BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il) Reynolds number: 500,000 Max Cl/Cd: 65.52 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707e-il-500000.txt Download as CSV file: xf-b707e-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4542 0.08631 0.08409 -0.0335 1.0000 0.0162
-8.500 -0.4576 0.08209 0.07989 -0.0368 1.0000 0.0162
-8.250 -0.4681 0.07847 0.07627 -0.0387 1.0000 0.0162
-8.000 -0.4735 0.07511 0.07288 -0.0389 1.0000 0.0163
-7.750 -0.4767 0.07166 0.06938 -0.0389 1.0000 0.0163
-7.500 -0.4785 0.06835 0.06602 -0.0382 1.0000 0.0163
-7.250 -0.4796 0.06507 0.06266 -0.0371 1.0000 0.0163
-7.000 -0.4799 0.06196 0.05946 -0.0355 1.0000 0.0163
-6.750 -0.4930 0.05475 0.05214 -0.0342 0.9993 0.0168
-6.500 -0.4714 0.04966 0.04692 -0.0382 0.9952 0.0174
-6.250 -0.4463 0.04617 0.04332 -0.0412 0.9903 0.0180
-6.000 -0.4182 0.04280 0.03980 -0.0442 0.9852 0.0187
-5.750 -0.3896 0.03969 0.03650 -0.0466 0.9795 0.0199
-5.500 -0.3597 0.03655 0.03314 -0.0484 0.9728 0.0217
-5.250 -0.3186 0.03569 0.03196 -0.0497 0.9689 0.0242
-5.000 -0.2893 0.03371 0.02968 -0.0504 0.9587 0.0245
-4.750 -0.2696 0.02694 0.02248 -0.0514 0.9469 0.0260
-4.500 -0.2404 0.02483 0.02028 -0.0529 0.9362 0.0271
-4.250 -0.2109 0.02317 0.01846 -0.0539 0.9236 0.0286
-4.000 -0.1822 0.02182 0.01690 -0.0543 0.9098 0.0311
-3.750 -0.1501 0.02255 0.01738 -0.0542 0.8967 0.0351
-3.500 -0.1284 0.01940 0.01379 -0.0532 0.8841 0.0369
-3.250 -0.1039 0.01767 0.01198 -0.0531 0.8734 0.0389
-3.000 -0.0788 0.01672 0.01092 -0.0527 0.8635 0.0413
-2.750 -0.0524 0.01626 0.01029 -0.0522 0.8551 0.0460
-2.500 -0.0275 0.01494 0.00878 -0.0516 0.8471 0.0520
-2.250 -0.0014 0.01419 0.00797 -0.0513 0.8401 0.0570
-1.750 0.0561 0.01243 0.00583 -0.0497 0.8271 0.0362
-1.500 0.0817 0.01150 0.00491 -0.0492 0.8202 0.0342
-1.250 0.1068 0.01085 0.00423 -0.0485 0.8141 0.0335
-1.000 0.1305 0.01023 0.00358 -0.0476 0.8066 0.0317
-0.750 0.1549 0.00982 0.00310 -0.0468 0.7997 0.0303
-0.500 0.1793 0.00948 0.00271 -0.0460 0.7915 0.0293
-0.250 0.2036 0.00922 0.00238 -0.0451 0.7794 0.0288
0.000 0.2278 0.00900 0.00208 -0.0441 0.7635 0.0288
0.250 0.2529 0.00883 0.00185 -0.0435 0.7502 0.0292
0.500 0.2778 0.00870 0.00163 -0.0427 0.7328 0.0304
0.750 0.3032 0.00861 0.00145 -0.0420 0.7160 0.0344
1.000 0.3130 0.00675 0.00135 -0.0390 0.7023 0.6656
1.250 0.3283 0.00608 0.00144 -0.0357 0.6830 0.8810
1.500 0.3960 0.00632 0.00156 -0.0439 0.6296 0.9737
1.750 0.4514 0.00689 0.00163 -0.0501 0.5192 0.9927
2.000 0.4822 0.00792 0.00185 -0.0516 0.3384 0.9984
2.250 0.5048 0.00860 0.00206 -0.0512 0.2360 1.0000
2.500 0.5238 0.00894 0.00218 -0.0496 0.1908 1.0000
2.750 0.5431 0.00927 0.00233 -0.0482 0.1510 1.0000
3.250 0.5800 0.01019 0.00279 -0.0449 0.0511 1.0000
3.500 0.6019 0.01038 0.00295 -0.0438 0.0482 1.0000
3.750 0.6243 0.01056 0.00312 -0.0428 0.0463 1.0000
4.000 0.6466 0.01076 0.00332 -0.0417 0.0438 1.0000
4.250 0.6688 0.01099 0.00359 -0.0407 0.0416 1.0000
4.500 0.6909 0.01122 0.00386 -0.0396 0.0406 1.0000
4.750 0.7125 0.01152 0.00421 -0.0385 0.0386 1.0000
5.000 0.7332 0.01191 0.00462 -0.0373 0.0354 1.0000
5.250 0.7540 0.01230 0.00506 -0.0360 0.0329 1.0000
5.500 0.7763 0.01255 0.00535 -0.0351 0.0313 1.0000
5.750 0.7989 0.01277 0.00561 -0.0342 0.0294 1.0000
6.000 0.8211 0.01306 0.00593 -0.0332 0.0267 1.0000
6.250 0.8405 0.01360 0.00650 -0.0318 0.0230 1.0000
6.500 0.8673 0.01347 0.00639 -0.0316 0.0179 1.0000
6.750 0.8901 0.01371 0.00655 -0.0308 0.0132 1.0000
7.000 0.9103 0.01422 0.00705 -0.0294 0.0113 1.0000
7.250 0.9295 0.01484 0.00776 -0.0279 0.0108 1.0000
7.500 0.9475 0.01557 0.00859 -0.0262 0.0103 1.0000
7.750 0.9644 0.01639 0.00952 -0.0243 0.0101 1.0000
8.000 0.9799 0.01735 0.01059 -0.0222 0.0099 1.0000
8.250 0.9941 0.01846 0.01185 -0.0199 0.0098 1.0000
8.500 1.0083 0.01966 0.01318 -0.0177 0.0098 1.0000
8.750 1.0235 0.02079 0.01441 -0.0159 0.0094 1.0000
9.000 1.0385 0.02210 0.01584 -0.0140 0.0091 1.0000
9.250 1.0532 0.02357 0.01744 -0.0121 0.0088 1.0000
9.500 1.0673 0.02540 0.01945 -0.0103 0.0086 1.0000
9.750 1.0817 0.02774 0.02207 -0.0085 0.0089 1.0000
15.500 0.6485 0.16535 0.16328 -0.0405 0.0194 1.0000
15.750 0.6514 0.16860 0.16653 -0.0424 0.0183 1.0000
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Polar data table (+)
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