BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.39 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b707a-il-1000000.txt Download as CSV file: xf-b707a-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.5990 0.18839 0.18680 0.0404 1.0000 0.0170
-17.750 -1.0221 0.11815 0.11567 -0.0004 1.0000 0.0159
-17.500 -1.0481 0.10827 0.10563 -0.0067 1.0000 0.0158
-17.250 -1.0348 0.10793 0.10536 -0.0049 1.0000 0.0153
-17.000 -1.0630 0.09844 0.09572 -0.0104 1.0000 0.0152
-16.750 -1.0836 0.09087 0.08800 -0.0147 1.0000 0.0153
-16.500 -1.1067 0.08352 0.08050 -0.0183 1.0000 0.0150
-16.250 -1.1237 0.07732 0.07415 -0.0215 1.0000 0.0150
-16.000 -1.1398 0.07161 0.06829 -0.0243 1.0000 0.0150
-15.750 -1.1546 0.06632 0.06286 -0.0265 1.0000 0.0149
-15.500 -1.1732 0.06070 0.05704 -0.0286 1.0000 0.0145
-15.250 -1.1794 0.05688 0.05311 -0.0301 1.0000 0.0145
-15.000 -1.1852 0.05320 0.04930 -0.0314 1.0000 0.0146
-14.750 -1.1913 0.04953 0.04548 -0.0324 1.0000 0.0145
-14.500 -1.1948 0.04628 0.04209 -0.0331 1.0000 0.0144
-14.250 -1.1981 0.04311 0.03877 -0.0335 1.0000 0.0143
-14.000 -1.1956 0.04079 0.03636 -0.0337 1.0000 0.0143
-13.750 -1.1966 0.03806 0.03345 -0.0336 1.0000 0.0141
-13.500 -1.1937 0.03589 0.03115 -0.0332 1.0000 0.0140
-13.250 -1.1892 0.03397 0.02911 -0.0326 1.0000 0.0139
-13.000 -1.1827 0.03227 0.02732 -0.0317 1.0000 0.0138
-12.750 -1.1757 0.03070 0.02564 -0.0306 1.0000 0.0137
-12.500 -1.1681 0.02929 0.02416 -0.0294 1.0000 0.0137
-12.250 -1.1599 0.02807 0.02284 -0.0279 1.0000 0.0136
-12.000 -1.1515 0.02690 0.02161 -0.0261 1.0000 0.0136
-11.750 -1.1428 0.02586 0.02050 -0.0241 1.0000 0.0135
-11.500 -1.1343 0.02490 0.01948 -0.0218 1.0000 0.0135
-11.250 -1.1261 0.02408 0.01861 -0.0192 1.0000 0.0135
-11.000 -1.0458 0.02312 0.01648 -0.0316 0.5497 0.0134
-10.750 -1.0383 0.02243 0.01560 -0.0287 0.4855 0.0135
-10.500 -1.0308 0.02196 0.01483 -0.0256 0.3501 0.0135
-10.250 -1.0216 0.02124 0.01404 -0.0228 0.3388 0.0136
-10.000 -1.0076 0.02054 0.01329 -0.0208 0.3348 0.0136
-9.750 -0.9927 0.01985 0.01255 -0.0189 0.3321 0.0136
-9.500 -0.9756 0.01928 0.01193 -0.0172 0.3302 0.0135
-9.250 -0.9588 0.01866 0.01125 -0.0155 0.3284 0.0135
-9.000 -0.9403 0.01811 0.01066 -0.0140 0.3272 0.0135
-8.750 -0.9220 0.01753 0.01003 -0.0125 0.3261 0.0135
-8.500 -0.9029 0.01698 0.00944 -0.0111 0.3251 0.0135
-8.250 -0.8834 0.01643 0.00885 -0.0097 0.3241 0.0135
-8.000 -0.8627 0.01595 0.00833 -0.0085 0.3234 0.0135
-7.750 -0.8419 0.01544 0.00779 -0.0073 0.3227 0.0136
-7.500 -0.8204 0.01498 0.00729 -0.0061 0.3221 0.0137
-7.250 -0.7982 0.01456 0.00683 -0.0051 0.3217 0.0138
-7.000 -0.7755 0.01416 0.00639 -0.0041 0.3212 0.0139
-6.750 -0.7522 0.01380 0.00601 -0.0033 0.3209 0.0140
-6.500 -0.7284 0.01347 0.00564 -0.0024 0.3207 0.0141
-6.250 -0.7045 0.01312 0.00527 -0.0016 0.3201 0.0145
-6.000 -0.6800 0.01283 0.00495 -0.0009 0.3195 0.0148
-5.750 -0.6550 0.01258 0.00467 -0.0002 0.3192 0.0150
-5.500 -0.6298 0.01234 0.00441 0.0004 0.3189 0.0154
-5.250 -0.6043 0.01212 0.00415 0.0010 0.3184 0.0159
-5.000 -0.5789 0.01189 0.00390 0.0016 0.3173 0.0166
-4.750 -0.5532 0.01168 0.00366 0.0022 0.3165 0.0176
-4.500 -0.5275 0.01146 0.00344 0.0028 0.3161 0.0198
-4.250 -0.5023 0.01119 0.00328 0.0034 0.3156 0.0408
-4.000 -0.4753 0.01112 0.00323 0.0037 0.3146 0.0457
-3.750 -0.4485 0.01103 0.00317 0.0041 0.3131 0.0493
-3.500 -0.4213 0.01100 0.00312 0.0044 0.3120 0.0518
-3.250 -0.3948 0.01088 0.00302 0.0048 0.3104 0.0546
-3.000 -0.3680 0.01083 0.00296 0.0052 0.3087 0.0570
-2.750 -0.3415 0.01078 0.00289 0.0056 0.3066 0.0591
-2.500 -0.3148 0.01066 0.00279 0.0061 0.3053 0.0617
-2.250 -0.2877 0.01056 0.00269 0.0064 0.3043 0.0639
-2.000 -0.2604 0.01045 0.00259 0.0067 0.3024 0.0659
-1.750 -0.2334 0.01032 0.00247 0.0071 0.2999 0.0692
-1.500 -0.2064 0.01023 0.00238 0.0075 0.2970 0.0734
-1.250 -0.1847 0.00946 0.00208 0.0085 0.2940 0.2143
-1.000 -0.1641 0.00873 0.00188 0.0097 0.2912 0.3637
-0.750 -0.1360 0.00865 0.00187 0.0100 0.2892 0.3854
-0.500 -0.1081 0.00857 0.00185 0.0102 0.2857 0.3965
-0.250 -0.0797 0.00858 0.00184 0.0104 0.2817 0.4030
0.000 -0.0523 0.00860 0.00185 0.0107 0.2775 0.4098
0.250 -0.0237 0.00850 0.00180 0.0108 0.2738 0.4148
0.500 0.0050 0.00844 0.00173 0.0110 0.2661 0.4185
0.750 0.0341 0.00835 0.00155 0.0110 0.2257 0.4213
1.000 0.0608 0.00856 0.00159 0.0114 0.1954 0.4233
1.250 0.0875 0.00865 0.00164 0.0118 0.1809 0.4279
1.500 0.1146 0.00873 0.00169 0.0122 0.1682 0.4317
1.750 0.1418 0.00881 0.00175 0.0125 0.1550 0.4350
2.000 0.1689 0.00894 0.00181 0.0129 0.1400 0.4382
2.250 0.1961 0.00907 0.00188 0.0132 0.1265 0.4407
2.500 0.2234 0.00921 0.00196 0.0136 0.1165 0.4429
2.750 0.2501 0.00931 0.00204 0.0140 0.1054 0.4477
3.000 0.2769 0.00944 0.00213 0.0144 0.0902 0.4521
3.500 0.3291 0.00995 0.00246 0.0153 0.0542 0.4587
3.750 0.3561 0.01009 0.00260 0.0157 0.0510 0.4618
4.000 0.3832 0.01023 0.00273 0.0160 0.0484 0.4652
4.250 0.4099 0.01034 0.00287 0.0164 0.0464 0.4714
4.500 0.4369 0.01043 0.00299 0.0168 0.0444 0.4770
4.750 0.4637 0.01058 0.00313 0.0172 0.0421 0.4827
5.000 0.4906 0.01067 0.00326 0.0176 0.0396 0.4908
5.250 0.5172 0.01079 0.00340 0.0180 0.0361 0.5011
5.500 0.5417 0.01117 0.00371 0.0187 0.0162 0.5144
5.750 0.5674 0.01134 0.00397 0.0193 0.0148 0.5345
6.000 0.5925 0.01147 0.00424 0.0199 0.0142 0.5696
6.250 0.6160 0.01148 0.00453 0.0209 0.0137 0.6482
6.500 0.6387 0.01150 0.00482 0.0221 0.0134 0.7266
6.750 0.6602 0.01150 0.00512 0.0236 0.0132 0.8030
7.000 0.6892 0.01146 0.00552 0.0237 0.0129 0.9381
7.250 0.7493 0.01194 0.00607 0.0167 0.0128 0.9777
7.500 0.7861 0.01238 0.00653 0.0148 0.0126 0.9889
7.750 0.8200 0.01282 0.00701 0.0135 0.0125 0.9965
8.000 0.8564 0.01330 0.00753 0.0116 0.0124 1.0000
8.250 0.8777 0.01372 0.00797 0.0129 0.0123 1.0000
8.500 0.8989 0.01416 0.00846 0.0143 0.0123 1.0000
8.750 0.9199 0.01462 0.00896 0.0156 0.0123 1.0000
9.000 0.9407 0.01512 0.00949 0.0170 0.0123 1.0000
9.250 0.9610 0.01566 0.01008 0.0184 0.0122 1.0000
9.500 0.9814 0.01619 0.01066 0.0198 0.0122 1.0000
9.750 1.0012 0.01677 0.01129 0.0212 0.0122 1.0000
10.000 1.0207 0.01738 0.01195 0.0226 0.0121 1.0000
10.250 1.0394 0.01804 0.01266 0.0241 0.0120 1.0000
10.500 1.0576 0.01873 0.01341 0.0257 0.0120 1.0000
10.750 1.0754 0.01944 0.01418 0.0272 0.0120 1.0000
11.000 1.0926 0.02018 0.01498 0.0288 0.0120 1.0000
11.250 1.1088 0.02098 0.01584 0.0305 0.0120 1.0000
11.500 1.1243 0.02181 0.01674 0.0323 0.0120 1.0000
11.750 1.1392 0.02265 0.01764 0.0340 0.0120 1.0000
12.000 1.1521 0.02360 0.01866 0.0360 0.0120 1.0000
12.250 1.1642 0.02455 0.01968 0.0380 0.0120 1.0000
12.500 1.1741 0.02559 0.02079 0.0401 0.0120 1.0000
12.750 1.1816 0.02667 0.02195 0.0425 0.0120 1.0000
13.000 1.1825 0.02779 0.02314 0.0459 0.0120 1.0000
13.250 1.1820 0.02909 0.02451 0.0490 0.0120 1.0000
13.500 1.1808 0.03064 0.02616 0.0513 0.0120 1.0000
13.750 1.1779 0.03262 0.02823 0.0527 0.0120 1.0000
14.000 1.1717 0.03549 0.03122 0.0525 0.0121 1.0000
14.250 1.1627 0.04047 0.03637 0.0482 0.0121 1.0000
14.500 1.1536 0.04702 0.04308 0.0420 0.0121 1.0000
14.750 1.1431 0.05388 0.05008 0.0365 0.0121 1.0000
15.000 1.1265 0.06059 0.05690 0.0321 0.0121 1.0000
15.250 1.1068 0.06700 0.06341 0.0282 0.0122 1.0000
15.500 1.0887 0.07301 0.06949 0.0248 0.0122 1.0000
15.750 1.0729 0.07874 0.07531 0.0216 0.0123 1.0000
16.000 1.0574 0.08452 0.08116 0.0185 0.0123 1.0000
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Polar data table (+)
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