BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il) Reynolds number: 200,000 Max Cl/Cd: 43.61 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707a-il-200000-n5.txt Download as CSV file: xf-b707a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .08 SPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9521 0.10030 0.09540 -0.0092 1.0000 0.0176
-15.500 -0.9838 0.09028 0.08512 -0.0151 1.0000 0.0175
-15.250 -1.0041 0.08314 0.07777 -0.0189 1.0000 0.0174
-15.000 -1.0213 0.07695 0.07138 -0.0220 1.0000 0.0174
-14.750 -1.0355 0.07155 0.06578 -0.0244 1.0000 0.0173
-14.500 -1.0459 0.06689 0.06093 -0.0263 1.0000 0.0173
-14.250 -1.0545 0.06260 0.05646 -0.0278 1.0000 0.0173
-14.000 -1.0593 0.05893 0.05262 -0.0289 1.0000 0.0173
-13.750 -1.0629 0.05548 0.04902 -0.0297 1.0000 0.0173
-13.500 -1.0643 0.05241 0.04579 -0.0302 1.0000 0.0173
-13.250 -1.0640 0.04960 0.04283 -0.0305 1.0000 0.0173
-13.000 -1.0625 0.04701 0.04011 -0.0306 1.0000 0.0174
-12.750 -1.0602 0.04457 0.03753 -0.0305 1.0000 0.0174
-12.500 -1.0566 0.04234 0.03519 -0.0302 1.0000 0.0175
-12.250 -1.0519 0.04033 0.03306 -0.0297 1.0000 0.0175
-12.000 -1.0470 0.03839 0.03101 -0.0291 1.0000 0.0176
-11.750 -1.0414 0.03659 0.02910 -0.0282 1.0000 0.0177
-11.500 -1.0357 0.03490 0.02731 -0.0272 1.0000 0.0178
-11.250 -1.0293 0.03340 0.02572 -0.0259 1.0000 0.0178
-11.000 -1.0231 0.03198 0.02421 -0.0244 1.0000 0.0179
-10.750 -1.0166 0.03071 0.02286 -0.0225 1.0000 0.0180
-10.500 -1.0104 0.02954 0.02160 -0.0203 1.0000 0.0181
-10.250 -1.0041 0.02850 0.02049 -0.0178 1.0000 0.0182
-10.000 -0.9980 0.02754 0.01945 -0.0149 1.0000 0.0183
-9.750 -0.9899 0.02659 0.01844 -0.0123 1.0000 0.0185
-9.500 -0.9798 0.02566 0.01746 -0.0099 1.0000 0.0186
-9.250 -0.9691 0.02473 0.01650 -0.0076 1.0000 0.0189
-9.000 -0.9566 0.02390 0.01561 -0.0054 1.0000 0.0191
-8.750 -0.9430 0.02310 0.01477 -0.0033 1.0000 0.0194
-8.500 -0.9284 0.02236 0.01398 -0.0013 1.0000 0.0197
-8.250 -0.9130 0.02164 0.01322 0.0007 1.0000 0.0201
-8.000 -0.8968 0.02097 0.01251 0.0025 1.0000 0.0205
-7.750 -0.8800 0.02033 0.01182 0.0044 1.0000 0.0210
-7.500 -0.8629 0.01970 0.01116 0.0061 1.0000 0.0216
-7.250 -0.8455 0.01908 0.01054 0.0079 1.0000 0.0224
-7.000 -0.8274 0.01849 0.00996 0.0096 1.0000 0.0236
-6.750 -0.8085 0.01797 0.00949 0.0111 1.0000 0.0259
-6.500 -0.7878 0.01760 0.00927 0.0124 1.0000 0.0326
-6.250 -0.7656 0.01735 0.00898 0.0135 1.0000 0.0424
-6.000 -0.7431 0.01712 0.00872 0.0147 1.0000 0.0478
-5.750 -0.7156 0.01686 0.00841 0.0147 0.9981 0.0519
-5.500 -0.6838 0.01653 0.00807 0.0137 0.9932 0.0555
-5.250 -0.6535 0.01622 0.00771 0.0132 0.9876 0.0582
-5.000 -0.6220 0.01581 0.00730 0.0123 0.9812 0.0611
-4.750 -0.5945 0.01546 0.00693 0.0123 0.9736 0.0632
-4.500 -0.5645 0.01513 0.00657 0.0119 0.9666 0.0657
-4.250 -0.5352 0.01471 0.00616 0.0115 0.9551 0.0688
-3.750 -0.4269 0.01439 0.00498 0.0010 0.6263 0.0812
-3.500 -0.4058 0.01444 0.00469 0.0024 0.5373 0.0861
-3.250 -0.3822 0.01431 0.00442 0.0034 0.4986 0.0922
-3.000 -0.3609 0.01406 0.00408 0.0045 0.4097 0.1173
-2.750 -0.3446 0.01296 0.00346 0.0060 0.3784 0.2720
-2.500 -0.3212 0.01282 0.00357 0.0070 0.3689 0.3785
-2.250 -0.2949 0.01286 0.00355 0.0075 0.3634 0.3982
-2.000 -0.2683 0.01289 0.00352 0.0080 0.3596 0.4092
-1.500 -0.2153 0.01297 0.00350 0.0090 0.3516 0.4274
-1.250 -0.1889 0.01301 0.00352 0.0095 0.3463 0.4355
-1.000 -0.1625 0.01315 0.00353 0.0100 0.3393 0.4418
-0.750 -0.1361 0.01319 0.00356 0.0105 0.3327 0.4476
-0.500 -0.1096 0.01324 0.00360 0.0110 0.3270 0.4532
-0.250 -0.0828 0.01334 0.00364 0.0114 0.3230 0.4585
0.000 -0.0559 0.01344 0.00369 0.0118 0.3190 0.4645
0.250 -0.0293 0.01343 0.00375 0.0123 0.3137 0.4714
0.500 -0.0027 0.01354 0.00383 0.0127 0.3077 0.4787
0.750 0.0245 0.01362 0.00389 0.0131 0.3011 0.4844
1.000 0.0511 0.01363 0.00394 0.0135 0.2930 0.4882
1.250 0.0783 0.01359 0.00397 0.0139 0.2842 0.4908
1.500 0.1055 0.01356 0.00398 0.0143 0.2745 0.4939
1.750 0.1333 0.01345 0.00399 0.0146 0.2609 0.4973
2.000 0.1611 0.01334 0.00392 0.0149 0.2307 0.5014
2.500 0.2138 0.01344 0.00382 0.0158 0.1984 0.5105
2.750 0.2400 0.01356 0.00397 0.0163 0.1886 0.5161
3.000 0.2661 0.01373 0.00414 0.0167 0.1790 0.5222
3.250 0.2923 0.01387 0.00430 0.0172 0.1682 0.5285
3.500 0.3184 0.01396 0.00446 0.0177 0.1571 0.5363
3.750 0.3443 0.01410 0.00461 0.0182 0.1437 0.5460
4.000 0.3698 0.01422 0.00476 0.0188 0.1308 0.5582
4.250 0.3951 0.01434 0.00496 0.0194 0.1208 0.5749
4.500 0.4199 0.01446 0.00518 0.0201 0.1108 0.5993
4.750 0.4442 0.01456 0.00542 0.0210 0.1009 0.6361
5.000 0.4680 0.01463 0.00569 0.0220 0.0880 0.6860
5.250 0.4917 0.01474 0.00597 0.0230 0.0773 0.7424
5.500 0.5178 0.01490 0.00629 0.0236 0.0706 0.8050
5.750 0.5582 0.01519 0.00679 0.0213 0.0655 0.8856
6.000 0.6079 0.01567 0.00734 0.0167 0.0609 0.9487
6.250 0.6451 0.01613 0.00782 0.0147 0.0584 0.9794
6.500 0.6822 0.01658 0.00831 0.0127 0.0566 0.9966
6.750 0.7079 0.01696 0.00874 0.0130 0.0548 1.0000
7.000 0.7293 0.01742 0.00920 0.0142 0.0524 1.0000
7.250 0.7514 0.01781 0.00965 0.0153 0.0507 1.0000
7.500 0.7734 0.01821 0.01010 0.0164 0.0484 1.0000
7.750 0.7951 0.01866 0.01058 0.0176 0.0464 1.0000
8.000 0.8175 0.01903 0.01102 0.0186 0.0434 1.0000
8.250 0.8395 0.01945 0.01151 0.0197 0.0414 1.0000
8.500 0.8619 0.01985 0.01200 0.0207 0.0390 1.0000
8.750 0.8840 0.02027 0.01251 0.0218 0.0355 1.0000
9.000 0.9047 0.02088 0.01303 0.0229 0.0224 1.0000
9.250 0.9230 0.02176 0.01388 0.0242 0.0197 1.0000
9.500 0.9417 0.02258 0.01477 0.0255 0.0188 1.0000
9.750 0.9598 0.02346 0.01572 0.0269 0.0182 1.0000
10.000 0.9776 0.02433 0.01669 0.0282 0.0178 1.0000
10.250 0.9948 0.02524 0.01773 0.0296 0.0174 1.0000
10.500 1.0110 0.02622 0.01884 0.0311 0.0171 1.0000
10.750 1.0263 0.02726 0.02000 0.0326 0.0169 1.0000
11.000 1.0400 0.02838 0.02126 0.0341 0.0167 1.0000
11.250 1.0519 0.02962 0.02264 0.0358 0.0165 1.0000
11.500 1.0616 0.03097 0.02414 0.0376 0.0163 1.0000
11.750 1.0697 0.03235 0.02566 0.0394 0.0163 1.0000
12.000 1.0721 0.03402 0.02748 0.0416 0.0161 1.0000
12.250 1.0697 0.03571 0.02931 0.0442 0.0161 1.0000
12.500 1.0618 0.03796 0.03172 0.0464 0.0160 1.0000
12.750 1.0502 0.04101 0.03494 0.0469 0.0160 1.0000
13.000 1.0241 0.04782 0.04203 0.0420 0.0161 1.0000
13.250 0.9765 0.06134 0.05586 0.0309 0.0163 1.0000
13.500 0.9267 0.07312 0.06783 0.0235 0.0166 1.0000
13.750 0.8842 0.08401 0.07886 0.0172 0.0168 1.0000
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