244 0.02156 -0.0178 0.9894 0.0581
-2.750 -0.2611 0.03077 0.01954 -0.0191 0.9838 0.0571
-2.500 -0.2284 0.02933 0.01782 -0.0199 0.9779 0.0566
-2.250 -0.1942 0.02808 0.01630 -0.0210 0.9723 0.0562
-2.000 -0.1600 0.02702 0.01508 -0.0219 0.9671 0.0563
-1.750 -0.1280 0.02614 0.01405 -0.0225 0.9611 0.0567
-1.500 -0.0926 0.02538 0.01312 -0.0239 0.9562 0.0576
-1.250 -0.0643 0.02482 0.01235 -0.0242 0.9490 0.0596
-1.000 -0.0327 0.02423 0.01164 -0.0253 0.9431 0.0647
-0.750 -0.0049 0.02378 0.01109 -0.0258 0.9360 0.0706
-0.500 0.0275 0.02345 0.01055 -0.0270 0.9297 0.0759
-0.250 0.0567 0.02308 0.01011 -0.0277 0.9229 0.0858
0.000 0.0816 0.02107 0.00988 -0.0282 0.9174 0.4946
0.250 0.1602 0.02019 0.00999 -0.0364 0.9189 1.0000
0.500 0.1947 0.02040 0.00994 -0.0382 0.9128 1.0000
0.750 0.2205 0.02064 0.01002 -0.0384 0.9040 1.0000
1.000 0.2527 0.02087 0.01011 -0.0397 0.8972 1.0000
1.250 0.2822 0.02111 0.01026 -0.0405 0.8892 1.0000
1.500 0.3124 0.02136 0.01045 -0.0414 0.8813 1.0000
1.750 0.3464 0.02155 0.01061 -0.0428 0.8737 1.0000
2.000 0.3735 0.02180 0.01085 -0.0430 0.8638 1.0000
2.250 0.4076 0.02195 0.01103 -0.0442 0.8552 1.0000
2.500 0.4440 0.02198 0.01113 -0.0456 0.8444 1.0000
2.750 0.4802 0.02186 0.01109 -0.0464 0.8299 1.0000
3.000 0.5109 0.02178 0.01108 -0.0462 0.8128 1.0000
3.250 0.5396 0.02176 0.01120 -0.0457 0.7962 1.0000
3.500 0.5670 0.02178 0.01134 -0.0450 0.7805 1.0000
3.750 0.5977 0.02144 0.01110 -0.0440 0.7581 1.0000
4.000 0.6220 0.02112 0.01086 -0.0419 0.7307 1.0000
4.250 0.6431 0.02093 0.01078 -0.0395 0.7034 1.0000
4.500 0.6631 0.02092 0.01097 -0.0374 0.6780 1.0000
4.750 0.6846 0.02086 0.01104 -0.0354 0.6496 1.0000
5.000 0.7053 0.02083 0.01113 -0.0333 0.6146 1.0000
5.250 0.7245 0.02086 0.01124 -0.0309 0.5686 1.0000
5.500 0.7435 0.02095 0.01125 -0.0283 0.4992 1.0000
5.750 0.7623 0.02135 0.01133 -0.0259 0.4240 1.0000
6.000 0.7773 0.02219 0.01186 -0.0235 0.3616 1.0000
6.250 0.7883 0.02335 0.01264 -0.0209 0.2968 1.0000
6.500 0.7995 0.02459 0.01360 -0.0187 0.2413 1.0000
6.750 0.8133 0.02569 0.01467 -0.0167 0.1928 1.0000
7.000 0.8249 0.02709 0.01588 -0.0146 0.1422 1.0000
7.250 0.8369 0.02864 0.01734 -0.0125 0.1115 1.0000
7.500 0.8496 0.03025 0.01886 -0.0105 0.0942 1.0000
7.750 0.8621 0.03191 0.02040 -0.0088 0.0752 1.0000
8.000 0.8762 0.03361 0.02219 -0.0072 0.0615 1.0000
8.250 0.8898 0.03547 0.02409 -0.0056 0.0507 1.0000
8.500 0.9070 0.03755 0.02634 -0.0041 0.0456 1.0000
8.750 0.9283 0.04032 0.02916 -0.0032 0.0417 1.0000
9.000 0.9497 0.04289 0.03214 -0.0022 0.0379 1.0000
9.250 0.9650 0.04554 0.03511 -0.0011 0.0347 1.0000
9.500 0.9796 0.04890 0.03864 -0.0002 0.0327 1.0000
9.750 0.9898 0.05262 0.04268 0.0012 0.0319 1.0000
10.000 0.9923 0.05579 0.04632 0.0034 0.0314 1.0000
10.250 0.9900 0.05901 0.04995 0.0057 0.0312 1.0000
10.500 0.9825 0.06221 0.05348 0.0082 0.0310 1.0000
10.750 0.9713 0.06558 0.05714 0.0104 0.0309 1.0000
11.000 0.9575 0.06925 0.06108 0.0117 0.0309 1.0000
11.250 0.9426 0.07323 0.06528 0.0121 0.0309 1.0000
11.500 0.9252 0.07778 0.07004 0.0115 0.0310 1.0000
11.750 0.9088 0.08271 0.07513 0.0100 0.0312 1.0000
12.000 0.8905 0.08840 0.08096 0.0074 0.0313 1.0000
12.250 0.8742 0.09451 0.08717 0.0042 0.0315 1.0000
12.500 0.8577 0.10145 0.09418 0.0000 0.0317 1.0000
12.750 0.8445 0.10853 0.10131 -0.0042 0.0320 1.0000
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Polar data table (+)
Polar graphs
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