BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 100,000 Max Cl/Cd: 52.05 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe103-il-100000-n5.txt Download as CSV file: xf-boe103-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3858 0.09270 0.08757 -0.0457 1.0000 0.0446
-9.500 -0.3950 0.08856 0.08350 -0.0465 1.0000 0.0443
-9.250 -0.4082 0.08434 0.07937 -0.0471 1.0000 0.0439
-9.000 -0.4275 0.08014 0.07528 -0.0473 1.0000 0.0434
-8.750 -0.4576 0.07613 0.07140 -0.0468 1.0000 0.0429
-8.500 -0.4945 0.07090 0.06624 -0.0470 1.0000 0.0423
-8.250 -0.5166 0.05999 0.05504 -0.0544 0.9937 0.0415
-8.000 -0.5119 0.05163 0.04618 -0.0605 0.9849 0.0418
-7.750 -0.4981 0.04656 0.04067 -0.0634 0.9768 0.0430
-7.500 -0.4816 0.04168 0.03521 -0.0656 0.9695 0.0441
-7.250 -0.4601 0.03752 0.03043 -0.0673 0.9631 0.0448
-7.000 -0.4374 0.03441 0.02675 -0.0680 0.9563 0.0455
-6.750 -0.4097 0.03193 0.02367 -0.0691 0.9506 0.0470
-6.500 -0.3796 0.03024 0.02186 -0.0704 0.9457 0.0483
-6.250 -0.3521 0.02876 0.02017 -0.0708 0.9389 0.0492
-6.000 -0.3183 0.02726 0.01844 -0.0723 0.9348 0.0502
-5.750 -0.2889 0.02602 0.01700 -0.0728 0.9286 0.0513
-5.500 -0.2576 0.02496 0.01575 -0.0736 0.9227 0.0533
-5.250 -0.2214 0.02391 0.01448 -0.0752 0.9190 0.0552
-5.000 -0.1927 0.02295 0.01348 -0.0755 0.9122 0.0565
-4.750 -0.1615 0.02211 0.01264 -0.0762 0.9062 0.0580
-4.500 -0.1263 0.02131 0.01180 -0.0776 0.9021 0.0600
-4.250 -0.1002 0.02074 0.01117 -0.0773 0.8936 0.0623
-4.000 -0.0675 0.02011 0.01049 -0.0781 0.8880 0.0661
-3.750 -0.0375 0.01957 0.00996 -0.0785 0.8814 0.0713
-3.500 -0.0087 0.01908 0.00943 -0.0786 0.8736 0.0777
-3.250 0.0252 0.01846 0.00888 -0.0796 0.8687 0.0915
-3.000 0.0496 0.01806 0.00860 -0.0789 0.8590 0.1193
-2.750 0.0821 0.01758 0.00823 -0.0797 0.8532 0.1615
-2.500 0.1075 0.01726 0.00804 -0.0793 0.8438 0.2014
-2.250 0.1377 0.01667 0.00773 -0.0798 0.8373 0.2651
-2.000 0.1616 0.01607 0.00763 -0.0792 0.8281 0.3827
-1.750 0.1880 0.01538 0.00755 -0.0786 0.8211 0.5521
-1.500 0.2095 0.01500 0.00764 -0.0765 0.8120 0.6895
-1.250 0.2378 0.01472 0.00764 -0.0752 0.8049 0.7961
-1.000 0.2721 0.01467 0.00763 -0.0755 0.7959 0.8672
-0.750 0.3179 0.01453 0.00738 -0.0781 0.7869 0.9224
-0.500 0.3670 0.01446 0.00717 -0.0819 0.7734 0.9668
-0.250 0.4244 0.01434 0.00690 -0.0877 0.7604 0.9969
0.000 0.4522 0.01433 0.00674 -0.0877 0.7496 1.0000
0.250 0.4760 0.01434 0.00662 -0.0868 0.7389 1.0000
0.500 0.4978 0.01441 0.00659 -0.0857 0.7270 1.0000
0.750 0.5213 0.01447 0.00654 -0.0847 0.7162 1.0000
1.000 0.5462 0.01451 0.00646 -0.0840 0.7057 1.0000
1.250 0.5683 0.01462 0.00650 -0.0828 0.6935 1.0000
1.500 0.5919 0.01473 0.00652 -0.0819 0.6821 1.0000
1.750 0.6168 0.01482 0.00651 -0.0811 0.6710 1.0000
2.000 0.6404 0.01494 0.00656 -0.0802 0.6589 1.0000
2.250 0.6637 0.01509 0.00665 -0.0792 0.6464 1.0000
2.500 0.6878 0.01523 0.00673 -0.0783 0.6340 1.0000
2.750 0.7122 0.01538 0.00679 -0.0775 0.6215 1.0000
3.000 0.7364 0.01554 0.00689 -0.0766 0.6084 1.0000
3.250 0.7594 0.01573 0.00704 -0.0756 0.5938 1.0000
3.500 0.7824 0.01592 0.00717 -0.0745 0.5782 1.0000
3.750 0.8052 0.01611 0.00730 -0.0734 0.5611 1.0000
4.000 0.8275 0.01632 0.00744 -0.0722 0.5427 1.0000
4.250 0.8485 0.01656 0.00762 -0.0708 0.5213 1.0000
4.500 0.8691 0.01681 0.00777 -0.0693 0.4977 1.0000
4.750 0.8889 0.01711 0.00796 -0.0678 0.4716 1.0000
5.000 0.9083 0.01745 0.00816 -0.0662 0.4455 1.0000
5.250 0.9279 0.01783 0.00844 -0.0647 0.4207 1.0000
5.500 0.9476 0.01825 0.00875 -0.0633 0.4000 1.0000
5.750 0.9674 0.01869 0.00910 -0.0619 0.3817 1.0000
6.000 0.9871 0.01915 0.00949 -0.0606 0.3648 1.0000
6.250 1.0065 0.01963 0.00992 -0.0592 0.3491 1.0000
6.750 1.0444 0.02066 0.01088 -0.0565 0.3191 1.0000
7.000 1.0628 0.02119 0.01141 -0.0551 0.3044 1.0000
7.250 1.0806 0.02175 0.01197 -0.0536 0.2894 1.0000
7.500 1.0975 0.02234 0.01255 -0.0520 0.2737 1.0000
7.750 1.1133 0.02297 0.01317 -0.0503 0.2573 1.0000
8.000 1.1274 0.02363 0.01381 -0.0483 0.2404 1.0000
8.250 1.1398 0.02436 0.01451 -0.0461 0.2239 1.0000
8.500 1.1517 0.02516 0.01527 -0.0439 0.2083 1.0000
8.750 1.1634 0.02602 0.01610 -0.0419 0.1944 1.0000
9.000 1.1753 0.02693 0.01700 -0.0399 0.1829 1.0000
9.250 1.1865 0.02792 0.01797 -0.0379 0.1738 1.0000
9.500 1.1972 0.02896 0.01902 -0.0360 0.1663 1.0000
9.750 1.2085 0.03002 0.02010 -0.0343 0.1601 1.0000
10.000 1.2201 0.03109 0.02122 -0.0326 0.1544 1.0000
10.250 1.2293 0.03232 0.02242 -0.0309 0.1498 1.0000
10.500 1.2417 0.03342 0.02361 -0.0295 0.1449 1.0000
10.750 1.2527 0.03460 0.02488 -0.0281 0.1403 1.0000
11.000 1.2618 0.03592 0.02620 -0.0266 0.1364 1.0000
11.250 1.2727 0.03719 0.02754 -0.0253 0.1328 1.0000
11.500 1.2838 0.03846 0.02893 -0.0241 0.1291 1.0000
11.750 1.2933 0.03984 0.03039 -0.0229 0.1257 1.0000
12.000 1.3017 0.04131 0.03190 -0.0217 0.1227 1.0000
12.250 1.3111 0.04280 0.03347 -0.0206 0.1197 1.0000
12.500 1.3195 0.04435 0.03519 -0.0196 0.1164 1.0000
12.750 1.3262 0.04603 0.03698 -0.0187 0.1132 1.0000
13.000 1.3311 0.04785 0.03885 -0.0178 0.1100 1.0000
13.250 1.3357 0.04977 0.04086 -0.0170 0.1069 1.0000
13.500 1.3391 0.05189 0.04319 -0.0164 0.1036 1.0000
13.750 1.3414 0.05412 0.04555 -0.0159 0.1004 1.0000
14.000 1.3433 0.05642 0.04795 -0.0155 0.0978 1.0000
14.250 1.3461 0.05867 0.05021 -0.0150 0.0956 1.0000
14.500 1.3476 0.06123 0.05298 -0.0148 0.0935 1.0000
14.750 1.3479 0.06401 0.05598 -0.0148 0.0912 1.0000
15.000 1.3471 0.06695 0.05910 -0.0150 0.0890 1.0000
15.250 1.3454 0.07006 0.06238 -0.0153 0.0869 1.0000
15.500 1.3427 0.07337 0.06579 -0.0159 0.0849 1.0000
15.750 1.3406 0.07661 0.06907 -0.0165 0.0829 1.0000
16.000 1.3351 0.08060 0.07328 -0.0175 0.0811 1.0000
16.250 1.3279 0.08499 0.07792 -0.0188 0.0792 1.0000
16.500 1.3202 0.08957 0.08271 -0.0203 0.0775 1.0000
16.750 1.3116 0.09439 0.08773 -0.0221 0.0758 1.0000
17.000 1.3025 0.09940 0.09290 -0.0241 0.0743 1.0000
17.250 1.2932 0.10454 0.09818 -0.0263 0.0729 1.0000
17.500 1.2850 0.10958 0.10333 -0.0286 0.0715 1.0000
17.750 1.2721 0.11567 0.10958 -0.0316 0.0703 1.0000
18.000 1.2492 0.12402 0.11819 -0.0359 0.0692 1.0000
18.250 1.2178 0.13444 0.12885 -0.0416 0.0684 1.0000
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