BOEING 707 .19 SPAN AIRFOIL (b707b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BOEING 707 .19 SPAN AIRFOIL (b707b-il) Reynolds number: 1,000,000 Max Cl/Cd: 62.67 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707b-il-1000000-n5.txt Download as CSV file: xf-b707b-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .19 SPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9862 0.07150 0.06815 -0.0248 0.6444 0.0035
-14.750 -1.0398 0.05746 0.05375 -0.0315 0.6419 0.0035
-14.500 -1.0586 0.05253 0.04864 -0.0327 0.6406 0.0035
-14.250 -1.0646 0.04953 0.04554 -0.0330 0.6388 0.0035
-14.000 -1.0767 0.04602 0.04187 -0.0327 0.6372 0.0035
-13.750 -1.0895 0.04263 0.03830 -0.0318 0.6350 0.0035
-13.500 -1.0918 0.04058 0.03613 -0.0306 0.6331 0.0036
-13.250 -1.0970 0.03826 0.03365 -0.0289 0.6308 0.0036
-13.000 -1.1016 0.03606 0.03128 -0.0268 0.6282 0.0036
-12.500 -1.0996 0.03286 0.02781 -0.0223 0.6248 0.0038
-12.250 -1.0956 0.03153 0.02636 -0.0199 0.6234 0.0038
-12.000 -1.0909 0.03018 0.02489 -0.0174 0.6219 0.0038
-11.750 -1.0854 0.02879 0.02334 -0.0148 0.6204 0.0039
-11.500 -1.0761 0.02794 0.02240 -0.0124 0.6190 0.0040
-11.250 -1.0669 0.02696 0.02131 -0.0099 0.6171 0.0041
-11.000 -1.0569 0.02593 0.02016 -0.0075 0.6157 0.0044
-10.750 -1.0449 0.02511 0.01924 -0.0052 0.6145 0.0044
-10.500 -1.0311 0.02403 0.01803 -0.0033 0.6134 0.0047
-10.250 -1.0145 0.02320 0.01710 -0.0017 0.6122 0.0047
-10.000 -0.9974 0.02224 0.01602 -0.0002 0.6111 0.0050
-9.750 -0.9793 0.02137 0.01504 0.0011 0.6099 0.0052
-9.250 -0.9376 0.02136 0.01500 0.0031 0.6081 0.0064
-9.000 -0.9224 0.01872 0.01207 0.0052 0.6074 0.0103
-8.750 -0.8984 0.01866 0.01194 0.0058 0.6063 0.0111
-8.500 -0.8733 0.01888 0.01212 0.0063 0.6051 0.0115
-8.250 -0.8498 0.01888 0.01208 0.0071 0.6042 0.0117
-8.000 -0.8285 0.01823 0.01138 0.0080 0.6032 0.0119
-7.750 -0.8075 0.01755 0.01070 0.0089 0.6023 0.0123
-7.500 -0.7845 0.01728 0.01043 0.0096 0.6013 0.0128
-7.250 -0.7614 0.01688 0.01001 0.0103 0.6000 0.0131
-7.000 -0.7378 0.01657 0.00967 0.0110 0.5984 0.0135
-6.750 -0.7141 0.01621 0.00928 0.0117 0.5967 0.0139
-6.500 -0.6903 0.01585 0.00888 0.0123 0.5948 0.0141
-6.250 -0.6664 0.01549 0.00847 0.0130 0.5931 0.0143
-6.000 -0.6425 0.01511 0.00806 0.0137 0.5915 0.0144
-5.750 -0.6170 0.01494 0.00786 0.0141 0.5904 0.0148
-5.500 -0.5912 0.01481 0.00771 0.0145 0.5891 0.0150
-5.250 -0.5687 0.01413 0.00699 0.0154 0.5874 0.0154
-5.000 -0.5462 0.01354 0.00640 0.0163 0.5836 0.0156
-4.750 -0.5227 0.01311 0.00594 0.0171 0.5786 0.0157
-4.500 -0.4986 0.01275 0.00556 0.0178 0.5745 0.0157
-4.250 -0.4745 0.01237 0.00516 0.0185 0.5676 0.0157
-4.000 -0.4504 0.01202 0.00478 0.0192 0.5560 0.0158
-3.750 -0.4260 0.01173 0.00443 0.0199 0.5350 0.0158
-3.500 -0.4043 0.01200 0.00425 0.0208 0.3775 0.0158
-3.250 -0.3806 0.01202 0.00404 0.0215 0.2929 0.0157
-3.000 -0.3557 0.01188 0.00382 0.0220 0.2715 0.0157
-2.750 -0.3302 0.01172 0.00361 0.0225 0.2642 0.0156
-2.500 -0.3046 0.01155 0.00341 0.0229 0.2583 0.0155
-2.250 -0.2786 0.01139 0.00324 0.0233 0.2539 0.0155
-2.000 -0.2527 0.01125 0.00308 0.0237 0.2486 0.0154
-1.750 -0.2265 0.01112 0.00293 0.0241 0.2441 0.0154
-1.500 -0.2002 0.01097 0.00278 0.0244 0.2401 0.0153
-1.250 -0.1740 0.01086 0.00264 0.0248 0.2317 0.0153
-1.000 -0.1476 0.01077 0.00251 0.0251 0.2199 0.0153
-0.750 -0.1228 0.01091 0.00243 0.0255 0.1518 0.0152
-0.500 -0.0968 0.01091 0.00236 0.0259 0.1313 0.0152
-0.250 -0.0716 0.01104 0.00234 0.0263 0.0831 0.0152
0.000 -0.0450 0.01101 0.00230 0.0266 0.0801 0.0152
0.250 -0.0184 0.01099 0.00226 0.0268 0.0776 0.0152
0.500 0.0083 0.01098 0.00224 0.0271 0.0752 0.0153
0.750 0.0351 0.01099 0.00224 0.0273 0.0728 0.0154
1.000 0.0620 0.01098 0.00222 0.0275 0.0717 0.0155
1.250 0.0889 0.01099 0.00222 0.0277 0.0704 0.0158
1.500 0.1159 0.01100 0.00224 0.0279 0.0693 0.0162
1.750 0.1428 0.01103 0.00228 0.0281 0.0682 0.0169
2.000 0.1696 0.01107 0.00232 0.0282 0.0667 0.0184
2.250 0.1939 0.01087 0.00236 0.0289 0.0646 0.1466
2.500 0.2124 0.01015 0.00229 0.0303 0.0626 0.3844
2.750 0.2342 0.00977 0.00229 0.0313 0.0614 0.4864
3.000 0.2529 0.00927 0.00235 0.0330 0.0609 0.6469
3.250 0.2765 0.00915 0.00243 0.0339 0.0598 0.6987
3.500 0.3021 0.00917 0.00252 0.0343 0.0583 0.7210
3.750 0.3277 0.00921 0.00261 0.0347 0.0561 0.7426
4.000 0.3524 0.00925 0.00271 0.0354 0.0530 0.7692
4.250 0.3777 0.00931 0.00282 0.0359 0.0506 0.7897
4.500 0.4033 0.00941 0.00294 0.0363 0.0478 0.8050
4.750 0.4266 0.00970 0.00315 0.0370 0.0268 0.8206
5.000 0.4508 0.00992 0.00339 0.0376 0.0182 0.8370
5.250 0.4758 0.01005 0.00359 0.0382 0.0171 0.8540
5.500 0.5008 0.01018 0.00378 0.0387 0.0167 0.8712
5.750 0.5261 0.01034 0.00400 0.0391 0.0163 0.8873
6.000 0.5517 0.01051 0.00423 0.0395 0.0160 0.9029
6.250 0.5783 0.01071 0.00448 0.0396 0.0157 0.9178
6.500 0.6063 0.01094 0.00476 0.0394 0.0154 0.9311
6.750 0.6357 0.01120 0.00506 0.0389 0.0152 0.9420
7.000 0.6660 0.01149 0.00539 0.0381 0.0149 0.9511
7.250 0.6986 0.01182 0.00576 0.0368 0.0146 0.9582
7.500 0.7302 0.01218 0.00615 0.0356 0.0143 0.9638
7.750 0.7623 0.01253 0.00653 0.0344 0.0142 0.9684
8.000 0.7921 0.01288 0.00692 0.0336 0.0142 0.9730
8.250 0.8242 0.01328 0.00735 0.0322 0.0141 0.9755
8.500 0.8538 0.01368 0.00778 0.0314 0.0139 0.9794
8.750 0.8816 0.01410 0.00823 0.0310 0.0137 0.9838
9.000 0.9118 0.01455 0.00872 0.0299 0.0135 0.9862
9.250 0.9410 0.01503 0.00924 0.0291 0.0132 0.9892
9.500 0.9686 0.01553 0.00978 0.0285 0.0130 0.9925
9.750 0.9967 0.01607 0.01036 0.0278 0.0126 0.9950
10.000 1.0258 0.01665 0.01099 0.0268 0.0124 0.9974
10.250 1.0536 0.01729 0.01168 0.0260 0.0121 0.9991
10.500 1.0762 0.01796 0.01239 0.0261 0.0118 1.0000
10.750 1.0877 0.01864 0.01313 0.0285 0.0116 1.0000
11.000 1.0948 0.01958 0.01415 0.0314 0.0112 1.0000
11.250 1.1098 0.01999 0.01459 0.0332 0.0111 1.0000
11.500 1.1229 0.02052 0.01517 0.0352 0.0110 1.0000
11.750 1.1339 0.02100 0.01571 0.0376 0.0108 1.0000
12.000 1.1423 0.02150 0.01626 0.0403 0.0106 1.0000
12.250 1.1503 0.02216 0.01697 0.0427 0.0105 1.0000
12.500 1.1599 0.02290 0.01777 0.0446 0.0102 1.0000
12.750 1.1705 0.02369 0.01862 0.0460 0.0099 1.0000
13.000 1.1813 0.02459 0.01957 0.0471 0.0096 1.0000
13.250 1.1909 0.02566 0.02072 0.0481 0.0094 1.0000
13.500 1.2015 0.02673 0.02184 0.0489 0.0092 1.0000
13.750 1.2131 0.02778 0.02294 0.0495 0.0089 1.0000
14.000 1.2234 0.02897 0.02418 0.0500 0.0087 1.0000
14.250 1.2319 0.03038 0.02564 0.0504 0.0085 1.0000
14.500 1.2415 0.03170 0.02704 0.0508 0.0083 1.0000
14.750 1.2579 0.03239 0.02777 0.0510 0.0074 1.0000
15.000 1.2636 0.03413 0.02959 0.0513 0.0073 1.0000
15.250 1.2779 0.03505 0.03052 0.0514 0.0066 1.0000
15.500 1.2877 0.03642 0.03191 0.0516 0.0062 1.0000
15.750 1.2913 0.03843 0.03400 0.0516 0.0060 1.0000
16.000 1.2948 0.04047 0.03610 0.0516 0.0057 1.0000
16.250 1.2940 0.04301 0.03873 0.0514 0.0056 1.0000
16.500 1.2985 0.04503 0.04077 0.0512 0.0051 1.0000
16.750 1.2937 0.04815 0.04399 0.0506 0.0051 1.0000
17.000 1.2854 0.05187 0.04783 0.0496 0.0051 1.0000
17.250 1.2766 0.05599 0.05205 0.0480 0.0050 1.0000
17.500 1.2640 0.06119 0.05736 0.0455 0.0047 1.0000
17.750 1.2355 0.07044 0.06684 0.0398 0.0049 1.0000
18.000 1.1939 0.08191 0.07854 0.0333 0.0049 1.0000
18.250 1.0963 0.10263 0.09962 0.0220 0.0056 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING 707 .19 SPAN AIRFOIL (b707b-il)