XFOIL Version 6.96 Calculated polar for: KC-135 BL351.6 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4457 0.09282 0.08789 -0.0281 1.0000 0.0365 -8.500 -0.4448 0.08929 0.08441 -0.0296 1.0000 0.0372 -8.250 -0.4460 0.08568 0.08087 -0.0314 1.0000 0.0377 -8.000 -0.4505 0.08204 0.07730 -0.0336 1.0000 0.0382 -7.750 -0.4554 0.07851 0.07381 -0.0353 1.0000 0.0386 -7.500 -0.4575 0.07505 0.07035 -0.0365 1.0000 0.0391 -7.250 -0.4592 0.07167 0.06697 -0.0371 1.0000 0.0398 -7.000 -0.4602 0.06844 0.06370 -0.0371 1.0000 0.0407 -6.750 -0.4605 0.06538 0.06059 -0.0365 1.0000 0.0416 -6.500 -0.4601 0.06259 0.05772 -0.0355 1.0000 0.0427 -6.250 -0.4594 0.06190 0.05665 -0.0335 1.0000 0.0458 -5.750 -0.4481 0.05628 0.05055 -0.0310 0.9964 0.0469 -5.500 -0.4277 0.05023 0.04458 -0.0334 0.9905 0.0485 -5.250 -0.4022 0.04641 0.04058 -0.0355 0.9837 0.0502 -5.000 -0.3697 0.04272 0.03647 -0.0372 0.9775 0.0433 -4.750 -0.3427 0.03923 0.03266 -0.0383 0.9699 0.0413 -4.500 -0.3122 0.03560 0.02854 -0.0390 0.9634 0.0370 -4.250 -0.2786 0.03276 0.02512 -0.0392 0.9571 0.0314 -4.000 -0.2473 0.03002 0.02199 -0.0401 0.9517 0.0308 -3.750 -0.2169 0.02773 0.01930 -0.0405 0.9452 0.0308 -3.500 -0.1815 0.02630 0.01732 -0.0414 0.9407 0.0337 -3.250 -0.1532 0.02404 0.01481 -0.0416 0.9338 0.0347 -3.000 -0.1203 0.02232 0.01287 -0.0424 0.9288 0.0355 -2.750 -0.0884 0.02097 0.01140 -0.0431 0.9234 0.0373 -2.500 -0.0584 0.02001 0.01033 -0.0435 0.9168 0.0415 -2.250 -0.0249 0.01892 0.00916 -0.0444 0.9125 0.0428 -2.000 0.0008 0.01813 0.00833 -0.0439 0.9045 0.0441 -1.750 0.0307 0.01745 0.00759 -0.0442 0.8991 0.0461 -1.500 0.0545 0.01680 0.00690 -0.0436 0.8913 0.0516 -1.250 0.0837 0.01636 0.00633 -0.0438 0.8854 0.0559 -1.000 0.1103 0.01607 0.00590 -0.0435 0.8781 0.0609 -0.750 0.1389 0.01570 0.00550 -0.0436 0.8718 0.0769 -0.500 0.1514 0.01335 0.00552 -0.0407 0.8650 0.7264 -0.250 0.2508 0.01302 0.00561 -0.0527 0.8700 0.9741 0.000 0.3103 0.01294 0.00538 -0.0596 0.8659 0.9983 0.250 0.3361 0.01294 0.00527 -0.0595 0.8573 1.0000 0.500 0.3572 0.01299 0.00524 -0.0585 0.8475 1.0000 0.750 0.3812 0.01301 0.00518 -0.0578 0.8393 1.0000 1.000 0.4027 0.01308 0.00520 -0.0567 0.8291 1.0000 1.250 0.4245 0.01311 0.00519 -0.0554 0.8171 1.0000 1.500 0.4466 0.01309 0.00510 -0.0540 0.8027 1.0000 1.750 0.4687 0.01306 0.00502 -0.0525 0.7871 1.0000 2.000 0.4910 0.01307 0.00498 -0.0511 0.7724 1.0000 2.250 0.5135 0.01311 0.00503 -0.0498 0.7589 1.0000 2.500 0.5363 0.01318 0.00510 -0.0487 0.7460 1.0000 2.750 0.5593 0.01326 0.00520 -0.0476 0.7334 1.0000 3.000 0.5824 0.01334 0.00530 -0.0465 0.7201 1.0000 3.250 0.6054 0.01342 0.00546 -0.0454 0.7053 1.0000 3.500 0.6283 0.01351 0.00560 -0.0442 0.6893 1.0000 3.750 0.6513 0.01359 0.00573 -0.0431 0.6713 1.0000 4.000 0.6739 0.01369 0.00589 -0.0418 0.6507 1.0000 4.250 0.6964 0.01379 0.00607 -0.0405 0.6263 1.0000 4.500 0.7182 0.01393 0.00624 -0.0391 0.5961 1.0000 4.750 0.7395 0.01411 0.00641 -0.0375 0.5560 1.0000 5.000 0.7595 0.01440 0.00659 -0.0357 0.4998 1.0000 5.250 0.7772 0.01493 0.00684 -0.0336 0.4339 1.0000 5.500 0.7927 0.01572 0.00732 -0.0315 0.3655 1.0000 5.750 0.8054 0.01678 0.00790 -0.0291 0.2941 1.0000 6.000 0.8203 0.01774 0.00852 -0.0273 0.2331 1.0000 6.250 0.8388 0.01847 0.00916 -0.0260 0.1952 1.0000 6.500 0.8562 0.01933 0.00986 -0.0246 0.1405 1.0000 6.750 0.8680 0.02092 0.01090 -0.0225 0.0692 1.0000 7.000 0.8826 0.02230 0.01217 -0.0206 0.0510 1.0000 7.250 0.8974 0.02362 0.01349 -0.0188 0.0418 1.0000 7.500 0.9136 0.02474 0.01479 -0.0171 0.0372 1.0000 7.750 0.9277 0.02605 0.01622 -0.0152 0.0339 1.0000 8.000 0.9400 0.02762 0.01788 -0.0132 0.0308 1.0000 8.250 0.9558 0.02891 0.01938 -0.0116 0.0282 1.0000 8.500 0.9712 0.03047 0.02109 -0.0100 0.0264 1.0000 8.750 0.9875 0.03222 0.02296 -0.0086 0.0252 1.0000 9.000 1.0044 0.03421 0.02508 -0.0074 0.0241 1.0000 9.250 1.0220 0.03669 0.02773 -0.0064 0.0233 1.0000 9.500 1.0375 0.03982 0.03110 -0.0053 0.0224 1.0000 9.750 1.0484 0.04188 0.03357 -0.0034 0.0215 1.0000 10.000 1.0556 0.04418 0.03626 -0.0013 0.0205 1.0000 10.250 1.0589 0.04693 0.03943 0.0009 0.0200 1.0000 10.500 1.0563 0.04976 0.04260 0.0038 0.0197 1.0000 10.750 1.0490 0.05271 0.04587 0.0066 0.0196 1.0000 11.000 1.0385 0.05585 0.04931 0.0090 0.0195 1.0000 11.250 1.0252 0.05935 0.05308 0.0107 0.0194 1.0000 11.500 1.0101 0.06319 0.05718 0.0115 0.0195 1.0000 11.750 0.9923 0.06762 0.06185 0.0113 0.0195 1.0000 12.000 0.9735 0.07261 0.06705 0.0100 0.0195 1.0000 12.250 0.9529 0.07846 0.07309 0.0075 0.0196 1.0000 12.500 0.9317 0.08521 0.08001 0.0036 0.0198 1.0000 12.750 0.9093 0.09332 0.08825 -0.0018 0.0200 1.0000