BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 50,000 Max Cl/Cd: 32.58 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-boe103-il-50000.txt Download as CSV file: xf-boe103-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 103 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3430 0.10999 0.10301 -0.0267 1.0000 0.2656
-8.750 -0.3256 0.10581 0.09885 -0.0252 1.0000 0.2758
-8.500 -0.3641 0.10655 0.09983 -0.0246 1.0000 0.2834
-8.250 -0.3405 0.10212 0.09538 -0.0227 1.0000 0.2982
-8.000 -0.3279 0.09855 0.09186 -0.0210 1.0000 0.3088
-7.750 -0.3434 0.09701 0.09047 -0.0190 1.0000 0.3193
-7.500 -0.3599 0.09617 0.08977 -0.0160 1.0000 0.3321
-7.250 -0.3435 0.09256 0.08619 -0.0141 1.0000 0.3451
-7.000 -0.3464 0.09035 0.08408 -0.0113 1.0000 0.3574
-6.750 -0.3629 0.08905 0.08292 -0.0074 1.0000 0.3703
-6.500 -0.4039 0.08974 0.08381 -0.0014 1.0000 0.3823
-6.250 -0.4077 0.08773 0.08190 0.0023 1.0000 0.3986
-6.000 -0.4221 0.08639 0.08067 0.0064 1.0000 0.4158
-5.750 -0.3874 0.08252 0.07676 0.0088 1.0000 0.4443
-5.500 -0.4151 0.08214 0.07654 0.0146 1.0000 0.4652
-5.000 -0.4598 0.05374 0.04637 -0.0313 1.0000 0.1679
-4.750 -0.4432 0.05060 0.04303 -0.0313 1.0000 0.1640
-4.500 -0.4247 0.04736 0.03950 -0.0317 1.0000 0.1607
-4.250 -0.4023 0.04382 0.03537 -0.0328 1.0000 0.1552
-4.000 -0.3768 0.04110 0.03174 -0.0335 1.0000 0.1510
-3.750 -0.3542 0.03905 0.02935 -0.0335 1.0000 0.1512
-3.500 -0.3334 0.03745 0.02771 -0.0333 1.0000 0.1548
-3.250 -0.3113 0.03620 0.02626 -0.0331 1.0000 0.1594
-3.000 -0.2876 0.03500 0.02469 -0.0329 1.0000 0.1635
-2.750 -0.2637 0.03388 0.02325 -0.0327 1.0000 0.1680
-2.500 -0.2414 0.03297 0.02234 -0.0324 1.0000 0.1758
-2.250 -0.2184 0.03222 0.02152 -0.0321 1.0000 0.1887
-2.000 -0.1952 0.03150 0.02083 -0.0318 1.0000 0.2083
-1.750 -0.1682 0.03046 0.01997 -0.0318 1.0000 0.2534
-1.500 -0.1358 0.02854 0.01947 -0.0329 1.0000 0.4375
-1.250 -0.1300 0.02670 0.01966 -0.0263 1.0000 1.0000
-1.000 -0.1090 0.02731 0.01968 -0.0265 1.0000 1.0000
-0.750 -0.0614 0.02851 0.02033 -0.0316 0.9893 1.0000
-0.500 -0.0151 0.02969 0.02109 -0.0364 0.9771 1.0000
-0.250 0.0290 0.03078 0.02184 -0.0407 0.9639 1.0000
0.000 0.0718 0.03180 0.02258 -0.0446 0.9498 1.0000
0.250 0.1136 0.03275 0.02329 -0.0482 0.9350 1.0000
0.500 0.1540 0.03365 0.02399 -0.0514 0.9199 1.0000
0.750 0.1925 0.03450 0.02468 -0.0542 0.9048 1.0000
1.000 0.2297 0.03533 0.02535 -0.0566 0.8897 1.0000
1.250 0.2661 0.03612 0.02602 -0.0588 0.8746 1.0000
1.500 0.3021 0.03688 0.02668 -0.0608 0.8594 1.0000
1.750 0.3375 0.03759 0.02731 -0.0625 0.8439 1.0000
2.000 0.3723 0.03826 0.02792 -0.0641 0.8281 1.0000
2.250 0.4063 0.03889 0.02850 -0.0653 0.8121 1.0000
2.500 0.4395 0.03948 0.02906 -0.0663 0.7959 1.0000
2.750 0.4720 0.04004 0.02960 -0.0671 0.7795 1.0000
3.000 0.5035 0.04055 0.03010 -0.0676 0.7627 1.0000
3.250 0.5347 0.04104 0.03060 -0.0680 0.7462 1.0000
3.500 0.5659 0.04146 0.03103 -0.0682 0.7296 1.0000
3.750 0.5971 0.04184 0.03143 -0.0683 0.7134 1.0000
4.000 0.6291 0.04210 0.03173 -0.0683 0.6974 1.0000
4.250 0.6619 0.04224 0.03190 -0.0683 0.6821 1.0000
4.500 0.7224 0.04066 0.03039 -0.0702 0.6713 1.0000
4.750 0.7525 0.04066 0.03045 -0.0695 0.6556 1.0000
5.000 0.7831 0.04055 0.03040 -0.0687 0.6398 1.0000
5.250 0.8148 0.04030 0.03022 -0.0678 0.6240 1.0000
5.500 0.8496 0.03972 0.02969 -0.0670 0.6080 1.0000
5.750 0.8932 0.03830 0.02831 -0.0666 0.5913 1.0000
6.000 0.9267 0.03733 0.02739 -0.0652 0.5713 1.0000
6.250 0.9565 0.03655 0.02662 -0.0635 0.5496 1.0000
6.500 1.0011 0.03480 0.02482 -0.0631 0.5280 1.0000
6.750 1.0295 0.03441 0.02441 -0.0617 0.5064 1.0000
7.000 1.0520 0.03447 0.02448 -0.0599 0.4840 1.0000
7.250 1.0870 0.03384 0.02371 -0.0592 0.4609 1.0000
7.500 1.1022 0.03446 0.02437 -0.0567 0.4365 1.0000
7.750 1.1290 0.03465 0.02439 -0.0554 0.4114 1.0000
8.000 1.1493 0.03532 0.02495 -0.0536 0.3855 1.0000
8.250 1.1670 0.03639 0.02595 -0.0517 0.3611 1.0000
8.500 1.1870 0.03755 0.02699 -0.0502 0.3390 1.0000
8.750 1.2097 0.03895 0.02826 -0.0493 0.3206 1.0000
9.000 1.2242 0.04085 0.03026 -0.0476 0.3064 1.0000
9.250 1.2363 0.04300 0.03260 -0.0458 0.2951 1.0000
9.500 1.2578 0.04481 0.03440 -0.0451 0.2848 1.0000
9.750 1.2638 0.04708 0.03691 -0.0427 0.2761 1.0000
10.000 1.2775 0.04923 0.03916 -0.0413 0.2684 1.0000
10.250 1.2730 0.05219 0.04245 -0.0382 0.2628 1.0000
10.500 1.3038 0.05394 0.04416 -0.0387 0.2562 1.0000
10.750 1.2817 0.05791 0.04853 -0.0344 0.2536 1.0000
11.000 1.2465 0.06253 0.05350 -0.0296 0.2519 1.0000
11.250 1.1937 0.06870 0.05991 -0.0252 0.2520 1.0000
11.500 1.1090 0.08003 0.07138 -0.0245 0.2543 1.0000
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Polar data table (+)
Polar graphs
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