BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 106 AIRFOIL (boe106-il) Reynolds number: 500,000 Max Cl/Cd: 92.04 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe106-il-500000-n5.txt Download as CSV file: xf-boe106-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING 106 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9658 0.05131 0.04813 -0.0704 1.0000 0.0142
-14.750 -0.9970 0.04159 0.03812 -0.0796 1.0000 0.0141
-14.500 -1.0093 0.03721 0.03353 -0.0823 1.0000 0.0143
-14.250 -1.0158 0.03434 0.03047 -0.0824 1.0000 0.0145
-14.000 -1.0187 0.03222 0.02818 -0.0812 1.0000 0.0147
-13.750 -1.0198 0.03057 0.02638 -0.0790 1.0000 0.0150
-13.500 -1.0149 0.02945 0.02520 -0.0768 1.0000 0.0153
-13.250 -1.0057 0.02856 0.02425 -0.0749 1.0000 0.0156
-13.000 -0.9969 0.02782 0.02345 -0.0726 1.0000 0.0160
-12.750 -0.9850 0.02706 0.02262 -0.0708 0.9991 0.0164
-12.500 -0.9586 0.02603 0.02147 -0.0719 0.9949 0.0170
-12.250 -0.9334 0.02491 0.02019 -0.0727 0.9902 0.0177
-12.000 -0.9076 0.02377 0.01885 -0.0736 0.9855 0.0183
-11.750 -0.8813 0.02295 0.01796 -0.0743 0.9801 0.0188
-11.500 -0.8528 0.02238 0.01734 -0.0751 0.9749 0.0194
-11.250 -0.8248 0.02184 0.01673 -0.0758 0.9697 0.0200
-11.000 -0.7979 0.02125 0.01604 -0.0762 0.9631 0.0208
-10.750 -0.7715 0.02057 0.01523 -0.0765 0.9567 0.0216
-10.500 -0.7467 0.01992 0.01441 -0.0763 0.9489 0.0222
-10.250 -0.7227 0.01924 0.01366 -0.0761 0.9415 0.0228
-10.000 -0.6984 0.01880 0.01317 -0.0757 0.9331 0.0233
-9.750 -0.6736 0.01842 0.01273 -0.0754 0.9255 0.0240
-9.500 -0.6494 0.01801 0.01223 -0.0749 0.9170 0.0248
-9.250 -0.6251 0.01757 0.01168 -0.0743 0.9090 0.0255
-9.000 -0.6010 0.01710 0.01108 -0.0737 0.8998 0.0262
-8.750 -0.5765 0.01671 0.01054 -0.0732 0.8901 0.0268
-8.250 -0.5286 0.01571 0.00944 -0.0720 0.8707 0.0283
-8.000 -0.5034 0.01536 0.00901 -0.0716 0.8629 0.0290
-7.750 -0.4780 0.01501 0.00859 -0.0712 0.8546 0.0298
-7.500 -0.4525 0.01466 0.00814 -0.0708 0.8472 0.0307
-7.250 -0.4268 0.01430 0.00769 -0.0704 0.8392 0.0314
-7.000 -0.4010 0.01399 0.00727 -0.0700 0.8319 0.0319
-6.750 -0.3760 0.01349 0.00674 -0.0696 0.8242 0.0328
-6.500 -0.3506 0.01313 0.00632 -0.0691 0.8168 0.0337
-6.250 -0.3245 0.01281 0.00596 -0.0688 0.8095 0.0344
-6.000 -0.2984 0.01252 0.00562 -0.0685 0.8021 0.0352
-5.750 -0.2721 0.01225 0.00529 -0.0682 0.7949 0.0361
-5.500 -0.2457 0.01201 0.00499 -0.0679 0.7873 0.0371
-5.250 -0.2191 0.01178 0.00470 -0.0676 0.7805 0.0380
-5.000 -0.1928 0.01151 0.00437 -0.0672 0.7728 0.0388
-4.750 -0.1668 0.01123 0.00405 -0.0669 0.7657 0.0401
-4.500 -0.1401 0.01100 0.00380 -0.0666 0.7580 0.0415
-4.250 -0.1134 0.01083 0.00357 -0.0663 0.7508 0.0430
-4.000 -0.0864 0.01066 0.00336 -0.0661 0.7428 0.0448
-3.750 -0.0597 0.01051 0.00315 -0.0658 0.7350 0.0469
-3.500 -0.0329 0.01031 0.00295 -0.0656 0.7266 0.0502
-3.250 -0.0061 0.01018 0.00277 -0.0653 0.7182 0.0537
-3.000 0.0206 0.01002 0.00261 -0.0650 0.7077 0.0593
-2.750 0.0470 0.00987 0.00246 -0.0647 0.6961 0.0700
-2.500 0.0730 0.00970 0.00234 -0.0643 0.6843 0.0935
-2.250 0.0996 0.00957 0.00225 -0.0641 0.6732 0.1147
-2.000 0.1264 0.00947 0.00216 -0.0638 0.6632 0.1317
-1.750 0.1531 0.00938 0.00207 -0.0636 0.6533 0.1476
-1.500 0.1797 0.00928 0.00200 -0.0633 0.6423 0.1662
-1.250 0.2054 0.00907 0.00192 -0.0630 0.6316 0.2153
-1.000 0.2301 0.00878 0.00187 -0.0625 0.6212 0.3006
-0.750 0.2552 0.00854 0.00184 -0.0621 0.6105 0.3737
-0.500 0.2792 0.00822 0.00180 -0.0614 0.5999 0.4710
-0.250 0.3009 0.00783 0.00181 -0.0603 0.5892 0.6007
0.000 0.3239 0.00762 0.00185 -0.0592 0.5782 0.6947
0.250 0.3486 0.00753 0.00189 -0.0584 0.5685 0.7460
0.500 0.3732 0.00747 0.00193 -0.0576 0.5592 0.7921
1.000 0.4255 0.00747 0.00207 -0.0564 0.5407 0.8679
1.250 0.4548 0.00754 0.00216 -0.0565 0.5309 0.9034
1.500 0.4873 0.00765 0.00226 -0.0574 0.5216 0.9296
1.750 0.5238 0.00780 0.00237 -0.0591 0.5124 0.9520
2.000 0.5604 0.00793 0.00247 -0.0610 0.5037 0.9693
2.250 0.5998 0.00809 0.00257 -0.0634 0.4949 0.9801
2.500 0.6416 0.00821 0.00266 -0.0665 0.4856 0.9877
2.750 0.6776 0.00835 0.00274 -0.0684 0.4759 0.9926
3.000 0.7112 0.00850 0.00283 -0.0698 0.4625 0.9955
3.500 0.7747 0.00880 0.00300 -0.0719 0.4353 1.0000
3.750 0.7974 0.00894 0.00311 -0.0709 0.4243 1.0000
4.000 0.8196 0.00911 0.00323 -0.0699 0.4128 1.0000
4.500 0.8640 0.00946 0.00349 -0.0678 0.3897 1.0000
4.750 0.8861 0.00964 0.00364 -0.0667 0.3796 1.0000
5.000 0.9075 0.00986 0.00380 -0.0656 0.3679 1.0000
5.250 0.9283 0.01011 0.00399 -0.0643 0.3525 1.0000
5.500 0.9490 0.01038 0.00418 -0.0630 0.3378 1.0000
5.750 0.9703 0.01061 0.00438 -0.0619 0.3251 1.0000
6.000 0.9916 0.01085 0.00459 -0.0607 0.3130 1.0000
6.250 1.0129 0.01111 0.00481 -0.0596 0.3013 1.0000
6.500 1.0341 0.01139 0.00505 -0.0584 0.2891 1.0000
6.750 1.0553 0.01168 0.00530 -0.0573 0.2757 1.0000
7.000 1.0762 0.01200 0.00557 -0.0562 0.2584 1.0000
7.250 1.0946 0.01248 0.00592 -0.0548 0.2299 1.0000
7.500 1.1089 0.01322 0.00642 -0.0527 0.1880 1.0000
7.750 1.1251 0.01386 0.00693 -0.0510 0.1643 1.0000
8.000 1.1434 0.01436 0.00738 -0.0496 0.1512 1.0000
8.250 1.1621 0.01483 0.00782 -0.0483 0.1410 1.0000
8.500 1.1798 0.01532 0.00828 -0.0468 0.1316 1.0000
8.750 1.1977 0.01573 0.00871 -0.0453 0.1237 1.0000
9.000 1.2138 0.01625 0.00920 -0.0437 0.1155 1.0000
9.250 1.2306 0.01674 0.00969 -0.0421 0.1078 1.0000
9.500 1.2465 0.01730 0.01024 -0.0406 0.1006 1.0000
9.750 1.2617 0.01792 0.01085 -0.0390 0.0927 1.0000
10.000 1.2771 0.01855 0.01147 -0.0375 0.0857 1.0000
10.500 1.3062 0.01995 0.01288 -0.0346 0.0747 1.0000
10.750 1.3197 0.02074 0.01368 -0.0331 0.0701 1.0000
11.000 1.3331 0.02157 0.01453 -0.0318 0.0661 1.0000
11.250 1.3467 0.02240 0.01540 -0.0305 0.0625 1.0000
11.500 1.3587 0.02338 0.01639 -0.0291 0.0594 1.0000
11.750 1.3707 0.02438 0.01744 -0.0279 0.0569 1.0000
12.000 1.3836 0.02536 0.01847 -0.0268 0.0543 1.0000
12.250 1.3945 0.02650 0.01965 -0.0257 0.0514 1.0000
12.500 1.4035 0.02783 0.02100 -0.0245 0.0487 1.0000
12.750 1.4147 0.02902 0.02226 -0.0236 0.0469 1.0000
13.000 1.4248 0.03032 0.02362 -0.0226 0.0446 1.0000
13.250 1.4329 0.03183 0.02518 -0.0217 0.0420 1.0000
13.500 1.4405 0.03343 0.02683 -0.0208 0.0396 1.0000
13.750 1.4477 0.03508 0.02854 -0.0201 0.0365 1.0000
14.000 1.4526 0.03700 0.03049 -0.0193 0.0333 1.0000
14.250 1.4564 0.03906 0.03259 -0.0186 0.0291 1.0000
14.500 1.4578 0.04141 0.03496 -0.0179 0.0247 1.0000
14.750 1.4570 0.04407 0.03764 -0.0174 0.0207 1.0000
15.000 1.4557 0.04688 0.04050 -0.0170 0.0180 1.0000
15.250 1.4537 0.04984 0.04352 -0.0168 0.0162 1.0000
15.500 1.4526 0.05280 0.04657 -0.0167 0.0150 1.0000
15.750 1.4509 0.05592 0.04978 -0.0168 0.0141 1.0000
16.000 1.4479 0.05927 0.05321 -0.0169 0.0133 1.0000
16.250 1.4439 0.06280 0.05682 -0.0173 0.0127 1.0000
16.500 1.4419 0.06617 0.06029 -0.0177 0.0122 1.0000
16.750 1.4387 0.06975 0.06398 -0.0182 0.0118 1.0000
17.000 1.4342 0.07354 0.06788 -0.0189 0.0114 1.0000
17.250 1.4286 0.07754 0.07197 -0.0197 0.0110 1.0000
17.500 1.4220 0.08175 0.07628 -0.0207 0.0107 1.0000
17.750 1.4143 0.08620 0.08084 -0.0218 0.0104 1.0000
18.000 1.4052 0.09093 0.08567 -0.0231 0.0102 1.0000
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