10x6-4 (10x6-4.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0027 0.7071 -2.6532 0.0000 -0.0062 0.3536 0.0000 0.3588 0.0000 0.2537 0.0000 0.1750 0.0000 0.0000 0.1024 0.6122 -1.7552 0.0078 -0.2617 0.3061 0.0049 0.3585 0.6958 0.2195 0.1568 0.1771 0.0009 0.0217 0.2022 0.5458 -0.9088 0.0645 -0.5385 0.2698 0.0184 0.3575 2.9078 0.1951 0.1408 0.1827 -0.0015 0.0255 0.3017 0.5040 -0.1141 0.2193 -0.7739 0.2431 0.0382 0.3558 6.5992 0.1793 0.1301 0.1909 -0.0050 0.0305 0.4011 0.4829 0.6305 0.5068 -0.8912 0.2247 0.0622 0.3535 11.3701 0.1707 0.1229 0.2009 -0.0083 0.0354 0.5006 0.4781 1.3279 0.9363 -0.8834 0.2134 0.0885 0.3505 16.5764 0.1676 0.1180 0.2118 -0.0105 0.0403 0.6003 0.4838 1.9799 1.4959 -0.7164 0.2078 0.1150 0.3469 21.6325 0.1678 0.1143 0.2227 -0.0105 0.0452 0.7003 0.4927 2.5876 2.1703 -0.4205 0.2065 0.1398 0.3426 26.2536 0.1688 0.1104 0.2329 -0.0070 0.0504 0.8005 0.4976 3.1505 2.9532 -0.0058 0.2082 0.1608 0.3376 30.4192 0.1680 0.1051 0.2415 0.0008 0.0561 0.9006 0.5049 3.6675 3.7187 0.4932 0.2116 0.1763 0.3320 33.3116 0.1676 0.1010 0.2477 0.0075 0.0612 1.0000 0.5109 4.1366 4.3491 0.9578 0.2154 0.1840 0.3257 34.6905 0.1664 0.0980 0.2505 0.0122 0.0647 1.1013 0.5169 4.5696 4.8065 1.3566 0.2215 0.1863 0.3187 34.7833 0.1647 0.0959 0.2510 0.0161 0.0675 1.2259 0.5232 5.0395 5.3038 1.8804 0.2286 0.1887 0.3091 34.5512 0.1617 0.0926 0.2512 0.0203 0.0718 1.3517 0.5291 5.4448 5.7357 2.4279 0.2352 0.1909 0.2983 34.0323 0.1578 0.0887 0.2512 0.0237 0.0768 1.4776 0.5351 5.7797 6.0952 2.9723 0.2412 0.1929 0.2865 33.2861 0.1533 0.0845 0.2507 0.0261 0.0820 1.6034 0.5416 6.0436 6.3808 3.4940 0.2466 0.1946 0.2737 32.3480 0.1482 0.0803 0.2500 0.0275 0.0873 1.7293 0.5489 6.2357 6.5906 3.9752 0.2515 0.1962 0.2598 31.2392 0.1426 0.0760 0.2490 0.0277 0.0925 1.8552 0.5573 6.3545 6.7222 4.3993 0.2557 0.1976 0.2448 29.9717 0.1364 0.0717 0.2476 0.0267 0.0977 1.9810 0.5668 6.3985 6.7739 4.7518 0.2593 0.1987 0.2295 28.5555 0.1301 0.0676 0.2459 0.0245 0.1027 2.1069 0.5775 6.3886 6.7698 5.0373 0.2624 0.1989 0.2156 27.0848 0.1245 0.0640 0.2439 0.0210 0.1072 2.2328 0.5893 6.3654 6.7515 5.2821 0.2648 0.1984 0.2031 25.6997 0.1197 0.0609 0.2416 0.0165 0.1106 2.3586 0.6010 6.3325 6.7232 5.4881 0.2667 0.1972 0.1922 24.4022 0.1155 0.0583 0.2390 0.0117 0.1132 2.4845 0.6104 6.2924 6.6876 5.6569 0.2679 0.1956 0.1828 23.1905 0.1116 0.0557 0.2360 0.0073 0.1155 2.6103 0.6179 6.2472 6.6480 5.7904 0.2686 0.1933 0.1749 22.0643 0.1080 0.0532 0.2328 0.0032 0.1172 2.7362 0.6238 6.1989 6.6072 5.8905 0.2687 0.1904 0.1685 21.0226 0.1051 0.0511 0.2292 -0.0006 0.1183 2.8621 0.6283 6.1489 6.5676 5.9591 0.2682 0.1869 0.1636 20.0630 0.1028 0.0495 0.2253 -0.0042 0.1186 2.9879 0.6314 6.0984 6.5313 5.9980 0.2671 0.1825 0.1602 19.1826 0.1011 0.0482 0.2211 -0.0076 0.1181 3.1138 0.6332 6.0483 6.4974 6.0086 0.2654 0.1777 0.1577 18.3715 0.0998 0.0473 0.2166 -0.0108 0.1169 3.2397 0.6335 5.9991 6.4636 5.9923 0.2631 0.1727 0.1551 17.6167 0.0983 0.0463 0.2118 -0.0137 0.1153 3.3655 0.6320 5.9510 6.4300 5.9510 0.2603 0.1676 0.1526 16.9131 0.0965 0.0452 0.2066 -0.0164 0.1133 3.4914 0.6283 5.9038 6.3962 5.9039 0.2568 0.1624 0.1501 16.2552 0.0943 0.0439 0.2011 -0.0186 0.1111 3.6172 0.6219 5.8571 6.3617 5.8572 0.2527 0.1570 0.1476 15.6373 0.0918 0.0423 0.1953 -0.0201 0.1088 3.7431 0.6122 5.8100 6.3253 5.8101 0.2481 0.1517 0.1451 15.0535 0.0888 0.0403 0.1892 -0.0208 0.1065 3.8690 0.5983 5.7613 6.2858 5.7614 0.2429 0.1462 0.1425 14.4976 0.0853 0.0378 0.1828 -0.0202 0.1042 3.9948 0.5795 5.7096 6.2411 5.7097 0.2375 0.1408 0.1400 13.9633 0.0811 0.0348 0.1760 -0.0176 0.1020 4.1207 0.5549 5.6563 6.1924 5.6564 0.2321 0.1355 0.1375 13.4509 0.0763 0.0314 0.1690 -0.0126 0.1000 4.2466 0.5281 5.5970 6.1359 5.5971 0.2253 0.1299 0.1350 12.9508 0.0713 0.0279 0.1616 -0.0079 0.0977 4.3724 0.4976 5.5194 6.0584 5.5195 0.2159 0.1242 0.1325 12.4360 0.0659 0.0243 0.1539 -0.0041 0.0954 4.4983 0.4596 5.4109 5.9453 5.4110 0.2028 0.1186 0.1299 11.8792 0.0597 0.0204 0.1459 -0.0010 0.0935 4.6241 0.4104 5.2586 5.7802 5.2587 0.1845 0.1132 0.1274 11.2518 0.0523 0.0160 0.1375 0.0019 0.0923 4.7448 0.3491 5.0594 5.5538 5.0594 0.1610 0.1085 0.1250 10.5529 0.0436 0.0114 0.1292 0.0049 0.0921 4.7753 0.3310 4.9993 5.4829 4.9993 0.1540 0.1074 0.1244 10.3560 0.0412 0.0102 0.1271 0.0058 0.0922 4.8005 0.3151 4.9463 5.4192 4.9463 0.1479 0.1065 0.1239 10.1855 0.0390 0.0093 0.1253 0.0065 0.0923 4.8258 0.2984 4.8902 5.3504 4.8902 0.1415 0.1057 0.1234 10.0072 0.0368 0.0083 0.1235 0.0073 0.0925 4.8510 0.2808 4.8309 5.2758 4.8310 0.1347 0.1049 0.1229 9.8201 0.0345 0.0073 0.1217 0.0081 0.0928 4.8763 0.2624 4.7684 5.1947 4.7684 0.1275 0.1041 0.1224 9.6229 0.0321 0.0064 0.1199 0.0090 0.0931 4.9015 0.2429 4.7025 5.1060 4.7025 0.1200 0.1034 0.1219 9.4137 0.0296 0.0055 0.1180 0.0099 0.0934 4.9268 0.2221 4.6330 5.0081 4.6331 0.1117 0.1027 0.1214 9.1898 0.0270 0.0046 0.1161 0.0106 0.0938 4.9520 0.1927 4.5599 4.8991 4.5706 0.0974 0.1011 0.1209 8.9481 0.0233 0.0035 0.1128 0.0092 0.0936 4.9773 0.1411 4.4831 4.7754 4.6032 0.0720 0.0979 0.1204 8.6819 0.0170 0.0019 0.1065 0.0067 0.0925 5.0000 0.0031 4.4106 4.4108 4.4105 0.0038 0.0887 0.1199 7.9921 0.0004 0.0000 0.0887 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.35 HUB RADIUS (IN) HUBTRA: 1.00 HUB TRANSITION (IN) BLADES: 4 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.069034 TOTAL WEIGHT (Kg) = 0.031308 TOTAL VOLUME (IN**3) = 1.124653 TOTAL PROJECTED AREA (IN**2) = 9.3450 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000930 MOMENT OF INERTIA (Kg-M**2) = 0.000105 STATIC MOMENT, ONE SIDE (IN-LB) = 0.033540 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 76.724 INNER LIMIT (NORMALIZED BY RADIUS) = 0.070 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 18046.59 BASED ON MODULUS (MILLION) = 2.86 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.80, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 2.70, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.