XFOIL Version 6.96 Calculated polar for: FX 74-130 WP1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.1074 0.08860 0.08541 -0.1223 0.8593 0.0166 -10.250 -0.1047 0.08525 0.08208 -0.1238 0.8578 0.0168 -10.000 -0.1017 0.08205 0.07890 -0.1252 0.8561 0.0169 -9.750 -0.1004 0.07848 0.07536 -0.1270 0.8541 0.0174 -9.500 -0.1017 0.07410 0.07100 -0.1298 0.8521 0.0183 -9.250 -0.1025 0.06948 0.06641 -0.1335 0.8499 0.0187 -9.000 -0.1059 0.06464 0.06158 -0.1376 0.8478 0.0188 -8.750 -0.1129 0.06046 0.05735 -0.1402 0.8455 0.0188 -8.500 -0.1240 0.05702 0.05388 -0.1404 0.8433 0.0188 -8.250 -0.1366 0.05443 0.05125 -0.1389 0.8409 0.0188 -8.000 -0.1420 0.05154 0.04823 -0.1378 0.8385 0.0189 -7.750 -0.1444 0.04870 0.04524 -0.1365 0.8363 0.0190 -7.500 -0.1443 0.04587 0.04221 -0.1351 0.8343 0.0190 -7.250 -0.1579 0.03969 0.03581 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2.500 0.7467 0.01144 0.00704 -0.1115 0.7618 0.8931 2.750 0.7774 0.01136 0.00696 -0.1123 0.7600 0.8939 3.000 0.7996 0.01137 0.00704 -0.1115 0.7551 0.8953 3.250 0.8290 0.01119 0.00689 -0.1120 0.7516 0.8962 3.500 0.8608 0.01094 0.00665 -0.1129 0.7488 0.8971 3.750 0.8927 0.01070 0.00641 -0.1139 0.7456 0.8979 4.000 0.9176 0.01056 0.00635 -0.1135 0.7394 0.8988 4.250 0.9497 0.01020 0.00599 -0.1144 0.7345 0.8994 4.500 0.9757 0.00998 0.00585 -0.1142 0.7271 0.9004 4.750 1.0062 0.00961 0.00547 -0.1147 0.7192 0.9013 5.000 1.0305 0.00938 0.00530 -0.1141 0.7066 0.9022 5.250 1.0547 0.00923 0.00516 -0.1135 0.6900 0.9030 5.500 1.0792 0.00919 0.00516 -0.1131 0.6735 0.9037 5.750 1.1023 0.00924 0.00516 -0.1123 0.6512 0.9044 6.000 1.1191 0.00941 0.00524 -0.1102 0.6159 0.9057 6.250 1.1246 0.00986 0.00546 -0.1060 0.5573 0.9073 6.500 1.1138 0.01067 0.00594 -0.0987 0.4950 0.9095 6.750 1.1025 0.01174 0.00672 -0.0919 0.4368 0.9119 7.000 1.0923 0.01304 0.00774 -0.0859 0.3770 0.9144 7.250 1.0851 0.01450 0.00890 -0.0810 0.3161 0.9168 7.500 1.0802 0.01603 0.01010 -0.0767 0.2533 0.9193 7.750 1.0784 0.01749 0.01124 -0.0729 0.1946 0.9214 8.000 1.0794 0.01892 0.01238 -0.0698 0.1394 0.9234 8.250 1.0831 0.02029 0.01349 -0.0671 0.0924 0.9255 8.500 1.0886 0.02165 0.01463 -0.0646 0.0572 0.9276 8.750 1.0988 0.02277 0.01568 -0.0628 0.0432 0.9295 9.000 1.1114 0.02376 0.01671 -0.0614 0.0365 0.9315 9.250 1.1241 0.02470 0.01769 -0.0599 0.0324 0.9337 9.500 1.1300 0.02610 0.01916 -0.0575 0.0290 0.9366 9.750 1.1451 0.02686 0.02000 -0.0564 0.0275 0.9398 10.000 1.1587 0.02773 0.02094 -0.0551 0.0253 0.9442 10.250 1.1702 0.02875 0.02202 -0.0536 0.0233 0.9503 10.750 1.1886 0.03146 0.02494 -0.0507 0.0199 1.0000 11.000 1.2030 0.03262 0.02617 -0.0500 0.0185 1.0000 11.250 1.2163 0.03387 0.02748 -0.0492 0.0172 1.0000 11.500 1.2266 0.03541 0.02906 -0.0482 0.0158 1.0000 11.750 1.2304 0.03768 0.03145 -0.0464 0.0145 1.0000 12.000 1.2460 0.03877 0.03262 -0.0460 0.0136 1.0000 12.250 1.2599 0.04003 0.03395 -0.0455 0.0124 1.0000 12.500 1.2720 0.04149 0.03547 -0.0449 0.0115 1.0000 12.750 1.2810 0.04330 0.03735 -0.0440 0.0108 1.0000 13.000 1.2851 0.04608 0.04028 -0.0423 0.0101 1.0000 13.250 1.2964 0.04775 0.04209 -0.0417 0.0097 1.0000 13.500 1.3064 0.04964 0.04413 -0.0410 0.0093 1.0000 13.750 1.3149 0.05174 0.04638 -0.0402 0.0089 1.0000 14.000 1.3222 0.05406 0.04885 -0.0394 0.0086 1.0000 14.250 1.3276 0.05650 0.05144 -0.0387 0.0083 1.0000 14.500 1.3315 0.05918 0.05428 -0.0381 0.0080 1.0000 14.750 1.3336 0.06210 0.05736 -0.0376 0.0079 1.0000 15.000 1.3339 0.06523 0.06065 -0.0372 0.0077 1.0000 15.250 1.3320 0.06878 0.06437 -0.0369 0.0076 1.0000 15.500 1.3285 0.07256 0.06831 -0.0368 0.0074 1.0000 15.750 1.3222 0.07686 0.07278 -0.0370 0.0073 1.0000 16.000 1.3127 0.08173 0.07787 -0.0374 0.0072 1.0000 16.250 1.2999 0.08733 0.08368 -0.0383 0.0071 1.0000 16.500 1.2856 0.09334 0.08991 -0.0398 0.0071 1.0000 16.750 1.2681 0.10015 0.09694 -0.0420 0.0071 1.0000 17.000 1.2513 0.10716 0.10416 -0.0448 0.0071 1.0000