Airfoil: Avistar Builder: B. Champine Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 100900 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.425 -0.0357 -5.04 -0.276 -0.0450 -4.04 -0.158 -0.0533 -3.04 -0.034 -0.0592 -2.04 0.067 -0.0545 -1.00 0.264 -0.0659 0.03 0.408 -0.0758 1.04 0.464 -0.0684 2.07 0.539 -0.0629 3.10 0.619 -0.0588 4.13 0.701 -0.0565 5.17 0.783 -0.0520 6.21 0.865 -0.0470 7.23 0.936 -0.0417 8.22 0.970 -0.0331 9.18 0.986 -0.0234 10.45 1.011 -0.0140 11.39 1.031 -0.0097 12.34 1.040 -0.0071 13.27 1.043 -0.0067 14.22 1.047 -0.0084 15.20 1.026 -0.0164 16.15 0.891 -0.0866 17.14 0.836 -0.0937 18.16 0.811 -0.0956 16.41 0.883 -0.0888 15.54 0.988 -0.0589 14.71 1.033 -0.0166 13.62 1.035 -0.0121 12.77 1.037 -0.0116 11.67 1.033 -0.0142 10.60 1.012 -0.0180 9.51 0.987 -0.0248 8.66 0.983 -0.0334 7.53 0.963 -0.0422 6.63 0.922 -0.0481 5.46 0.837 -0.0536 4.54 0.771 -0.0561 3.61 0.684 -0.0579 2.45 0.585 -0.0610 1.55 0.538 -0.0649 0.39 0.427 -0.0721 -0.47 0.370 -0.0760 -1.66 0.115 -0.0571 -2.52 0.022 -0.0617 -3.66 -0.101 -0.0618 -4.80 -0.248 -0.0525 -5.71 -0.349 -0.0434 -6.85 -0.462 -0.0350 Tabulated from data in file CL01117.DAT & reduced using program Q06.01L Average Reynolds #: 201600 Number of angles of attack: 53 alpha / Cl / Cm -6.36 -0.294 -0.0649 -4.90 -0.175 -0.0635 -4.14 -0.111 -0.0608 -3.07 -0.027 -0.0570 -1.97 0.068 -0.0513 -0.87 0.169 -0.0458 0.24 0.304 -0.0486 0.96 0.409 -0.0543 2.03 0.541 -0.0590 3.04 0.638 -0.0560 4.25 0.759 -0.0527 5.31 0.845 -0.0491 6.35 0.902 -0.0415 7.07 0.922 -0.0342 8.35 0.957 -0.0221 9.30 0.986 -0.0156 10.22 1.005 -0.0106 11.14 1.019 -0.0081 12.35 1.032 -0.0070 13.30 1.034 -0.0084 14.22 1.033 -0.0124 15.14 1.033 -0.0202 16.17 0.863 -0.0951 17.18 0.825 -0.1004 18.26 0.838 -0.1063 19.36 0.851 -0.1095 20.40 0.869 -0.1118 18.41 0.836 -0.1087 17.38 0.827 -0.1052 16.39 0.843 -0.0988 15.77 0.895 -0.0907 14.65 1.038 -0.0179 13.53 1.031 -0.0120 12.77 1.030 -0.0101 11.69 1.028 -0.0093 10.63 1.011 -0.0108 9.60 0.990 -0.0153 8.55 0.962 -0.0221 7.45 0.928 -0.0309 6.62 0.913 -0.0408 5.40 0.861 -0.0505 4.49 0.793 -0.0538 3.59 0.723 -0.0558 2.47 0.595 -0.0594 1.59 0.509 -0.0611 0.31 0.321 -0.0498 -0.65 0.196 -0.0454 -1.61 0.111 -0.0486 -2.84 0.010 -0.0554 -3.82 -0.076 -0.0591 -4.82 -0.150 -0.0624 -5.85 -0.240 -0.0656 -6.90 -0.351 -0.0649 Tabulated from data in file CL01119.DAT & reduced using program Q06.01L Average Reynolds #: 302500 Number of angles of attack: 53 alpha / Cl / Cm -6.29 -0.293 -0.0605 -5.13 -0.215 -0.0584 -3.90 -0.106 -0.0554 -2.93 -0.019 -0.0539 -1.89 0.078 -0.0508 -0.77 0.178 -0.0463 0.03 0.269 -0.0444 1.19 0.469 -0.0529 2.27 0.607 -0.0581 3.40 0.711 -0.0558 4.15 0.783 -0.0538 5.30 0.863 -0.0472 6.39 0.904 -0.0374 7.11 0.931 -0.0307 8.35 0.977 -0.0205 9.24 1.003 -0.0149 10.13 1.023 -0.0105 11.23 1.039 -0.0075 12.07 1.046 -0.0076 13.15 1.057 -0.0093 14.34 1.097 -0.0146 15.18 1.104 -0.0484 16.18 0.966 -0.0917 17.22 0.892 -0.1030 18.17 0.892 -0.1075 19.09 0.903 -0.1134 20.17 0.916 -0.1263 18.22 0.910 -0.1091 17.54 0.890 -0.1046 16.50 0.921 -0.0960 15.62 1.084 -0.0750 14.75 1.118 -0.0187 13.72 1.093 -0.0129 12.64 1.070 -0.0092 11.75 1.063 -0.0079 10.60 1.048 -0.0098 9.70 1.029 -0.0131 8.74 1.003 -0.0186 7.45 0.956 -0.0280 6.64 0.926 -0.0356 5.44 0.880 -0.0462 4.51 0.822 -0.0527 3.53 0.740 -0.0552 2.48 0.635 -0.0579 1.42 0.512 -0.0557 0.42 0.360 -0.0474 -0.78 0.208 -0.0463 -1.86 0.106 -0.0505 -2.64 0.042 -0.0526 -3.74 -0.061 -0.0546 -4.82 -0.165 -0.0574 -5.86 -0.257 -0.0601 -6.88 -0.336 -0.0635 Tabulated from data in file CL01121.DAT & reduced using program Q06.01L Average Reynolds #: 403100 Number of angles of attack: 53 alpha / Cl / Cm -6.56 -0.333 -0.0596 -4.94 -0.198 -0.0559 -4.00 -0.110 -0.0541 -3.03 -0.015 -0.0526 -1.97 0.079 -0.0508 -1.01 0.184 -0.0474 0.07 0.320 -0.0451 1.25 0.466 -0.0480 2.05 0.577 -0.0521 3.26 0.723 -0.0567 4.13 0.796 -0.0536 5.59 0.870 -0.0421 6.15 0.894 -0.0371 7.55 0.950 -0.0256 8.40 0.975 -0.0192 9.19 0.998 -0.0147 10.33 1.022 -0.0105 11.41 1.040 -0.0098 12.47 1.062 -0.0122 13.18 1.102 -0.0126 14.44 1.149 -0.0171 15.36 1.102 -0.0599 16.19 1.031 -0.0843 17.08 0.928 -0.0997 18.17 0.958 -0.1094 19.00 0.967 -0.1219 20.01 0.955 -0.1341 18.46 0.962 -0.1168 17.42 0.954 -0.1023 16.33 0.965 -0.0926 15.34 1.061 -0.0645 14.81 1.208 -0.0280 13.56 1.157 -0.0155 12.70 1.106 -0.0133 11.58 1.072 -0.0091 10.76 1.056 -0.0090 9.65 1.026 -0.0113 8.48 0.990 -0.0167 7.53 0.964 -0.0240 6.46 0.929 -0.0325 5.27 0.874 -0.0431 4.38 0.827 -0.0501 3.42 0.752 -0.0544 2.42 0.630 -0.0534 1.49 0.504 -0.0489 0.13 0.325 -0.0453 -0.77 0.224 -0.0466 -1.89 0.094 -0.0507 -2.78 0.017 -0.0524 -3.92 -0.099 -0.0541 -4.72 -0.174 -0.0551 -5.88 -0.282 -0.0578 -7.01 -0.372 -0.0607 Tabulated from data in file CL01123.DAT & reduced using program Q06.01L Average Reynolds #: 504100 Number of angles of attack: 51 alpha / Cl / Cm -7.28 -0.394 -0.0618 -5.14 -0.229 -0.0594 -3.87 -0.113 -0.0581 -2.95 -0.025 -0.0569 -1.99 0.064 -0.0568 -0.95 0.167 -0.0543 0.16 0.282 -0.0522 1.33 0.410 -0.0516 2.50 0.560 -0.0550 3.16 0.645 -0.0588 4.39 0.764 -0.0593 5.67 0.831 -0.0509 6.59 0.870 -0.0433 7.57 0.913 -0.0354 8.45 0.947 -0.0289 9.29 0.974 -0.0238 10.63 1.007 -0.0194 11.34 1.025 -0.0183 12.57 1.063 -0.0200 13.81 1.138 -0.0206 14.54 1.185 -0.0204 15.61 1.169 -0.0449 16.27 1.031 -0.0756 17.41 0.963 -0.1004 18.06 0.934 -0.1041 19.12 0.995 -0.1191 17.60 0.967 -0.1015 16.59 0.988 -0.0901 15.62 1.171 -0.0463 14.33 1.199 -0.0173 13.44 1.147 -0.0159 12.55 1.117 -0.0119 11.68 1.095 -0.0087 10.23 1.064 -0.0096 9.67 1.044 -0.0118 8.08 0.983 -0.0215 7.38 0.955 -0.0263 6.01 0.892 -0.0374 5.17 0.852 -0.0452 4.10 0.776 -0.0528 3.18 0.674 -0.0524 2.37 0.568 -0.0487 0.83 0.386 -0.0462 -0.01 0.302 -0.0474 -0.80 0.219 -0.0485 -1.61 0.139 -0.0509 -2.91 0.013 -0.0526 -4.12 -0.108 -0.0541 -4.84 -0.177 -0.0551 -6.15 -0.291 -0.0574 -6.87 -0.350 -0.0596 Tabulated from data in file CL01766.DAT & reduced using program Q06.01L File AVISTAR.LFT created on 10-24-1997 at 19:34:41 using program FORMAT