BOEING 106 AIRFOIL (boe106-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING 106 AIRFOIL (boe106-il) Reynolds number: 200,000 Max Cl/Cd: 70.24 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-boe106-il-200000-n5.txt Download as CSV file: xf-boe106-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6377 0.05204 0.04802 -0.0750 1.0000 0.0266
-11.000 -0.6734 0.04781 0.04362 -0.0738 1.0000 0.0265
-10.750 -0.7093 0.04498 0.04061 -0.0684 1.0000 0.0266
-10.500 -0.7145 0.04147 0.03680 -0.0681 0.9947 0.0271
-10.250 -0.6903 0.04020 0.03547 -0.0697 0.9890 0.0276
-10.000 -0.6672 0.03819 0.03328 -0.0718 0.9839 0.0284
-9.750 -0.6485 0.03573 0.03053 -0.0730 0.9765 0.0293
-9.500 -0.6296 0.03288 0.02723 -0.0741 0.9701 0.0307
-9.250 -0.6121 0.03003 0.02372 -0.0744 0.9623 0.0321
-9.000 -0.5857 0.02864 0.02227 -0.0753 0.9570 0.0329
-8.750 -0.5607 0.02761 0.02113 -0.0756 0.9499 0.0338
-8.500 -0.5323 0.02654 0.01989 -0.0765 0.9450 0.0350
-8.250 -0.5094 0.02541 0.01853 -0.0762 0.9366 0.0364
-8.000 -0.4828 0.02414 0.01695 -0.0764 0.9303 0.0376
-7.750 -0.4587 0.02306 0.01560 -0.0760 0.9219 0.0386
-7.500 -0.4326 0.02203 0.01454 -0.0761 0.9147 0.0397
-7.250 -0.4076 0.02132 0.01376 -0.0757 0.9064 0.0409
-7.000 -0.3817 0.02055 0.01287 -0.0755 0.8988 0.0421
-6.750 -0.3566 0.01979 0.01198 -0.0750 0.8913 0.0432
-6.500 -0.3311 0.01912 0.01117 -0.0746 0.8837 0.0445
-6.250 -0.3052 0.01856 0.01046 -0.0741 0.8765 0.0458
-6.000 -0.2809 0.01776 0.00963 -0.0735 0.8686 0.0471
-5.750 -0.2556 0.01714 0.00897 -0.0731 0.8618 0.0483
-5.500 -0.2309 0.01663 0.00842 -0.0725 0.8536 0.0497
-5.250 -0.2052 0.01615 0.00787 -0.0720 0.8470 0.0513
-5.000 -0.1802 0.01575 0.00740 -0.0714 0.8386 0.0533
-4.500 -0.1300 0.01487 0.00643 -0.0703 0.8235 0.0579
-4.250 -0.1041 0.01450 0.00601 -0.0698 0.8166 0.0607
-4.000 -0.0788 0.01420 0.00566 -0.0693 0.8082 0.0641
-3.750 -0.0529 0.01386 0.00530 -0.0688 0.8010 0.0692
-3.500 -0.0274 0.01359 0.00503 -0.0684 0.7926 0.0776
-3.250 -0.0014 0.01329 0.00478 -0.0679 0.7851 0.0928
-3.000 0.0243 0.01305 0.00459 -0.0675 0.7766 0.1144
-2.750 0.0505 0.01283 0.00436 -0.0671 0.7687 0.1364
-2.500 0.0761 0.01258 0.00419 -0.0667 0.7597 0.1607
-2.250 0.1016 0.01229 0.00399 -0.0662 0.7516 0.1950
-2.000 0.1256 0.01190 0.00387 -0.0656 0.7415 0.2668
-1.750 0.1491 0.01149 0.00374 -0.0648 0.7319 0.3571
-1.500 0.1707 0.01098 0.00363 -0.0636 0.7213 0.4710
-1.250 0.1897 0.01043 0.00364 -0.0617 0.7107 0.6212
-1.000 0.2121 0.01016 0.00366 -0.0600 0.7010 0.7255
-0.750 0.2377 0.01004 0.00369 -0.0590 0.6905 0.7885
-0.500 0.2671 0.01002 0.00372 -0.0588 0.6806 0.8361
0.000 0.3363 0.01015 0.00378 -0.0608 0.6599 0.9107
0.250 0.3736 0.01025 0.00380 -0.0625 0.6491 0.9335
0.500 0.4106 0.01035 0.00380 -0.0641 0.6385 0.9529
0.750 0.4491 0.01046 0.00383 -0.0663 0.6272 0.9698
1.000 0.4910 0.01055 0.00383 -0.0692 0.6158 0.9818
1.250 0.5374 0.01063 0.00381 -0.0732 0.6041 0.9934
1.500 0.5778 0.01070 0.00378 -0.0760 0.5925 1.0000
1.750 0.6009 0.01079 0.00381 -0.0752 0.5821 1.0000
2.000 0.6240 0.01090 0.00385 -0.0743 0.5725 1.0000
2.250 0.6470 0.01102 0.00390 -0.0735 0.5623 1.0000
2.500 0.6699 0.01115 0.00398 -0.0726 0.5522 1.0000
2.750 0.6927 0.01130 0.00406 -0.0717 0.5427 1.0000
3.000 0.7157 0.01145 0.00418 -0.0708 0.5328 1.0000
3.250 0.7386 0.01161 0.00430 -0.0698 0.5241 1.0000
3.500 0.7614 0.01178 0.00443 -0.0689 0.5151 1.0000
3.750 0.7843 0.01196 0.00459 -0.0680 0.5061 1.0000
4.250 0.8284 0.01235 0.00489 -0.0658 0.4831 1.0000
4.500 0.8503 0.01255 0.00507 -0.0647 0.4711 1.0000
4.750 0.8720 0.01277 0.00525 -0.0636 0.4600 1.0000
5.000 0.8936 0.01300 0.00544 -0.0625 0.4487 1.0000
5.250 0.9156 0.01321 0.00567 -0.0614 0.4375 1.0000
5.500 0.9373 0.01345 0.00589 -0.0603 0.4264 1.0000
5.750 0.9586 0.01371 0.00612 -0.0592 0.4149 1.0000
6.000 0.9801 0.01397 0.00637 -0.0581 0.4031 1.0000
6.250 1.0009 0.01425 0.00663 -0.0569 0.3892 1.0000
6.500 1.0211 0.01457 0.00691 -0.0556 0.3739 1.0000
6.750 1.0412 0.01490 0.00721 -0.0543 0.3592 1.0000
7.000 1.0614 0.01524 0.00754 -0.0531 0.3458 1.0000
7.250 1.0814 0.01560 0.00789 -0.0519 0.3331 1.0000
7.500 1.1008 0.01598 0.00827 -0.0506 0.3195 1.0000
7.750 1.1196 0.01640 0.00868 -0.0492 0.3041 1.0000
8.000 1.1377 0.01684 0.00910 -0.0478 0.2864 1.0000
8.250 1.1545 0.01734 0.00957 -0.0462 0.2655 1.0000
8.500 1.1689 0.01795 0.01010 -0.0442 0.2390 1.0000
8.750 1.1778 0.01876 0.01075 -0.0415 0.2060 1.0000
9.000 1.1847 0.01971 0.01156 -0.0387 0.1805 1.0000
9.250 1.1934 0.02066 0.01243 -0.0362 0.1641 1.0000
9.500 1.2037 0.02158 0.01332 -0.0341 0.1520 1.0000
9.750 1.2140 0.02253 0.01427 -0.0322 0.1425 1.0000
10.000 1.2248 0.02348 0.01524 -0.0304 0.1338 1.0000
10.250 1.2358 0.02447 0.01628 -0.0287 0.1266 1.0000
10.500 1.2456 0.02556 0.01740 -0.0271 0.1194 1.0000
10.750 1.2554 0.02669 0.01858 -0.0255 0.1133 1.0000
11.000 1.2650 0.02789 0.01982 -0.0241 0.1073 1.0000
11.250 1.2722 0.02929 0.02124 -0.0226 0.1025 1.0000
11.500 1.2823 0.03053 0.02259 -0.0214 0.0977 1.0000
11.750 1.2895 0.03203 0.02412 -0.0202 0.0931 1.0000
12.000 1.2959 0.03365 0.02578 -0.0191 0.0892 1.0000
12.250 1.3047 0.03512 0.02734 -0.0182 0.0847 1.0000
12.500 1.3099 0.03692 0.02917 -0.0172 0.0805 1.0000
12.750 1.3157 0.03873 0.03104 -0.0164 0.0770 1.0000
13.000 1.3228 0.04047 0.03289 -0.0157 0.0732 1.0000
13.250 1.3269 0.04252 0.03499 -0.0151 0.0700 1.0000
13.500 1.3291 0.04479 0.03731 -0.0145 0.0671 1.0000
13.750 1.3355 0.04671 0.03936 -0.0140 0.0642 1.0000
14.000 1.3394 0.04894 0.04168 -0.0137 0.0616 1.0000
14.250 1.3409 0.05148 0.04428 -0.0135 0.0592 1.0000
14.500 1.3413 0.05422 0.04708 -0.0134 0.0570 1.0000
14.750 1.3461 0.05653 0.04955 -0.0133 0.0545 1.0000
15.000 1.3482 0.05919 0.05233 -0.0134 0.0519 1.0000
15.250 1.3475 0.06227 0.05547 -0.0136 0.0496 1.0000
15.500 1.3471 0.06538 0.05867 -0.0140 0.0474 1.0000
15.750 1.3491 0.06823 0.06167 -0.0143 0.0445 1.0000
16.000 1.3474 0.07164 0.06515 -0.0149 0.0419 1.0000
16.250 1.3453 0.07513 0.06874 -0.0156 0.0393 1.0000
16.500 1.3437 0.07863 0.07235 -0.0163 0.0362 1.0000
16.750 1.3384 0.08273 0.07653 -0.0174 0.0339 1.0000
17.000 1.3353 0.08654 0.08047 -0.0183 0.0310 1.0000
17.250 1.3283 0.09098 0.08499 -0.0196 0.0289 1.0000
17.500 1.3221 0.09539 0.08951 -0.0209 0.0270 1.0000
17.750 1.3144 0.10011 0.09432 -0.0225 0.0253 1.0000
18.000 1.3048 0.10523 0.09953 -0.0244 0.0240 1.0000
18.250 1.2961 0.11025 0.10466 -0.0262 0.0229 1.0000
18.500 1.2872 0.11539 0.10992 -0.0283 0.0219 1.0000
18.750 1.2772 0.12083 0.11548 -0.0306 0.0210 1.0000
19.000 1.2664 0.12655 0.12130 -0.0332 0.0203 1.0000
19.250 1.2545 0.13255 0.12739 -0.0361 0.0198 1.0000
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