BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 103 AIRFOIL (boe103-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.97 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe103-il-1000000-n5.txt Download as CSV file: xf-boe103-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.1259 0.03762 0.03444 -0.0938 1.0000 0.0106
-16.000 -1.1367 0.03384 0.03050 -0.0956 1.0000 0.0107
-15.750 -1.1447 0.03141 0.02795 -0.0950 1.0000 0.0109
-15.500 -1.1535 0.02975 0.02619 -0.0922 1.0000 0.0110
-15.250 -1.1647 0.02860 0.02496 -0.0876 1.0000 0.0111
-15.000 -1.1656 0.02749 0.02376 -0.0841 1.0000 0.0113
-14.750 -1.1627 0.02647 0.02264 -0.0811 1.0000 0.0115
-14.500 -1.1517 0.02542 0.02149 -0.0795 0.9996 0.0117
-14.250 -1.1276 0.02440 0.02039 -0.0801 0.9982 0.0120
-14.000 -1.1016 0.02361 0.01956 -0.0808 0.9968 0.0124
-13.750 -1.0743 0.02291 0.01882 -0.0816 0.9955 0.0128
-13.500 -1.0462 0.02223 0.01809 -0.0825 0.9943 0.0132
-13.250 -1.0203 0.02155 0.01734 -0.0829 0.9925 0.0136
-13.000 -0.9944 0.02084 0.01655 -0.0833 0.9902 0.0140
-12.750 -0.9672 0.02011 0.01572 -0.0839 0.9882 0.0144
-12.500 -0.9387 0.01945 0.01499 -0.0847 0.9865 0.0147
-12.250 -0.9076 0.01905 0.01457 -0.0858 0.9852 0.0152
-12.000 -0.8769 0.01873 0.01425 -0.0867 0.9834 0.0155
-11.750 -0.8494 0.01838 0.01387 -0.0869 0.9790 0.0159
-11.500 -0.8186 0.01796 0.01341 -0.0878 0.9759 0.0163
-11.250 -0.7881 0.01749 0.01287 -0.0887 0.9728 0.0167
-11.000 -0.7631 0.01702 0.01235 -0.0884 0.9661 0.0171
-10.750 -0.7331 0.01654 0.01179 -0.0892 0.9620 0.0175
-10.500 -0.7056 0.01613 0.01130 -0.0893 0.9552 0.0178
-10.250 -0.6762 0.01562 0.01073 -0.0899 0.9488 0.0182
-10.000 -0.6478 0.01522 0.01029 -0.0902 0.9404 0.0186
-9.750 -0.6185 0.01489 0.00992 -0.0906 0.9316 0.0189
-9.500 -0.5908 0.01461 0.00958 -0.0907 0.9214 0.0192
-9.250 -0.5636 0.01435 0.00927 -0.0906 0.9116 0.0195
-8.750 -0.5106 0.01381 0.00858 -0.0902 0.8927 0.0204
-8.500 -0.4846 0.01349 0.00817 -0.0899 0.8839 0.0207
-8.250 -0.4584 0.01320 0.00782 -0.0895 0.8752 0.0211
-8.000 -0.4321 0.01295 0.00748 -0.0892 0.8670 0.0215
-7.750 -0.4056 0.01270 0.00716 -0.0890 0.8586 0.0217
-7.500 -0.3792 0.01244 0.00683 -0.0886 0.8507 0.0219
-7.250 -0.3544 0.01189 0.00622 -0.0882 0.8423 0.0224
-7.000 -0.3285 0.01156 0.00585 -0.0878 0.8344 0.0228
-6.750 -0.3020 0.01129 0.00553 -0.0875 0.8263 0.0232
-6.500 -0.2756 0.01104 0.00522 -0.0872 0.8182 0.0235
-6.250 -0.2489 0.01079 0.00493 -0.0869 0.8096 0.0238
-6.000 -0.2223 0.01057 0.00466 -0.0866 0.8016 0.0242
-5.750 -0.1954 0.01036 0.00441 -0.0864 0.7930 0.0247
-5.500 -0.1687 0.01015 0.00415 -0.0861 0.7843 0.0250
-5.250 -0.1418 0.00994 0.00389 -0.0858 0.7750 0.0254
-5.000 -0.1150 0.00975 0.00365 -0.0855 0.7665 0.0257
-4.750 -0.0881 0.00958 0.00342 -0.0852 0.7568 0.0260
-4.500 -0.0610 0.00942 0.00322 -0.0850 0.7471 0.0262
-4.250 -0.0342 0.00930 0.00303 -0.0846 0.7357 0.0265
-4.000 -0.0075 0.00919 0.00286 -0.0843 0.7222 0.0266
-3.750 0.0187 0.00900 0.00260 -0.0839 0.7072 0.0273
-3.500 0.0452 0.00887 0.00241 -0.0835 0.6925 0.0281
-3.250 0.0719 0.00878 0.00226 -0.0832 0.6783 0.0287
-3.000 0.0988 0.00871 0.00213 -0.0829 0.6647 0.0293
-2.750 0.1255 0.00866 0.00202 -0.0825 0.6497 0.0299
-2.500 0.1524 0.00862 0.00191 -0.0822 0.6362 0.0304
-2.000 0.2070 0.00853 0.00175 -0.0818 0.6154 0.0318
-1.750 0.2343 0.00850 0.00168 -0.0816 0.6060 0.0325
-1.500 0.2619 0.00845 0.00161 -0.0815 0.5976 0.0348
-1.250 0.2892 0.00841 0.00156 -0.0813 0.5889 0.0380
-1.000 0.3157 0.00820 0.00149 -0.0810 0.5787 0.0864
-0.750 0.3423 0.00811 0.00147 -0.0807 0.5661 0.1211
-0.500 0.3691 0.00807 0.00146 -0.0805 0.5527 0.1469
-0.250 0.3959 0.00806 0.00146 -0.0803 0.5402 0.1683
0.000 0.4228 0.00802 0.00147 -0.0801 0.5277 0.1960
0.250 0.4492 0.00795 0.00147 -0.0798 0.5125 0.2409
0.500 0.4739 0.00767 0.00149 -0.0794 0.4958 0.3691
0.750 0.4990 0.00748 0.00154 -0.0789 0.4796 0.4739
1.000 0.5236 0.00733 0.00161 -0.0784 0.4613 0.5750
1.250 0.5476 0.00729 0.00171 -0.0777 0.4333 0.6608
1.500 0.5705 0.00747 0.00185 -0.0767 0.3900 0.7148
1.750 0.5925 0.00760 0.00201 -0.0756 0.3529 0.7832
2.000 0.6135 0.00762 0.00219 -0.0740 0.3279 0.8700
2.250 0.6366 0.00775 0.00234 -0.0728 0.3095 0.9174
2.500 0.6633 0.00795 0.00248 -0.0725 0.2896 0.9537
2.750 0.6974 0.00818 0.00263 -0.0739 0.2718 0.9763
3.000 0.7325 0.00844 0.00277 -0.0756 0.2534 0.9887
3.250 0.7648 0.00869 0.00292 -0.0768 0.2341 0.9951
3.500 0.7972 0.00896 0.00308 -0.0780 0.2144 0.9991
3.750 0.8205 0.00925 0.00324 -0.0772 0.1949 1.0000
4.000 0.8415 0.00955 0.00343 -0.0759 0.1746 1.0000
4.250 0.8629 0.00987 0.00363 -0.0747 0.1546 1.0000
4.500 0.8844 0.01021 0.00386 -0.0735 0.1354 1.0000
4.750 0.9065 0.01054 0.00410 -0.0725 0.1184 1.0000
5.000 0.9293 0.01085 0.00432 -0.0716 0.1057 1.0000
5.250 0.9528 0.01112 0.00454 -0.0709 0.0981 1.0000
5.500 0.9767 0.01136 0.00475 -0.0702 0.0926 1.0000
5.750 1.0007 0.01160 0.00496 -0.0696 0.0888 1.0000
6.000 1.0247 0.01184 0.00517 -0.0690 0.0860 1.0000
6.250 1.0488 0.01208 0.00540 -0.0684 0.0833 1.0000
6.500 1.0732 0.01229 0.00561 -0.0678 0.0820 1.0000
6.750 1.0975 0.01250 0.00582 -0.0673 0.0810 1.0000
7.000 1.1215 0.01272 0.00606 -0.0667 0.0797 1.0000
7.250 1.1452 0.01296 0.00630 -0.0661 0.0784 1.0000
7.500 1.1682 0.01324 0.00657 -0.0654 0.0760 1.0000
7.750 1.1903 0.01357 0.00687 -0.0645 0.0722 1.0000
8.000 1.2131 0.01384 0.00715 -0.0638 0.0704 1.0000
8.250 1.2359 0.01410 0.00742 -0.0630 0.0688 1.0000
8.500 1.2569 0.01442 0.00772 -0.0620 0.0645 1.0000
8.750 1.2756 0.01482 0.00809 -0.0606 0.0578 1.0000
9.000 1.2872 0.01563 0.00873 -0.0581 0.0386 1.0000
9.250 1.3050 0.01609 0.00919 -0.0566 0.0358 1.0000
9.500 1.3227 0.01657 0.00966 -0.0551 0.0336 1.0000
9.750 1.3409 0.01701 0.01013 -0.0538 0.0320 1.0000
10.000 1.3589 0.01746 0.01060 -0.0525 0.0311 1.0000
10.250 1.3759 0.01798 0.01114 -0.0510 0.0298 1.0000
10.500 1.3917 0.01857 0.01174 -0.0495 0.0282 1.0000
10.750 1.4073 0.01919 0.01239 -0.0480 0.0266 1.0000
11.000 1.4245 0.01971 0.01294 -0.0468 0.0258 1.0000
11.500 1.4437 0.02178 0.01499 -0.0426 0.0118 1.0000
11.750 1.4565 0.02265 0.01591 -0.0411 0.0107 1.0000
12.000 1.4687 0.02358 0.01690 -0.0396 0.0098 1.0000
12.250 1.4797 0.02462 0.01799 -0.0381 0.0091 1.0000
12.500 1.4923 0.02558 0.01900 -0.0369 0.0087 1.0000
12.750 1.5037 0.02665 0.02012 -0.0356 0.0083 1.0000
13.000 1.5141 0.02782 0.02135 -0.0343 0.0079 1.0000
13.250 1.5234 0.02911 0.02271 -0.0331 0.0076 1.0000
13.500 1.5314 0.03056 0.02421 -0.0319 0.0072 1.0000
13.750 1.5402 0.03196 0.02567 -0.0308 0.0070 1.0000
14.000 1.5484 0.03345 0.02723 -0.0298 0.0068 1.0000
14.250 1.5557 0.03507 0.02892 -0.0289 0.0066 1.0000
14.500 1.5619 0.03683 0.03075 -0.0280 0.0064 1.0000
14.750 1.5669 0.03874 0.03272 -0.0272 0.0062 1.0000
15.000 1.5709 0.04082 0.03488 -0.0265 0.0060 1.0000
15.250 1.5736 0.04311 0.03724 -0.0260 0.0058 1.0000
15.500 1.5745 0.04564 0.03985 -0.0255 0.0056 1.0000
15.750 1.5755 0.04825 0.04255 -0.0252 0.0055 1.0000
16.000 1.5768 0.05090 0.04528 -0.0250 0.0054 1.0000
16.250 1.5769 0.05377 0.04824 -0.0250 0.0053 1.0000
16.500 1.5757 0.05686 0.05143 -0.0251 0.0052 1.0000
16.750 1.5732 0.06017 0.05482 -0.0254 0.0051 1.0000
17.000 1.5697 0.06368 0.05844 -0.0258 0.0050 1.0000
17.250 1.5650 0.06745 0.06230 -0.0264 0.0049 1.0000
17.500 1.5588 0.07148 0.06644 -0.0271 0.0048 1.0000
17.750 1.5512 0.07579 0.07084 -0.0280 0.0047 1.0000
18.000 1.5419 0.08043 0.07559 -0.0292 0.0047 1.0000
18.250 1.5318 0.08528 0.08056 -0.0305 0.0046 1.0000
18.500 1.5193 0.09059 0.08598 -0.0321 0.0046 1.0000
18.750 1.5059 0.09612 0.09162 -0.0339 0.0045 1.0000
19.000 1.4911 0.10201 0.09764 -0.0360 0.0045 1.0000
19.250 1.4753 0.10815 0.10389 -0.0383 0.0045 1.0000
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