XFOIL Version 6.96 Calculated polar for: RG 14 10% 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.5577 0.09319 0.08942 -0.0270 1.0000 0.0185 -10.750 -0.7066 0.05313 0.04916 -0.0549 1.0000 0.0163 -10.500 -0.7495 0.04714 0.04285 -0.0545 1.0000 0.0161 -10.250 -0.7689 0.04399 0.03951 -0.0514 1.0000 0.0161 -10.000 -0.7699 0.04217 0.03757 -0.0493 1.0000 0.0164 -9.750 -0.7682 0.04038 0.03564 -0.0472 1.0000 0.0168 -9.500 -0.7688 0.03791 0.03293 -0.0448 1.0000 0.0172 -9.250 -0.7671 0.03538 0.03010 -0.0423 1.0000 0.0176 -9.000 -0.7620 0.03304 0.02747 -0.0399 1.0000 0.0181 -8.750 -0.7548 0.03076 0.02484 -0.0375 1.0000 0.0188 -8.500 -0.7447 0.02870 0.02243 -0.0353 1.0000 0.0195 -8.250 -0.7316 0.02713 0.02050 -0.0332 1.0000 0.0204 -8.000 -0.7181 0.02548 0.01867 -0.0313 1.0000 0.0213 -7.750 -0.7019 0.02446 0.01755 -0.0297 1.0000 0.0221 -7.500 -0.6852 0.02343 0.01640 -0.0281 1.0000 0.0230 -7.250 -0.6679 0.02236 0.01517 -0.0264 1.0000 0.0239 -7.000 -0.6500 0.02139 0.01404 -0.0248 1.0000 0.0249 -6.750 -0.6314 0.02061 0.01309 -0.0233 1.0000 0.0263 -6.500 -0.6132 0.01965 0.01201 -0.0217 1.0000 0.0273 -6.250 -0.5821 0.01858 0.01087 -0.0229 0.9969 0.0287 -6.000 -0.5492 0.01780 0.01002 -0.0243 0.9936 0.0302 -5.750 -0.5173 0.01711 0.00925 -0.0255 0.9894 0.0321 -5.500 -0.4836 0.01653 0.00856 -0.0269 0.9854 0.0346 -5.250 -0.4516 0.01574 0.00774 -0.0281 0.9812 0.0373 -5.000 -0.4203 0.01518 0.00714 -0.0290 0.9758 0.0407 -4.750 -0.3860 0.01467 0.00656 -0.0305 0.9716 0.0454 -4.500 -0.3555 0.01416 0.00607 -0.0312 0.9658 0.0546 -4.250 -0.3230 0.01369 0.00562 -0.0323 0.9604 0.0687 -4.000 -0.2877 0.01322 0.00523 -0.0341 0.9567 0.0880 -3.750 -0.2591 0.01284 0.00491 -0.0343 0.9490 0.1095 -3.500 -0.2249 0.01237 0.00459 -0.0359 0.9443 0.1455 -3.250 -0.1947 0.01187 0.00433 -0.0366 0.9374 0.1990 -3.000 -0.1622 0.01138 0.00407 -0.0378 0.9309 0.2580 -2.750 -0.1316 0.01092 0.00383 -0.0385 0.9231 0.3199 -2.500 -0.1003 0.01044 0.00361 -0.0393 0.9154 0.3941 -2.250 -0.0722 0.00997 0.00344 -0.0394 0.9058 0.4761 -2.000 -0.0426 0.00945 0.00330 -0.0396 0.8976 0.5761 -1.750 -0.0173 0.00905 0.00331 -0.0386 0.8865 0.6794 -1.500 0.0095 0.00890 0.00339 -0.0376 0.8752 0.7603 -1.250 0.0382 0.00887 0.00337 -0.0371 0.8635 0.8036 -1.000 0.0669 0.00885 0.00333 -0.0367 0.8507 0.8315 -0.750 0.0947 0.00885 0.00329 -0.0361 0.8368 0.8543 -0.500 0.1223 0.00887 0.00326 -0.0355 0.8220 0.8733 -0.250 0.1501 0.00889 0.00323 -0.0349 0.8064 0.8894 0.000 0.1784 0.00893 0.00321 -0.0345 0.7902 0.9036 0.250 0.2076 0.00898 0.00319 -0.0343 0.7730 0.9169 0.500 0.2376 0.00904 0.00317 -0.0344 0.7551 0.9292 0.750 0.2696 0.00912 0.00316 -0.0348 0.7360 0.9391 1.000 0.3031 0.00920 0.00315 -0.0357 0.7138 0.9473 1.250 0.3347 0.00931 0.00314 -0.0363 0.6900 0.9569 1.500 0.3715 0.00943 0.00315 -0.0379 0.6641 0.9632 1.750 0.4035 0.00955 0.00318 -0.0387 0.6389 0.9707 2.000 0.4403 0.00968 0.00319 -0.0406 0.6120 0.9752 2.250 0.4731 0.00984 0.00323 -0.0416 0.5843 0.9812 2.750 0.5396 0.01015 0.00335 -0.0441 0.5312 0.9910 3.000 0.5719 0.01033 0.00344 -0.0452 0.5046 0.9961 3.250 0.6015 0.01053 0.00355 -0.0458 0.4765 1.0000 3.500 0.6191 0.01075 0.00367 -0.0439 0.4473 1.0000 3.750 0.6365 0.01101 0.00380 -0.0419 0.4173 1.0000 4.000 0.6542 0.01127 0.00398 -0.0400 0.3889 1.0000 4.250 0.6722 0.01156 0.00416 -0.0382 0.3603 1.0000 4.500 0.6905 0.01188 0.00437 -0.0365 0.3315 1.0000 4.750 0.7091 0.01223 0.00461 -0.0348 0.3017 1.0000 5.000 0.7280 0.01262 0.00487 -0.0332 0.2698 1.0000 5.250 0.7474 0.01305 0.00519 -0.0318 0.2387 1.0000 5.500 0.7675 0.01350 0.00553 -0.0305 0.2100 1.0000 5.750 0.7877 0.01398 0.00589 -0.0293 0.1835 1.0000 6.000 0.8080 0.01449 0.00630 -0.0281 0.1635 1.0000 6.250 0.8288 0.01499 0.00676 -0.0270 0.1482 1.0000 6.500 0.8501 0.01547 0.00721 -0.0260 0.1346 1.0000 6.750 0.8719 0.01592 0.00767 -0.0250 0.1215 1.0000 7.000 0.8936 0.01638 0.00813 -0.0241 0.1088 1.0000 7.250 0.9150 0.01687 0.00862 -0.0231 0.0974 1.0000 7.500 0.9359 0.01740 0.00917 -0.0221 0.0880 1.0000 7.750 0.9559 0.01802 0.00976 -0.0210 0.0798 1.0000 8.000 0.9768 0.01856 0.01037 -0.0200 0.0731 1.0000 8.250 0.9956 0.01926 0.01107 -0.0187 0.0674 1.0000 8.500 1.0160 0.01983 0.01176 -0.0177 0.0619 1.0000 8.750 1.0339 0.02058 0.01252 -0.0163 0.0568 1.0000 9.000 1.0527 0.02126 0.01330 -0.0151 0.0529 1.0000 9.250 1.0710 0.02196 0.01408 -0.0138 0.0488 1.0000 9.500 1.0865 0.02284 0.01496 -0.0122 0.0449 1.0000 9.750 1.1052 0.02346 0.01572 -0.0110 0.0408 1.0000 10.000 1.1211 0.02423 0.01655 -0.0096 0.0372 1.0000 10.250 1.1345 0.02513 0.01752 -0.0078 0.0344 1.0000 10.500 1.1483 0.02591 0.01843 -0.0059 0.0316 1.0000 10.750 1.1598 0.02681 0.01941 -0.0039 0.0294 1.0000 11.000 1.1677 0.02797 0.02062 -0.0016 0.0272 1.0000 11.250 1.1792 0.02894 0.02174 0.0002 0.0249 1.0000 11.500 1.1880 0.03006 0.02297 0.0021 0.0230 1.0000 11.750 1.1921 0.03153 0.02452 0.0042 0.0214 1.0000 12.000 1.1977 0.03304 0.02619 0.0060 0.0202 1.0000 12.250 1.2019 0.03468 0.02799 0.0077 0.0190 1.0000 12.500 1.2051 0.03645 0.02989 0.0091 0.0180 1.0000 12.750 1.2067 0.03843 0.03198 0.0102 0.0171 1.0000 13.000 1.2037 0.04096 0.03460 0.0111 0.0164 1.0000 13.250 1.2032 0.04348 0.03731 0.0116 0.0156 1.0000 13.500 1.2012 0.04631 0.04033 0.0118 0.0150 1.0000 13.750 1.1979 0.04944 0.04363 0.0115 0.0143 1.0000 14.000 1.1928 0.05298 0.04733 0.0108 0.0140 1.0000 14.250 1.1865 0.05690 0.05140 0.0095 0.0135 1.0000 14.500 1.1789 0.06123 0.05588 0.0078 0.0132 1.0000 14.750 1.1695 0.06608 0.06089 0.0056 0.0130 1.0000 15.000 1.1578 0.07154 0.06650 0.0029 0.0129 1.0000 15.250 1.1447 0.07754 0.07266 -0.0003 0.0127 1.0000 15.500 1.1301 0.08409 0.07935 -0.0039 0.0126 1.0000 15.750 1.1145 0.09114 0.08656 -0.0078 0.0126 1.0000 16.000 1.0974 0.09879 0.09437 -0.0122 0.0125 1.0000 16.250 1.0793 0.10697 0.10271 -0.0169 0.0125 1.0000 16.500 1.0600 0.11581 0.11171 -0.0220 0.0126 1.0000 16.750 1.0382 0.12557 0.12163 -0.0276 0.0126 1.0000 17.000 1.0097 0.13759 0.13384 -0.0345 0.0128 1.0000