XFOIL Version 6.96 Calculated polar for: LOCKHEED C-5A BL488.2 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.6617 0.07759 0.07344 -0.0566 1.0000 0.0211 -11.750 -0.6952 0.06814 0.06386 -0.0629 1.0000 0.0209 -11.500 -0.7243 0.06205 0.05765 -0.0655 1.0000 0.0208 -11.250 -0.7521 0.05767 0.05314 -0.0653 1.0000 0.0207 -11.000 -0.7793 0.05447 0.04981 -0.0628 1.0000 0.0207 -10.750 -0.8071 0.05220 0.04742 -0.0580 1.0000 0.0207 -10.500 -0.8343 0.05033 0.04543 -0.0519 1.0000 0.0206 -10.250 -0.8537 0.04778 0.04267 -0.0470 1.0000 0.0206 -10.000 -0.8680 0.04512 0.03976 -0.0425 1.0000 0.0207 -9.750 -0.8768 0.04249 0.03684 -0.0384 1.0000 0.0207 -9.500 -0.8797 0.03990 0.03392 -0.0350 0.9999 0.0208 -9.250 -0.8659 0.03687 0.03045 -0.0348 0.9975 0.0210 -9.000 -0.8478 0.03440 0.02753 -0.0348 0.9952 0.0212 -8.750 -0.8279 0.03231 0.02522 -0.0348 0.9933 0.0217 -8.500 -0.8068 0.03088 0.02366 -0.0347 0.9912 0.0221 -8.250 -0.7837 0.02956 0.02218 -0.0348 0.9891 0.0226 -8.000 -0.7588 0.02819 0.02061 -0.0352 0.9873 0.0230 -7.750 -0.7326 0.02680 0.01901 -0.0356 0.9857 0.0234 -7.500 -0.7071 0.02555 0.01758 -0.0358 0.9841 0.0238 -7.250 -0.6839 0.02443 0.01631 -0.0353 0.9816 0.0243 -7.000 -0.6583 0.02338 0.01513 -0.0354 0.9794 0.0249 -6.750 -0.6313 0.02242 0.01403 -0.0356 0.9775 0.0256 -6.500 -0.6033 0.02158 0.01307 -0.0361 0.9759 0.0264 -6.250 -0.5753 0.02062 0.01210 -0.0367 0.9745 0.0273 -6.000 -0.5524 0.01995 0.01141 -0.0362 0.9713 0.0284 -5.750 -0.5269 0.01934 0.01077 -0.0361 0.9685 0.0299 -5.500 -0.4989 0.01879 0.01015 -0.0366 0.9662 0.0319 -5.250 -0.4698 0.01819 0.00952 -0.0373 0.9643 0.0345 -5.000 -0.4391 0.01771 0.00902 -0.0383 0.9628 0.0379 -4.750 -0.4156 0.01729 0.00855 -0.0377 0.9592 0.0414 -4.500 -0.3898 0.01682 0.00808 -0.0377 0.9559 0.0464 -4.250 -0.3610 0.01637 0.00762 -0.0382 0.9534 0.0531 -4.000 -0.3305 0.01589 0.00722 -0.0391 0.9514 0.0669 -3.750 -0.2992 0.01535 0.00690 -0.0403 0.9498 0.1071 -3.500 -0.2752 0.01493 0.00664 -0.0399 0.9458 0.1475 -3.250 -0.2495 0.01448 0.00638 -0.0399 0.9418 0.1967 -3.000 -0.2204 0.01382 0.00612 -0.0407 0.9389 0.2884 -2.750 -0.1914 0.01296 0.00589 -0.0417 0.9368 0.4313 -2.250 -0.1430 0.01212 0.00599 -0.0401 0.9293 0.6563 -2.000 -0.1152 0.01204 0.00600 -0.0399 0.9256 0.6989 -1.750 -0.0834 0.01198 0.00593 -0.0407 0.9231 0.7207 -1.500 -0.0502 0.01191 0.00588 -0.0416 0.9211 0.7405 -1.250 -0.0159 0.01184 0.00582 -0.0428 0.9196 0.7587 -1.000 0.0023 0.01187 0.00588 -0.0407 0.9121 0.7752 -0.750 0.0323 0.01182 0.00587 -0.0409 0.9089 0.7955 -0.500 0.0644 0.01175 0.00583 -0.0415 0.9066 0.8165 -0.250 0.0978 0.01166 0.00578 -0.0424 0.9047 0.8326 0.000 0.1175 0.01169 0.00586 -0.0405 0.8971 0.8453 0.250 0.1480 0.01161 0.00581 -0.0407 0.8933 0.8577 0.500 0.1817 0.01148 0.00570 -0.0417 0.8904 0.8691 0.750 0.2058 0.01144 0.00569 -0.0407 0.8829 0.8800 1.000 0.2376 0.01128 0.00556 -0.0412 0.8773 0.8882 1.250 0.2663 0.01109 0.00539 -0.0409 0.8681 0.8982 1.500 0.3008 0.01077 0.00509 -0.0417 0.8572 0.9056 1.750 0.3311 0.01053 0.00486 -0.0417 0.8424 0.9149 2.000 0.3636 0.01036 0.00471 -0.0422 0.8266 0.9231 2.250 0.3967 0.01018 0.00452 -0.0429 0.8048 0.9315 2.500 0.4352 0.01000 0.00427 -0.0446 0.7713 0.9375 2.750 0.4705 0.00996 0.00407 -0.0457 0.7239 0.9449 3.000 0.5049 0.01012 0.00399 -0.0467 0.6647 0.9505 3.250 0.5309 0.01052 0.00403 -0.0461 0.5915 0.9600 3.500 0.5546 0.01122 0.00423 -0.0454 0.4872 0.9686 3.750 0.5776 0.01202 0.00454 -0.0449 0.3854 0.9783 4.000 0.6025 0.01290 0.00493 -0.0450 0.2864 0.9874 4.250 0.6314 0.01366 0.00533 -0.0459 0.2097 0.9952 4.500 0.6565 0.01425 0.00568 -0.0460 0.1665 1.0000 4.750 0.6702 0.01462 0.00593 -0.0435 0.1412 1.0000 5.000 0.6857 0.01499 0.00620 -0.0413 0.1233 1.0000 5.250 0.7028 0.01537 0.00651 -0.0393 0.1085 1.0000 5.500 0.7210 0.01576 0.00688 -0.0376 0.0954 1.0000 5.750 0.7400 0.01618 0.00725 -0.0361 0.0845 1.0000 6.000 0.7593 0.01662 0.00764 -0.0346 0.0762 1.0000 6.250 0.7794 0.01704 0.00807 -0.0332 0.0708 1.0000 6.500 0.7993 0.01751 0.00854 -0.0319 0.0669 1.0000 6.750 0.8182 0.01808 0.00908 -0.0304 0.0637 1.0000 7.000 0.8385 0.01855 0.00962 -0.0292 0.0610 1.0000 7.250 0.8587 0.01905 0.01016 -0.0279 0.0578 1.0000 7.500 0.8777 0.01965 0.01075 -0.0266 0.0548 1.0000 7.750 0.8963 0.02032 0.01144 -0.0252 0.0523 1.0000 8.000 0.9163 0.02090 0.01210 -0.0239 0.0502 1.0000 8.250 0.9356 0.02153 0.01280 -0.0226 0.0482 1.0000 8.500 0.9540 0.02222 0.01353 -0.0212 0.0464 1.0000 8.750 0.9713 0.02307 0.01440 -0.0197 0.0446 1.0000 9.000 0.9896 0.02401 0.01539 -0.0184 0.0429 1.0000 9.250 1.0089 0.02471 0.01624 -0.0171 0.0411 1.0000 9.500 1.0275 0.02548 0.01711 -0.0158 0.0392 1.0000 9.750 1.0451 0.02630 0.01800 -0.0145 0.0376 1.0000 10.000 1.0621 0.02724 0.01897 -0.0131 0.0364 1.0000 10.250 1.0795 0.02853 0.02030 -0.0119 0.0351 1.0000 10.500 1.0969 0.02955 0.02154 -0.0105 0.0340 1.0000 10.750 1.1131 0.03063 0.02281 -0.0090 0.0326 1.0000 11.000 1.1273 0.03159 0.02389 -0.0073 0.0312 1.0000 11.250 1.1400 0.03236 0.02474 -0.0055 0.0300 1.0000 11.500 1.1515 0.03320 0.02559 -0.0036 0.0290 1.0000 11.750 1.1627 0.03439 0.02701 -0.0017 0.0277 1.0000 12.000 1.1730 0.03564 0.02849 0.0002 0.0264 1.0000 12.250 1.1822 0.03681 0.02981 0.0021 0.0254 1.0000 12.500 1.1906 0.03793 0.03103 0.0039 0.0246 1.0000 12.750 1.1981 0.03909 0.03227 0.0057 0.0240 1.0000 13.000 1.2035 0.04057 0.03383 0.0075 0.0234 1.0000 13.250 1.2052 0.04279 0.03638 0.0095 0.0225 1.0000 13.500 1.2057 0.04497 0.03880 0.0113 0.0217 1.0000 13.750 1.2064 0.04701 0.04105 0.0128 0.0209 1.0000 14.000 1.2074 0.04902 0.04319 0.0139 0.0203 1.0000 14.250 1.2082 0.05108 0.04535 0.0148 0.0198 1.0000 14.500 1.2076 0.05341 0.04778 0.0153 0.0194 1.0000 14.750 1.2023 0.05651 0.05100 0.0156 0.0190 1.0000 15.000 1.1877 0.06119 0.05599 0.0153 0.0187 1.0000 15.250 1.1704 0.06657 0.06165 0.0141 0.0184 1.0000 15.500 1.1499 0.07292 0.06826 0.0118 0.0182 1.0000 15.750 1.1257 0.08064 0.07624 0.0079 0.0181 1.0000 16.000 1.0959 0.09033 0.08617 0.0021 0.0182 1.0000 16.250 1.0589 0.10276 0.09883 -0.0058 0.0185 1.0000 16.500 1.0155 0.11766 0.11388 -0.0150 0.0190 1.0000