XFOIL Version 6.96 Calculated polar for: B-29 TIP 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.4151 0.08708 0.08278 -0.0075 1.0000 0.1017 -8.250 -0.4168 0.08329 0.07903 -0.0091 1.0000 0.1063 -7.750 -0.5088 0.08357 0.07914 -0.0119 1.0000 0.1010 -7.500 -0.5075 0.08015 0.07572 -0.0136 1.0000 0.1055 -7.250 -0.4344 0.06670 0.06265 -0.0161 1.0000 0.1176 -7.000 -0.4449 0.06247 0.05843 -0.0194 1.0000 0.1223 -6.750 -0.4574 0.05717 0.05304 -0.0232 1.0000 0.1260 -6.500 -0.4394 0.05364 0.04962 -0.0210 1.0000 0.1306 -6.250 -0.4485 0.04908 0.04482 -0.0247 1.0000 0.1400 -6.000 -0.4312 0.04541 0.04132 -0.0229 1.0000 0.1444 -5.750 -0.4629 0.05519 0.05053 -0.0216 1.0000 0.1485 -5.500 -0.4540 0.05209 0.04737 -0.0213 1.0000 0.1587 -5.250 -0.4498 0.04977 0.04497 -0.0201 1.0000 0.1712 -5.000 -0.4523 0.04824 0.04353 -0.0164 1.0000 0.1768 -4.750 -0.4649 0.04709 0.04230 -0.0123 1.0000 0.1861 -4.250 -0.3731 0.03397 0.02709 -0.0207 0.9766 0.0979 -4.000 -0.3278 0.03010 0.02238 -0.0229 0.9674 0.0807 -3.750 -0.2851 0.02674 0.01865 -0.0259 0.9583 0.0779 -3.500 -0.2429 0.02415 0.01559 -0.0281 0.9483 0.0751 -3.250 -0.1988 0.02211 0.01315 -0.0306 0.9388 0.0754 -3.000 -0.1574 0.02055 0.01136 -0.0326 0.9282 0.0785 -2.750 -0.1223 0.01925 0.01004 -0.0337 0.9157 0.0874 -2.500 -0.0907 0.01815 0.00892 -0.0339 0.9029 0.0977 -2.250 0.0796 0.01316 0.00711 -0.0578 0.9201 1.0000 -2.000 0.1067 0.01321 0.00683 -0.0577 0.9006 1.0000 -1.750 0.1288 0.01332 0.00669 -0.0566 0.8830 1.0000 -1.500 0.1496 0.01345 0.00663 -0.0553 0.8665 1.0000 -1.250 0.1707 0.01359 0.00658 -0.0540 0.8517 1.0000 -1.000 0.1913 0.01374 0.00655 -0.0525 0.8383 1.0000 -0.750 0.2119 0.01389 0.00653 -0.0511 0.8261 1.0000 -0.500 0.2334 0.01405 0.00657 -0.0499 0.8137 1.0000 -0.250 0.2553 0.01423 0.00664 -0.0489 0.8019 1.0000 0.000 0.2773 0.01442 0.00673 -0.0478 0.7909 1.0000 0.250 0.2990 0.01460 0.00680 -0.0465 0.7813 1.0000 0.500 0.3214 0.01480 0.00693 -0.0455 0.7709 1.0000 0.750 0.3441 0.01504 0.00712 -0.0447 0.7606 1.0000 1.000 0.3664 0.01525 0.00726 -0.0435 0.7520 1.0000 1.250 0.3893 0.01550 0.00748 -0.0427 0.7423 1.0000 1.500 0.4122 0.01578 0.00774 -0.0419 0.7329 1.0000 1.750 0.4347 0.01599 0.00789 -0.0406 0.7253 1.0000 2.000 0.4580 0.01633 0.00828 -0.0401 0.7153 1.0000 2.250 0.4810 0.01662 0.00856 -0.0391 0.7072 1.0000 2.500 0.5040 0.01691 0.00887 -0.0383 0.6985 1.0000 2.750 0.5271 0.01728 0.00930 -0.0376 0.6897 1.0000 3.000 0.5501 0.01753 0.00957 -0.0365 0.6823 1.0000 3.250 0.5731 0.01798 0.01011 -0.0359 0.6728 1.0000 3.500 0.5963 0.01822 0.01037 -0.0347 0.6661 1.0000 3.750 0.6190 0.01870 0.01096 -0.0341 0.6562 1.0000 4.000 0.6418 0.01910 0.01148 -0.0333 0.6478 1.0000 4.250 0.6650 0.01939 0.01184 -0.0322 0.6395 1.0000 4.500 0.6872 0.01983 0.01242 -0.0313 0.6292 1.0000 4.750 0.7094 0.01979 0.01245 -0.0296 0.6161 1.0000 5.000 0.7317 0.01927 0.01196 -0.0271 0.5985 1.0000 5.250 0.7546 0.01869 0.01134 -0.0246 0.5807 1.0000 5.500 0.7770 0.01846 0.01119 -0.0228 0.5634 1.0000 5.750 0.7993 0.01834 0.01120 -0.0212 0.5456 1.0000 6.000 0.8220 0.01799 0.01097 -0.0193 0.5250 1.0000 6.250 0.8429 0.01735 0.01036 -0.0168 0.4921 1.0000 6.500 0.8603 0.01682 0.00986 -0.0140 0.4289 1.0000 6.750 0.8624 0.01825 0.01010 -0.0100 0.2147 1.0000 7.000 0.8569 0.02168 0.01250 -0.0061 0.1104 1.0000 7.250 0.8626 0.02373 0.01434 -0.0030 0.0832 1.0000 7.500 0.8731 0.02541 0.01592 -0.0005 0.0711 1.0000 7.750 0.8875 0.02720 0.01758 0.0017 0.0638 1.0000 8.000 0.9087 0.02913 0.01956 0.0032 0.0593 1.0000 8.250 0.9291 0.03077 0.02128 0.0044 0.0542 1.0000 8.500 0.9542 0.03405 0.02444 0.0048 0.0506 1.0000 8.750 0.9755 0.03644 0.02712 0.0060 0.0498 1.0000 9.000 0.9939 0.03920 0.03029 0.0075 0.0493 1.0000 9.250 1.0093 0.04241 0.03386 0.0091 0.0493 1.0000 9.500 1.0213 0.04610 0.03790 0.0107 0.0497 1.0000 9.750 1.0295 0.04983 0.04199 0.0125 0.0499 1.0000 10.000 1.0321 0.05293 0.04549 0.0147 0.0496 1.0000 10.250 1.0324 0.05670 0.04959 0.0166 0.0497 1.0000 10.500 1.0310 0.06099 0.05413 0.0182 0.0501 1.0000 10.750 1.0319 0.06317 0.05667 0.0205 0.0518 1.0000 11.000 0.9787 0.06689 0.06102 0.0248 0.0559 1.0000 11.250 0.9557 0.07099 0.06530 0.0251 0.0565 1.0000 11.500 0.9301 0.07603 0.07051 0.0239 0.0577 1.0000 11.750 0.9100 0.08170 0.07628 0.0218 0.0596 1.0000 12.000 0.8911 0.08774 0.08240 0.0192 0.0606 1.0000