XFOIL Version 6.94 Calculated polar for: 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3344 0.00759 0.00265 -0.0750 0.7542 0.7570 0.500 0.3893 0.00760 0.00265 -0.0746 0.7411 0.7793 1.000 0.4432 0.00757 0.00266 -0.0739 0.7265 0.8015 1.500 0.4967 0.00756 0.00268 -0.0731 0.7104 0.8247 2.000 0.5489 0.00753 0.00271 -0.0720 0.6919 0.8495 2.500 0.5992 0.00750 0.00277 -0.0706 0.6699 0.8771 3.000 0.6470 0.00750 0.00281 -0.0684 0.6440 0.9101 3.500 0.6976 0.00757 0.00288 -0.0669 0.6104 0.9515 4.000 0.7697 0.00785 0.00304 -0.0706 0.5637 0.9856 4.500 0.8257 0.00831 0.00331 -0.0712 0.5142 1.0000 5.000 0.8686 0.00885 0.00366 -0.0689 0.4674 1.0000 5.500 0.9121 0.00946 0.00409 -0.0668 0.4203 1.0000 6.000 0.9549 0.01015 0.00462 -0.0646 0.3730 1.0000 6.500 0.9963 0.01093 0.00521 -0.0623 0.3254 1.0000 7.000 1.0357 0.01180 0.00589 -0.0597 0.2752 1.0000 7.500 1.0726 0.01280 0.00666 -0.0567 0.2233 1.0000 8.000 1.1070 0.01387 0.00753 -0.0534 0.1778 1.0000 8.500 1.1380 0.01491 0.00846 -0.0495 0.1419 1.0000 9.000 1.1665 0.01609 0.00951 -0.0453 0.1099 1.0000 9.500 1.1931 0.01743 0.01074 -0.0411 0.0819 1.0000 10.000 1.2161 0.01904 0.01222 -0.0368 0.0538 1.0000 10.500 1.2243 0.02169 0.01463 -0.0311 0.0203 1.0000 11.000 1.2380 0.02419 0.01721 -0.0265 0.0142 1.0000 11.500 1.2545 0.02664 0.01985 -0.0228 0.0126 1.0000 12.000 1.2666 0.02958 0.02298 -0.0194 0.0116 1.0000 12.500 1.2710 0.03336 0.02694 -0.0161 0.0107 1.0000 13.000 1.2668 0.03823 0.03205 -0.0133 0.0103 1.0000 13.500 1.2574 0.04408 0.03814 -0.0113 0.0099 1.0000 14.000 1.2590 0.04930 0.04360 -0.0105 0.0097 1.0000 14.500 1.2573 0.05536 0.04990 -0.0104 0.0094 1.0000 15.000 1.2558 0.06188 0.05665 -0.0113 0.0090 1.0000 15.500 1.2487 0.06963 0.06466 -0.0130 0.0088 1.0000 16.000 1.2393 0.07821 0.07351 -0.0155 0.0087 1.0000 16.500 1.2277 0.08768 0.08326 -0.0189 0.0087 1.0000 17.000 1.2143 0.09802 0.09389 -0.0234 0.0085 1.0000 17.500 1.1970 0.10962 0.10580 -0.0291 0.0085 1.0000 18.000 1.1755 0.12263 0.11913 -0.0361 0.0085 1.0000 18.500 1.1499 0.13725 0.13408 -0.0445 0.0086 1.0000 19.000 1.1222 0.15321 0.15032 -0.0544 0.0087 1.0000 19.500 1.0847 0.17297 0.17040 -0.0667 0.0089 1.0000 21.500 0.7655 0.25250 0.25075 -0.1077 0.0177 1.0000 22.000 0.7735 0.26123 0.25950 -0.1117 0.0160 1.0000 22.500 0.7833 0.26866 0.26695 -0.1150 0.0149 1.0000 23.000 0.7950 0.27530 0.27363 -0.1177 0.0143 1.0000 23.500 0.8040 0.28504 0.28338 -0.1207 0.0139 1.0000 24.000 0.8058 0.29584 0.29418 -0.1261 0.0133 1.0000 24.500 0.8134 0.30515 0.30350 -0.1299 0.0119 1.0000 25.000 0.8217 0.31316 0.31154 -0.1333 0.0109 1.0000 25.500 0.8303 0.32066 0.31906 -0.1364 0.0104 1.0000 26.000 0.8405 0.32958 0.32799 -0.1388 0.0100 1.0000 26.500 0.8443 0.33979 0.33822 -0.1431 0.0099 1.0000 27.000 0.8492 0.35063 0.34908 -0.1472 0.0091 1.0000 27.500 0.8560 0.35993 0.35840 -0.1507 0.0083 1.0000