BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.05 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707c-il-1000000.txt Download as CSV file: xf-b707c-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .40 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4801 0.08746 0.08577 -0.0256 1.0000 0.0108
-9.000 -0.4816 0.08351 0.08184 -0.0277 1.0000 0.0109
-8.750 -0.4861 0.07926 0.07761 -0.0305 1.0000 0.0109
-8.500 -0.5003 0.07461 0.07298 -0.0346 1.0000 0.0109
-8.250 -0.5162 0.07120 0.06956 -0.0342 1.0000 0.0110
-8.000 -0.5245 0.06783 0.06614 -0.0338 1.0000 0.0110
-7.750 -0.5316 0.06478 0.06305 -0.0324 1.0000 0.0111
-7.500 -0.5124 0.05943 0.05756 -0.0372 0.9970 0.0119
-7.250 -0.4884 0.05381 0.05165 -0.0406 0.9926 0.0123
-7.000 -0.4668 0.04983 0.04751 -0.0426 0.9885 0.0123
-6.750 -0.4511 0.04414 0.04163 -0.0450 0.9851 0.0126
-6.500 -0.4323 0.04151 0.03891 -0.0457 0.9790 0.0127
-6.250 -0.4073 0.03877 0.03606 -0.0473 0.9747 0.0129
-6.000 -0.3810 0.03628 0.03344 -0.0488 0.9682 0.0132
-5.750 -0.3513 0.03368 0.03068 -0.0506 0.9596 0.0136
-5.500 -0.3217 0.03111 0.02791 -0.0518 0.9446 0.0142
-5.250 -0.2883 0.02893 0.02539 -0.0513 0.9245 0.0155
-5.000 -0.2653 0.02703 0.02319 -0.0503 0.8898 0.0155
-4.750 -0.2520 0.02368 0.01945 -0.0482 0.8446 0.0158
-4.500 -0.2356 0.02256 0.01801 -0.0464 0.7774 0.0161
-4.250 -0.2182 0.02168 0.01678 -0.0446 0.7074 0.0163
-4.000 -0.1971 0.02067 0.01553 -0.0435 0.6733 0.0167
-3.750 -0.1743 0.01956 0.01422 -0.0425 0.6534 0.0173
-3.250 -0.1262 0.01689 0.01090 -0.0397 0.6160 0.0197
-3.000 -0.1021 0.01586 0.00979 -0.0392 0.5973 0.0202
-2.750 -0.0774 0.01509 0.00890 -0.0387 0.5750 0.0208
-2.500 -0.0516 0.01174 0.00510 -0.0366 0.5512 0.0158
-2.250 -0.0302 0.01148 0.00446 -0.0353 0.4546 0.0157
-2.000 -0.0130 0.01173 0.00403 -0.0335 0.2672 0.0156
-1.750 0.0082 0.01125 0.00335 -0.0323 0.2199 0.0159
-1.500 0.0323 0.01092 0.00297 -0.0316 0.2097 0.0163
-1.250 0.0566 0.01064 0.00261 -0.0308 0.1980 0.0164
-1.000 0.0814 0.01047 0.00230 -0.0302 0.1721 0.0167
-0.750 0.1041 0.01071 0.00219 -0.0293 0.0378 0.0173
-0.500 0.1301 0.01061 0.00208 -0.0289 0.0366 0.0185
-0.250 0.1563 0.01053 0.00200 -0.0285 0.0356 0.0210
0.000 0.1827 0.01052 0.00201 -0.0281 0.0350 0.0266
0.250 0.2090 0.01054 0.00206 -0.0278 0.0331 0.0343
0.500 0.2348 0.01062 0.00214 -0.0274 0.0310 0.0390
0.750 0.2610 0.01065 0.00217 -0.0271 0.0306 0.0436
1.000 0.2875 0.01067 0.00217 -0.0269 0.0298 0.0470
1.250 0.3136 0.01069 0.00219 -0.0266 0.0292 0.0584
1.500 0.3347 0.01000 0.00219 -0.0256 0.0272 0.3747
1.750 0.3596 0.00997 0.00229 -0.0252 0.0260 0.4254
2.000 0.3816 0.00959 0.00232 -0.0243 0.0251 0.5610
2.250 0.4037 0.00923 0.00236 -0.0232 0.0241 0.7041
2.500 0.4288 0.00921 0.00242 -0.0227 0.0231 0.7411
2.750 0.4534 0.00918 0.00249 -0.0221 0.0224 0.7774
3.000 0.4772 0.00915 0.00256 -0.0212 0.0212 0.8174
3.250 0.5003 0.00908 0.00265 -0.0202 0.0206 0.8665
3.500 0.5255 0.00903 0.00276 -0.0195 0.0190 0.9210
3.750 0.5621 0.00919 0.00288 -0.0215 0.0125 0.9542
4.000 0.6034 0.00945 0.00315 -0.0247 0.0120 0.9723
4.250 0.6424 0.00972 0.00343 -0.0274 0.0117 0.9816
4.500 0.6777 0.00998 0.00368 -0.0292 0.0116 0.9892
4.750 0.7106 0.01023 0.00392 -0.0306 0.0116 0.9952
5.000 0.7467 0.01050 0.00419 -0.0327 0.0115 0.9995
5.250 0.7712 0.01074 0.00444 -0.0321 0.0115 1.0000
5.500 0.7929 0.01098 0.00468 -0.0310 0.0115 1.0000
5.750 0.8147 0.01122 0.00494 -0.0299 0.0116 1.0000
6.000 0.8366 0.01148 0.00521 -0.0288 0.0116 1.0000
6.250 0.8585 0.01176 0.00551 -0.0277 0.0117 1.0000
6.500 0.8803 0.01205 0.00583 -0.0266 0.0118 1.0000
6.750 0.9019 0.01237 0.00618 -0.0255 0.0118 1.0000
7.000 0.9233 0.01270 0.00654 -0.0244 0.0119 1.0000
7.250 0.9437 0.01313 0.00700 -0.0231 0.0118 1.0000
7.500 0.9644 0.01354 0.00745 -0.0219 0.0118 1.0000
7.750 0.9848 0.01398 0.00793 -0.0206 0.0118 1.0000
8.000 1.0051 0.01442 0.00842 -0.0194 0.0119 1.0000
8.250 1.0246 0.01494 0.00898 -0.0180 0.0120 1.0000
8.500 1.0438 0.01548 0.00958 -0.0166 0.0120 1.0000
8.750 1.0624 0.01606 0.01022 -0.0152 0.0121 1.0000
9.000 1.0802 0.01670 0.01092 -0.0136 0.0122 1.0000
9.250 1.0972 0.01742 0.01171 -0.0120 0.0122 1.0000
9.500 1.1136 0.01818 0.01256 -0.0102 0.0122 1.0000
9.750 1.1288 0.01906 0.01352 -0.0084 0.0123 1.0000
10.000 1.1425 0.02011 0.01467 -0.0064 0.0124 1.0000
10.250 1.1572 0.02106 0.01570 -0.0045 0.0125 1.0000
10.500 1.1694 0.02234 0.01712 -0.0024 0.0124 1.0000
10.750 1.1833 0.02309 0.01794 -0.0004 0.0125 1.0000
11.000 1.1964 0.02374 0.01865 0.0017 0.0127 1.0000
11.250 1.2069 0.02484 0.01987 0.0040 0.0128 1.0000
11.500 1.2173 0.02595 0.02112 0.0063 0.0129 1.0000
15.500 0.7876 0.17401 0.17222 -0.0370 0.0158 1.0000
15.750 0.7929 0.17759 0.17579 -0.0388 0.0155 1.0000
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