Airfoil: W1015-30 f0 Builder: S. Cassidy Comment: Clean, Cf/C = 30%, Flap = 0° Number of Reynolds #'s: 3 Average Reynolds #: 100074.6 Number of angles of attack: 51 alpha / Cl / Cm -10.31 -0.91 -0.0082 -9.25 -0.87 -0.0047 -8.35 -0.82 -0.0019 -7.33 -0.74 0.0013 -6.32 -0.66 0.0043 -5.34 -0.58 0.0067 -4.12 -0.49 0.0113 -3.18 -0.41 0.0139 -2.16 -0.31 0.0137 -1.02 -0.14 -0.0006 -0.05 -0.04 -0.0060 1.02 0.04 -0.0017 1.92 0.18 -0.0159 3.06 0.29 -0.0116 4.00 0.40 -0.0130 5.12 0.49 -0.0085 6.00 0.56 -0.0057 7.07 0.64 -0.0024 8.02 0.71 0.0014 9.03 0.79 0.0040 10.14 0.86 0.0059 11.16 0.91 0.0097 12.20 0.97 0.0114 12.91 0.58 -0.0754 13.92 0.55 -0.0721 14.95 0.61 -0.0789 14.81 0.61 -0.0633 13.81 0.58 -0.0579 12.80 0.57 -0.0527 11.66 0.61 -0.0532 10.75 0.64 -0.0398 9.81 0.86 0.0136 8.76 0.79 0.0092 7.76 0.72 0.0070 6.76 0.65 0.0027 5.81 0.57 -0.0012 4.76 0.49 -0.0048 3.67 0.40 -0.0094 2.64 0.25 0.0076 1.71 0.18 -0.0049 0.72 0.03 0.0078 -0.45 -0.05 0.0005 -1.34 -0.21 0.0238 -2.38 -0.30 0.0195 -3.41 -0.41 0.0162 -4.62 -0.50 0.0111 -5.48 -0.57 0.0078 -6.54 -0.67 0.0046 -7.58 -0.74 0.0004 -8.53 -0.82 -0.0042 -9.63 -0.88 -0.0082 Tabulated from data in file 07188sn.dat & reduced using program C10.20 Average Reynolds #: 200060.0 Number of angles of attack: 57 alpha / Cl / Cm -10.28 -0.94 -0.0086 -9.25 -0.87 -0.0059 -8.34 -0.80 -0.0033 -7.32 -0.72 -0.0004 -6.18 -0.63 0.0033 -5.19 -0.56 0.0068 -4.16 -0.48 0.0105 -3.15 -0.39 0.0118 -2.14 -0.24 -0.0030 -1.06 -0.13 -0.0008 0.02 -0.03 0.0014 0.98 0.06 0.0044 1.91 0.15 0.0066 2.91 0.28 0.0009 4.09 0.43 -0.0086 5.01 0.51 -0.0070 6.15 0.61 -0.0038 7.13 0.69 -0.0010 8.17 0.77 0.0015 9.21 0.85 0.0044 10.12 0.92 0.0069 11.22 0.99 0.0102 12.26 1.06 0.0136 13.14 1.11 0.0163 14.21 1.14 0.0183 15.29 1.14 0.0039 16.25 1.13 -0.0132 16.84 0.70 -0.0878 18.07 0.69 -0.0900 17.72 0.69 -0.0824 16.72 0.68 -0.0809 15.72 0.71 -0.0808 14.71 0.66 -0.0764 13.84 0.64 -0.0717 12.67 0.63 -0.0669 11.99 1.04 0.0184 10.88 0.98 0.0143 9.90 0.90 0.0119 8.87 0.83 0.0082 7.74 0.74 0.0051 6.78 0.66 0.0019 5.69 0.57 -0.0015 4.71 0.49 -0.0041 3.86 0.40 -0.0026 2.74 0.26 0.0074 1.64 0.13 0.0079 0.56 0.03 0.0048 -0.40 -0.05 0.0019 -1.47 -0.17 -0.0002 -2.33 -0.27 0.0005 -3.50 -0.43 0.0131 -4.40 -0.50 0.0097 -5.56 -0.59 0.0051 -6.42 -0.66 0.0016 -7.58 -0.74 -0.0023 -8.53 -0.82 -0.0056 -9.56 -0.89 -0.0094 Tabulated from data in file 07190sn.dat & reduced using program C10.20 Average Reynolds #: 400089.4 Number of angles of attack: 57 alpha / Cl / Cm -10.25 -0.98 -0.0109 -9.29 -0.91 -0.0083 -8.25 -0.83 -0.0058 -7.31 -0.75 -0.0026 -6.25 -0.66 0.0014 -5.13 -0.57 0.0056 -4.13 -0.47 0.0089 -3.16 -0.34 -0.0009 -2.11 -0.22 -0.0010 -1.19 -0.14 -0.0004 -0.13 -0.03 0.0013 0.87 0.06 0.0029 2.06 0.17 0.0050 3.13 0.27 0.0051 4.07 0.37 0.0052 5.04 0.46 0.0060 6.05 0.59 0.0017 7.08 0.69 0.0027 8.12 0.78 0.0052 9.25 0.88 0.0083 10.15 0.94 0.0108 11.26 1.03 0.0141 12.29 1.10 0.0171 13.32 1.16 0.0195 14.21 1.20 0.0213 15.31 1.18 -0.0056 16.20 1.16 -0.0219 17.09 1.13 -0.0312 18.09 1.10 -0.0401 17.80 1.08 -0.0339 16.83 1.12 -0.0268 15.84 1.16 -0.0141 14.88 1.20 0.0088 13.82 1.19 0.0223 12.93 1.14 0.0204 11.80 1.07 0.0172 10.84 1.00 0.0142 9.72 0.91 0.0111 8.86 0.84 0.0087 7.75 0.74 0.0054 6.73 0.66 0.0037 5.75 0.55 0.0029 4.64 0.42 0.0069 3.70 0.34 0.0063 2.57 0.22 0.0062 1.68 0.13 0.0052 0.61 0.03 0.0037 -0.37 -0.06 0.0022 -1.49 -0.16 0.0002 -2.45 -0.26 -0.0000 -3.49 -0.41 0.0096 -4.49 -0.51 0.0086 -5.60 -0.60 0.0043 -6.57 -0.68 0.0004 -7.64 -0.78 -0.0039 -8.59 -0.86 -0.0075 -9.67 -0.94 -0.0105 Tabulated from data in file 07192sn.dat & reduced using program C10.20 File w1015-30_f0_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:59