XFOIL Version 6.96 Calculated polar for: DFVLR R-4 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.6430 0.09035 0.08454 -0.0581 1.0000 0.0325 -12.750 -0.6761 0.08100 0.07506 -0.0638 1.0000 0.0321 -12.500 -0.7058 0.07383 0.06774 -0.0675 1.0000 0.0319 -12.250 -0.7323 0.06818 0.06192 -0.0694 1.0000 0.0318 -12.000 -0.7567 0.06360 0.05718 -0.0698 1.0000 0.0317 -11.750 -0.7793 0.05986 0.05327 -0.0688 1.0000 0.0317 -11.500 -0.8008 0.05679 0.05004 -0.0667 1.0000 0.0317 -11.250 -0.8228 0.05436 0.04747 -0.0633 1.0000 0.0318 -11.000 -0.8436 0.05223 0.04520 -0.0594 1.0000 0.0318 -10.750 -0.8571 0.04972 0.04246 -0.0565 1.0000 0.0320 -10.500 -0.8653 0.04721 0.03968 -0.0538 1.0000 0.0322 -10.250 -0.8681 0.04476 0.03691 -0.0514 1.0000 0.0326 -10.000 -0.8661 0.04241 0.03421 -0.0492 1.0000 0.0330 -9.750 -0.8588 0.04047 0.03209 -0.0475 1.0000 0.0337 -9.500 -0.8482 0.03912 0.03070 -0.0461 1.0000 0.0346 -9.250 -0.8364 0.03783 0.02929 -0.0447 1.0000 0.0357 -9.000 -0.8230 0.03641 0.02770 -0.0434 1.0000 0.0370 -8.750 -0.8079 0.03490 0.02599 -0.0421 1.0000 0.0382 -8.500 -0.7915 0.03343 0.02430 -0.0408 1.0000 0.0394 -8.250 -0.7741 0.03210 0.02278 -0.0394 1.0000 0.0405 -8.000 -0.7522 0.03089 0.02161 -0.0394 0.9990 0.0421 -7.750 -0.7247 0.02988 0.02055 -0.0403 0.9968 0.0447 -7.500 -0.6962 0.02888 0.01937 -0.0411 0.9947 0.0481 -7.250 -0.6697 0.02779 0.01833 -0.0418 0.9924 0.0510 -7.000 -0.6420 0.02685 0.01736 -0.0427 0.9899 0.0549 -6.750 -0.6136 0.02596 0.01645 -0.0439 0.9876 0.0603 -6.500 -0.5835 0.02524 0.01566 -0.0452 0.9857 0.0677 -6.250 -0.5543 0.02441 0.01486 -0.0467 0.9837 0.0760 -6.000 -0.5257 0.02364 0.01411 -0.0480 0.9810 0.0876 -5.750 -0.4948 0.02289 0.01341 -0.0497 0.9786 0.1044 -5.500 -0.4620 0.02207 0.01270 -0.0520 0.9765 0.1275 -5.250 -0.4275 0.02107 0.01197 -0.0548 0.9749 0.1727 -5.000 -0.3888 0.01924 0.01125 -0.0598 0.9745 0.3597 -4.750 -0.3561 0.01891 0.01143 -0.0612 0.9731 0.4788 -4.500 -0.3310 0.01910 0.01180 -0.0603 0.9701 0.5321 -4.250 -0.3049 0.01942 0.01215 -0.0597 0.9665 0.5680 -4.000 -0.2780 0.01992 0.01265 -0.0589 0.9632 0.5965 -3.750 -0.2485 0.02047 0.01313 -0.0588 0.9607 0.6220 -3.500 -0.2219 0.02109 0.01370 -0.0579 0.9581 0.6393 -3.250 -0.2000 0.02159 0.01414 -0.0563 0.9536 0.6537 -3.000 -0.1716 0.02197 0.01443 -0.0563 0.9503 0.6670 -2.750 -0.1458 0.02237 0.01479 -0.0554 0.9472 0.6725 -2.500 -0.1093 0.02236 0.01465 -0.0577 0.9453 0.6811 -2.250 -0.0839 0.02256 0.01481 -0.0573 0.9419 0.6857 -2.000 -0.0590 0.02272 0.01492 -0.0569 0.9377 0.6919 -1.750 -0.0270 0.02278 0.01491 -0.0582 0.9345 0.6994 -1.500 0.0019 0.02296 0.01507 -0.0584 0.9317 0.7039 -1.250 0.0388 0.02298 0.01502 -0.0608 0.9296 0.7112 -1.000 0.0630 0.02313 0.01517 -0.0603 0.9252 0.7156 -0.750 0.0882 0.02328 0.01532 -0.0598 0.9203 0.7201 -0.500 0.1243 0.02329 0.01530 -0.0621 0.9170 0.7272 0.000 0.1800 0.02349 0.01555 -0.0621 0.9074 0.7355 0.250 0.2138 0.02349 0.01556 -0.0637 0.9026 0.7410 0.500 0.2521 0.02343 0.01551 -0.0659 0.8990 0.7458 0.750 0.2764 0.02348 0.01563 -0.0651 0.8916 0.7494 1.000 0.3107 0.02335 0.01554 -0.0663 0.8850 0.7537 1.250 0.3583 0.02296 0.01520 -0.0700 0.8801 0.7589 1.500 0.3976 0.02221 0.01451 -0.0709 0.8659 0.7625 1.750 0.4339 0.02120 0.01355 -0.0706 0.8453 0.7661 2.000 0.4667 0.02043 0.01282 -0.0702 0.8232 0.7706 2.250 0.5028 0.01991 0.01233 -0.0714 0.8044 0.7759 2.500 0.5294 0.01958 0.01208 -0.0703 0.7859 0.7791 2.750 0.5507 0.01944 0.01204 -0.0686 0.7619 0.7827 3.000 0.5789 0.01915 0.01179 -0.0681 0.7275 0.7865 3.250 0.6258 0.01850 0.01076 -0.0703 0.6160 0.7901 3.500 0.6489 0.01933 0.01054 -0.0687 0.4455 0.7936 3.750 0.6614 0.02033 0.01093 -0.0660 0.3345 0.7970 4.000 0.6794 0.02119 0.01134 -0.0645 0.2570 0.8007 4.250 0.7022 0.02191 0.01180 -0.0642 0.2109 0.8043 4.500 0.7268 0.02255 0.01227 -0.0641 0.1836 0.8079 4.750 0.7469 0.02306 0.01270 -0.0629 0.1670 0.8106 5.000 0.7688 0.02356 0.01320 -0.0620 0.1546 0.8136 5.250 0.7914 0.02414 0.01372 -0.0614 0.1455 0.8168 5.500 0.8164 0.02470 0.01431 -0.0613 0.1379 0.8202 6.000 0.8619 0.02592 0.01558 -0.0601 0.1275 0.8259 6.250 0.8848 0.02652 0.01623 -0.0594 0.1230 0.8287 6.500 0.9085 0.02724 0.01692 -0.0591 0.1189 0.8318 6.750 0.9346 0.02801 0.01774 -0.0592 0.1147 0.8350 7.000 0.9617 0.02873 0.01855 -0.0596 0.1101 0.8378 7.250 0.9843 0.02939 0.01926 -0.0589 0.1064 0.8403 7.500 1.0083 0.03029 0.02012 -0.0586 0.1032 0.8430 7.750 1.0341 0.03114 0.02114 -0.0586 0.1001 0.8459 8.000 1.0597 0.03197 0.02214 -0.0586 0.0962 0.8488 8.250 1.0847 0.03280 0.02303 -0.0587 0.0924 0.8517 8.500 1.1070 0.03373 0.02395 -0.0583 0.0893 0.8542 8.750 1.1298 0.03476 0.02521 -0.0577 0.0865 0.8568 9.000 1.1529 0.03588 0.02658 -0.0573 0.0837 0.8594 9.250 1.1757 0.03704 0.02792 -0.0570 0.0809 0.8619 9.500 1.1983 0.03821 0.02920 -0.0568 0.0786 0.8647 9.750 1.2215 0.03958 0.03056 -0.0568 0.0764 0.8674 10.000 1.2367 0.04104 0.03240 -0.0551 0.0738 0.8700 10.250 1.2505 0.04242 0.03412 -0.0535 0.0708 0.8728 10.500 1.2649 0.04359 0.03547 -0.0521 0.0683 0.8756 10.750 1.2808 0.04453 0.03645 -0.0511 0.0662 0.8783 11.000 1.2933 0.04612 0.03823 -0.0497 0.0641 0.8809 11.250 1.2954 0.04808 0.04062 -0.0466 0.0619 0.8836 11.500 1.2977 0.04976 0.04259 -0.0438 0.0600 0.8868 11.750 1.3025 0.05124 0.04425 -0.0415 0.0583 0.8902 12.000 1.3095 0.05261 0.04572 -0.0398 0.0570 0.8936 12.250 1.3195 0.05392 0.04701 -0.0385 0.0557 0.8967 12.500 1.3046 0.05730 0.05089 -0.0351 0.0544 0.8995 12.750 1.2884 0.06097 0.05500 -0.0323 0.0531 0.9025 13.000 1.2716 0.06487 0.05926 -0.0304 0.0520 0.9056 13.250 1.2544 0.06904 0.06372 -0.0292 0.0511 0.9087 13.500 1.2359 0.07350 0.06845 -0.0287 0.0503 0.9119 13.750 1.2128 0.07892 0.07414 -0.0293 0.0498 0.9150 14.000 1.1701 0.08810 0.08368 -0.0325 0.0499 0.9172