BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.45 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b707a-il-1000000-n5.txt Download as CSV file: xf-b707a-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -0.9890 0.15939 0.15702 0.0255 1.0000 0.0091
-19.250 -1.0397 0.14248 0.13985 0.0159 1.0000 0.0090
-19.000 -1.0616 0.13330 0.13054 0.0108 1.0000 0.0090
-18.750 -1.0851 0.12410 0.12120 0.0058 1.0000 0.0090
-18.500 -1.1044 0.11594 0.11290 0.0014 1.0000 0.0089
-18.250 -1.1231 0.10816 0.10498 -0.0027 1.0000 0.0089
-18.000 -1.1384 0.10135 0.09805 -0.0061 1.0000 0.0089
-17.750 -1.1519 0.09514 0.09172 -0.0091 1.0000 0.0089
-17.500 -1.1633 0.08953 0.08601 -0.0118 1.0000 0.0089
-17.250 -1.1735 0.08428 0.08065 -0.0141 1.0000 0.0089
-17.000 -1.1827 0.07935 0.07561 -0.0163 1.0000 0.0089
-16.750 -1.1899 0.07487 0.07104 -0.0181 1.0000 0.0089
-16.500 -1.1974 0.07046 0.06653 -0.0199 1.0000 0.0088
-16.250 -1.2028 0.06648 0.06246 -0.0214 1.0000 0.0089
-16.000 -1.2079 0.06267 0.05856 -0.0227 1.0000 0.0089
-15.750 -1.2129 0.05899 0.05478 -0.0238 1.0000 0.0089
-15.250 -1.2198 0.05219 0.04780 -0.0258 1.0000 0.0089
-14.750 -1.1405 0.04442 0.03898 -0.0458 0.6830 0.0090
-14.500 -1.1437 0.04274 0.03654 -0.0448 0.3333 0.0090
-14.250 -1.1426 0.04034 0.03404 -0.0449 0.3198 0.0090
-14.000 -1.1380 0.03833 0.03197 -0.0449 0.3167 0.0091
-13.750 -1.1362 0.03613 0.02968 -0.0447 0.3137 0.0091
-13.500 -1.1327 0.03418 0.02765 -0.0443 0.3113 0.0091
-13.250 -1.1290 0.03234 0.02573 -0.0437 0.3095 0.0091
-13.000 -1.1247 0.03065 0.02396 -0.0429 0.3074 0.0091
-12.500 -1.1165 0.02758 0.02075 -0.0404 0.3051 0.0092
-12.250 -1.1115 0.02631 0.01941 -0.0388 0.3040 0.0091
-12.000 -1.1064 0.02515 0.01819 -0.0368 0.3034 0.0092
-11.750 -1.1003 0.02415 0.01712 -0.0346 0.3030 0.0092
-11.500 -1.0944 0.02321 0.01612 -0.0321 0.3023 0.0092
-11.250 -1.0868 0.02242 0.01527 -0.0294 0.3018 0.0092
-11.000 -1.0787 0.02170 0.01450 -0.0266 0.3013 0.0092
-10.750 -1.0706 0.02109 0.01383 -0.0236 0.3006 0.0092
-10.500 -1.0590 0.02047 0.01316 -0.0212 0.3002 0.0093
-10.250 -1.0441 0.01987 0.01251 -0.0193 0.2998 0.0093
-10.000 -1.0283 0.01927 0.01185 -0.0175 0.2994 0.0093
-9.750 -1.0112 0.01871 0.01124 -0.0158 0.2988 0.0094
-9.500 -0.9929 0.01819 0.01068 -0.0144 0.2984 0.0094
-9.250 -0.9741 0.01767 0.01011 -0.0130 0.2978 0.0094
-9.000 -0.9543 0.01720 0.00959 -0.0117 0.2975 0.0095
-8.750 -0.9340 0.01673 0.00907 -0.0104 0.2972 0.0095
-8.500 -0.9129 0.01630 0.00861 -0.0093 0.2968 0.0096
-8.250 -0.8915 0.01588 0.00814 -0.0082 0.2965 0.0097
-8.000 -0.8695 0.01548 0.00771 -0.0072 0.2962 0.0098
-7.750 -0.8470 0.01510 0.00729 -0.0062 0.2959 0.0099
-7.500 -0.8241 0.01475 0.00690 -0.0053 0.2957 0.0100
-7.250 -0.8008 0.01442 0.00654 -0.0045 0.2955 0.0101
-7.000 -0.7771 0.01410 0.00619 -0.0037 0.2952 0.0102
-6.750 -0.7531 0.01381 0.00586 -0.0029 0.2950 0.0103
-6.500 -0.7287 0.01353 0.00556 -0.0022 0.2948 0.0104
-6.250 -0.7040 0.01329 0.00529 -0.0015 0.2940 0.0106
-6.000 -0.6796 0.01300 0.00497 -0.0008 0.2931 0.0108
-5.750 -0.6548 0.01276 0.00469 -0.0002 0.2924 0.0109
-5.500 -0.6296 0.01252 0.00444 0.0005 0.2921 0.0112
-5.250 -0.6042 0.01231 0.00420 0.0011 0.2917 0.0115
-5.000 -0.5785 0.01212 0.00399 0.0016 0.2911 0.0118
-4.750 -0.5524 0.01193 0.00379 0.0021 0.2905 0.0122
-4.500 -0.5263 0.01176 0.00360 0.0026 0.2901 0.0125
-4.250 -0.5000 0.01160 0.00342 0.0030 0.2898 0.0129
-4.000 -0.4736 0.01144 0.00325 0.0035 0.2891 0.0135
-3.750 -0.4473 0.01127 0.00307 0.0039 0.2880 0.0150
-3.500 -0.4221 0.01096 0.00286 0.0046 0.2871 0.0377
-3.250 -0.3952 0.01085 0.00278 0.0049 0.2859 0.0426
-3.000 -0.3680 0.01076 0.00269 0.0052 0.2844 0.0457
-2.750 -0.3410 0.01066 0.00260 0.0056 0.2828 0.0486
-2.500 -0.3139 0.01058 0.00252 0.0059 0.2812 0.0506
-2.250 -0.2868 0.01051 0.00244 0.0063 0.2797 0.0524
-2.000 -0.2598 0.01043 0.00237 0.0066 0.2775 0.0543
-1.750 -0.2322 0.01031 0.00227 0.0069 0.2756 0.0559
-1.500 -0.2046 0.01021 0.00218 0.0072 0.2725 0.0578
-1.250 -0.1772 0.01009 0.00208 0.0075 0.2689 0.0618
-1.000 -0.1498 0.00999 0.00199 0.0078 0.2653 0.0673
-0.750 -0.1226 0.00982 0.00188 0.0082 0.2603 0.0850
-0.500 -0.0999 0.00906 0.00149 0.0090 0.2192 0.2358
0.000 -0.0506 0.00860 0.00135 0.0104 0.1877 0.3664
0.250 -0.0234 0.00864 0.00140 0.0107 0.1795 0.3758
0.500 0.0039 0.00871 0.00144 0.0111 0.1672 0.3824
0.750 0.0312 0.00882 0.00147 0.0114 0.1493 0.3860
1.000 0.0580 0.00893 0.00151 0.0118 0.1293 0.3910
1.250 0.0850 0.00905 0.00157 0.0121 0.1152 0.3960
1.500 0.1123 0.00914 0.00163 0.0125 0.1062 0.3997
1.750 0.1398 0.00924 0.00170 0.0128 0.0984 0.4025
2.000 0.1658 0.00953 0.00182 0.0132 0.0612 0.4051
2.250 0.1927 0.00967 0.00193 0.0136 0.0532 0.4089
2.500 0.2199 0.00977 0.00203 0.0140 0.0501 0.4126
2.750 0.2471 0.00988 0.00214 0.0143 0.0473 0.4166
3.000 0.2744 0.00998 0.00224 0.0146 0.0445 0.4199
3.250 0.3017 0.01011 0.00235 0.0150 0.0417 0.4219
3.500 0.3289 0.01024 0.00245 0.0153 0.0374 0.4232
3.750 0.3546 0.01058 0.00269 0.0159 0.0128 0.4263
4.000 0.3814 0.01073 0.00286 0.0163 0.0117 0.4294
4.250 0.4083 0.01087 0.00302 0.0166 0.0112 0.4326
4.500 0.4353 0.01102 0.00319 0.0170 0.0109 0.4355
4.750 0.4621 0.01118 0.00337 0.0174 0.0107 0.4384
5.000 0.4889 0.01135 0.00357 0.0178 0.0105 0.4410
5.500 0.5420 0.01172 0.00400 0.0187 0.0101 0.4482
5.750 0.5683 0.01191 0.00424 0.0191 0.0100 0.4531
6.000 0.5945 0.01213 0.00451 0.0196 0.0098 0.4579
6.250 0.6205 0.01237 0.00479 0.0201 0.0096 0.4635
6.500 0.6462 0.01261 0.00509 0.0206 0.0095 0.4716
6.750 0.6717 0.01288 0.00543 0.0212 0.0093 0.4815
7.000 0.6965 0.01322 0.00586 0.0218 0.0091 0.4936
7.250 0.7213 0.01352 0.00624 0.0225 0.0090 0.5080
7.750 0.7704 0.01404 0.00698 0.0238 0.0089 0.5539
8.000 0.7939 0.01427 0.00739 0.0247 0.0088 0.6008
8.250 0.8165 0.01450 0.00783 0.0257 0.0088 0.6606
8.500 0.8389 0.01477 0.00829 0.0267 0.0087 0.7128
8.750 0.8603 0.01504 0.00877 0.0279 0.0086 0.7637
9.000 0.8787 0.01522 0.00926 0.0299 0.0086 0.8437
9.250 0.9428 0.01586 0.01026 0.0218 0.0085 0.9843
9.500 0.9735 0.01649 0.01095 0.0209 0.0084 0.9978
9.750 0.9977 0.01710 0.01160 0.0213 0.0084 1.0000
10.000 1.0174 0.01769 0.01225 0.0227 0.0084 1.0000
10.250 1.0364 0.01833 0.01294 0.0241 0.0083 1.0000
10.500 1.0549 0.01900 0.01367 0.0256 0.0083 1.0000
10.750 1.0729 0.01970 0.01443 0.0271 0.0083 1.0000
11.000 1.0903 0.02043 0.01522 0.0286 0.0083 1.0000
11.250 1.1068 0.02123 0.01609 0.0303 0.0082 1.0000
11.500 1.1224 0.02207 0.01699 0.0319 0.0082 1.0000
11.750 1.1382 0.02286 0.01785 0.0335 0.0082 1.0000
12.000 1.1514 0.02382 0.01888 0.0354 0.0081 1.0000
12.250 1.1642 0.02475 0.01988 0.0372 0.0081 1.0000
12.500 1.1747 0.02580 0.02101 0.0393 0.0080 1.0000
12.750 1.1833 0.02689 0.02218 0.0414 0.0080 1.0000
13.000 1.1856 0.02804 0.02341 0.0445 0.0080 1.0000
13.250 1.1840 0.02939 0.02485 0.0477 0.0080 1.0000
13.500 1.1813 0.03106 0.02662 0.0501 0.0079 1.0000
13.750 1.1768 0.03324 0.02890 0.0513 0.0079 1.0000
14.000 1.1636 0.03728 0.03311 0.0497 0.0079 1.0000
14.250 1.1420 0.04757 0.04368 0.0390 0.0079 1.0000
14.500 1.1074 0.05846 0.05475 0.0308 0.0080 1.0000
14.750 1.0699 0.06768 0.06410 0.0249 0.0080 1.0000
15.000 1.0390 0.07593 0.07247 0.0202 0.0081 1.0000
15.250 1.0145 0.08325 0.07987 0.0162 0.0081 1.0000
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Polar data table (+)
Polar graphs
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