BOEING 707 .54 SPAN AIRFOIL (b707d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .54 SPAN AIRFOIL (b707d-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.88 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707d-il-1000000.txt Download as CSV file: xf-b707d-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 707 .54 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4569 0.08119 0.07962 -0.0329 1.0000 0.0104
-8.500 -0.4636 0.07639 0.07484 -0.0379 1.0000 0.0104
-8.250 -0.4725 0.07276 0.07120 -0.0389 1.0000 0.0104
-8.000 -0.4753 0.06894 0.06734 -0.0398 1.0000 0.0104
-7.750 -0.4766 0.06554 0.06390 -0.0397 1.0000 0.0104
-7.250 -0.4146 0.03789 0.03611 -0.0500 0.9822 0.0108
-7.000 -0.3966 0.03400 0.03212 -0.0525 0.9721 0.0111
-6.750 -0.3777 0.03032 0.02832 -0.0545 0.9589 0.0114
-6.500 -0.3623 0.02714 0.02500 -0.0549 0.9418 0.0119
-6.250 -0.3494 0.02426 0.02194 -0.0541 0.9243 0.0125
-6.000 -0.3278 0.02229 0.01973 -0.0527 0.9102 0.0146
-5.750 -0.3092 0.02031 0.01754 -0.0514 0.8973 0.0148
-5.500 -0.2925 0.01791 0.01491 -0.0503 0.8853 0.0149
-5.250 -0.2751 0.01551 0.01229 -0.0492 0.8747 0.0150
-5.000 -0.2565 0.01341 0.00996 -0.0481 0.8653 0.0150
-2.250 0.0038 0.01045 0.00484 -0.0442 0.7982 0.0191
-2.000 0.0279 0.00919 0.00348 -0.0432 0.7911 0.0173
-1.750 0.0524 0.00863 0.00285 -0.0425 0.7845 0.0174
-1.500 0.0781 0.00828 0.00248 -0.0420 0.7775 0.0185
-1.250 0.1039 0.00804 0.00219 -0.0416 0.7700 0.0199
-1.000 0.1299 0.00783 0.00193 -0.0412 0.7598 0.0208
-0.750 0.1560 0.00767 0.00172 -0.0408 0.7473 0.0214
-0.500 0.1808 0.00738 0.00131 -0.0402 0.7309 0.0241
0.000 0.2332 0.00719 0.00098 -0.0394 0.7010 0.0333
0.250 0.2496 0.00567 0.00080 -0.0379 0.6898 0.5396
0.750 0.2889 0.00491 0.00084 -0.0344 0.6448 0.8260
1.000 0.3111 0.00480 0.00089 -0.0329 0.6211 0.9006
1.250 0.3396 0.00488 0.00095 -0.0330 0.5928 0.9418
1.500 0.3754 0.00517 0.00102 -0.0348 0.5331 0.9649
1.750 0.4093 0.00616 0.00129 -0.0368 0.3608 0.9805
2.000 0.4408 0.00685 0.00151 -0.0382 0.2535 0.9854
2.250 0.4741 0.00728 0.00166 -0.0399 0.1941 0.9895
2.500 0.5062 0.00767 0.00181 -0.0412 0.1440 0.9936
2.750 0.5401 0.00803 0.00197 -0.0430 0.1032 0.9965
3.000 0.5739 0.00843 0.00219 -0.0447 0.0589 0.9991
3.250 0.6024 0.00859 0.00232 -0.0451 0.0538 1.0000
3.500 0.6248 0.00872 0.00246 -0.0441 0.0495 1.0000
3.750 0.6469 0.00891 0.00262 -0.0431 0.0418 1.0000
4.000 0.6684 0.00917 0.00281 -0.0420 0.0275 1.0000
4.250 0.6909 0.00937 0.00298 -0.0410 0.0231 1.0000
4.500 0.7137 0.00957 0.00319 -0.0401 0.0215 1.0000
4.750 0.7365 0.00978 0.00342 -0.0392 0.0210 1.0000
5.000 0.7591 0.01003 0.00369 -0.0382 0.0204 1.0000
5.250 0.7816 0.01030 0.00402 -0.0373 0.0196 1.0000
5.500 0.8037 0.01062 0.00437 -0.0363 0.0185 1.0000
5.750 0.8252 0.01101 0.00480 -0.0352 0.0168 1.0000
6.000 0.8467 0.01139 0.00524 -0.0341 0.0151 1.0000
6.250 0.8696 0.01165 0.00550 -0.0334 0.0130 1.0000
6.500 0.8891 0.01225 0.00615 -0.0320 0.0104 1.0000
6.750 0.9125 0.01249 0.00641 -0.0313 0.0093 1.0000
7.000 0.9351 0.01279 0.00673 -0.0305 0.0083 1.0000
7.250 0.9573 0.01315 0.00707 -0.0296 0.0073 1.0000
7.500 0.9760 0.01387 0.00789 -0.0281 0.0069 1.0000
7.750 0.9955 0.01449 0.00858 -0.0268 0.0065 1.0000
8.000 1.0148 0.01513 0.00930 -0.0254 0.0060 1.0000
8.250 1.0319 0.01598 0.01024 -0.0237 0.0059 1.0000
8.500 1.0480 0.01693 0.01128 -0.0219 0.0057 1.0000
8.750 1.0624 0.01809 0.01256 -0.0199 0.0056 1.0000
9.000 1.0759 0.01947 0.01407 -0.0177 0.0056 1.0000
9.250 1.0889 0.02119 0.01596 -0.0155 0.0056 1.0000
9.500 1.1059 0.02201 0.01687 -0.0142 0.0054 1.0000
9.750 1.1211 0.02308 0.01805 -0.0126 0.0053 1.0000
10.000 1.1315 0.02536 0.02055 -0.0103 0.0052 1.0000
10.250 1.1439 0.02658 0.02190 -0.0084 0.0052 1.0000
10.500 1.1280 0.03428 0.03036 -0.0028 0.0058 1.0000
10.750 1.1204 0.03691 0.03324 0.0015 0.0058 1.0000
11.000 1.0997 0.04094 0.03758 0.0067 0.0062 1.0000
11.250 1.0834 0.04409 0.04094 0.0103 0.0063 1.0000
11.500 1.0709 0.04693 0.04397 0.0127 0.0062 1.0000
11.750 1.0488 0.05105 0.04826 0.0144 0.0066 1.0000
12.000 1.0322 0.05500 0.05241 0.0150 0.0064 1.0000
12.250 1.0041 0.06077 0.05831 0.0141 0.0068 1.0000
12.500 0.9873 0.06575 0.06345 0.0123 0.0067 1.0000
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Polar data table (+)
Polar graphs
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