9.25x6.0 (925x60.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) 0.0000 0.8000 1.0585 0.0000 0.0000 0.4000 0.0000 0.4125 0.0000 0.3300 0.0000 0.0700 0.0000 0.0000 0.1100 0.7643 1.5731 0.0104 -0.4497 0.3954 0.0034 0.4105 0.8583 0.3137 0.2128 0.0733 0.0096 -0.0846 0.2200 0.7253 2.0594 0.0808 -0.8751 0.3926 0.0126 0.4044 3.3465 0.2933 0.2075 0.0822 0.0271 -0.0823 0.3300 0.6873 2.5175 0.2658 -1.1773 0.3912 0.0258 0.3943 7.3051 0.2710 0.1975 0.0947 0.0476 -0.0776 0.4400 0.6546 2.9472 0.6119 -1.2410 0.3909 0.0414 0.3801 12.4800 0.2488 0.1819 0.1094 0.0698 -0.0706 0.5500 0.6309 3.3487 1.1520 -0.9784 0.3915 0.0579 0.3619 18.4368 0.2283 0.1634 0.1246 0.0922 -0.0621 0.6600 0.6175 3.7218 1.8936 -0.3411 0.3927 0.0738 0.3400 24.5431 0.2099 0.1442 0.1388 0.1136 -0.0530 0.7700 0.6135 4.0667 2.8010 0.6499 0.3942 0.0875 0.3185 30.0684 0.1954 0.1259 0.1504 0.1325 -0.0440 0.8800 0.6154 4.3833 3.7767 1.8673 0.3959 0.0974 0.2985 34.3350 0.1837 0.1098 0.1578 0.1476 -0.0363 0.9900 0.6187 4.6716 4.6529 3.0528 0.3973 0.1021 0.2800 36.7971 0.1732 0.0966 0.1593 0.1577 -0.0311 1.1000 0.6196 4.9316 5.2075 3.8331 0.3983 0.1000 0.2631 36.9965 0.1630 0.0870 0.1534 0.1615 -0.0300 1.2100 0.6181 5.1633 5.4570 4.1829 0.3989 0.0930 0.2477 35.6700 0.1531 0.0799 0.1423 0.1608 -0.0324 1.3198 0.6165 5.3664 5.6726 4.5055 0.3994 0.0856 0.2338 34.3747 0.1441 0.0736 0.1314 0.1600 -0.0351 1.4296 0.6148 5.5413 5.8581 4.8017 0.3998 0.0778 0.2214 33.1117 0.1361 0.0680 0.1206 0.1592 -0.0382 1.5394 0.6129 5.6880 6.0141 5.0681 0.4001 0.0696 0.2106 31.8733 0.1291 0.0629 0.1100 0.1583 -0.0416 1.6491 0.6107 5.8065 6.1413 5.3015 0.4002 0.0611 0.2013 30.6545 0.1229 0.0586 0.0994 0.1572 -0.0452 1.7589 0.6082 5.8968 6.2405 5.4992 0.4000 0.0521 0.1935 29.4518 0.1177 0.0548 0.0890 0.1561 -0.0491 1.8687 0.6053 5.9590 6.3122 5.6589 0.3995 0.0429 0.1872 28.2627 0.1133 0.0516 0.0788 0.1549 -0.0532 1.9785 0.6020 5.9930 6.3574 5.7785 0.3987 0.0332 0.1824 27.0853 0.1098 0.0489 0.0686 0.1536 -0.0575 2.0883 0.5981 6.0000 6.3775 5.8578 0.3975 0.0232 0.1791 25.9223 0.1071 0.0468 0.0586 0.1521 -0.0620 2.1981 0.5936 6.0000 6.3910 5.9155 0.3958 0.0133 0.1762 24.8324 0.1046 0.0450 0.0486 0.1503 -0.0669 2.3078 0.5884 6.0000 6.4039 5.9582 0.3937 0.0037 0.1732 23.8276 0.1019 0.0433 0.0388 0.1483 -0.0720 2.4176 0.5823 6.0000 6.4163 5.9860 0.3910 -0.0057 0.1703 22.8987 0.0992 0.0418 0.0292 0.1461 -0.0772 2.5274 0.5754 6.0000 6.4281 5.9990 0.3877 -0.0149 0.1674 22.0375 0.0963 0.0403 0.0196 0.1440 -0.0825 2.6372 0.5676 6.0000 6.4393 6.0000 0.3838 -0.0238 0.1644 21.2368 0.0933 0.0387 0.0102 0.1418 -0.0877 2.7470 0.5587 6.0000 6.4495 6.0001 0.3793 -0.0324 0.1615 20.4894 0.0902 0.0370 0.0008 0.1397 -0.0929 2.8568 0.5487 6.0000 6.4588 6.0002 0.3740 -0.0408 0.1586 19.7902 0.0870 0.0351 -0.0084 0.1377 -0.0979 2.9666 0.5374 6.0000 6.4676 6.0002 0.3679 -0.0489 0.1556 19.1360 0.0836 0.0331 -0.0175 0.1358 -0.1028 3.0763 0.5249 6.0000 6.4760 6.0002 0.3610 -0.0569 0.1527 18.5228 0.0801 0.0310 -0.0264 0.1338 -0.1075 3.1861 0.5110 6.0000 6.4837 6.0002 0.3532 -0.0646 0.1497 17.9460 0.0765 0.0288 -0.0353 0.1317 -0.1122 3.2959 0.4956 6.0000 6.4906 6.0001 0.3445 -0.0722 0.1468 17.4022 0.0727 0.0265 -0.0440 0.1294 -0.1167 3.4057 0.4786 6.0000 6.4966 6.0001 0.3348 -0.0794 0.1439 16.8883 0.0689 0.0243 -0.0526 0.1268 -0.1211 3.5155 0.4600 6.0000 6.5017 6.0001 0.3241 -0.0865 0.1409 16.4018 0.0648 0.0220 -0.0611 0.1239 -0.1253 3.6253 0.4397 6.0000 6.5058 6.0001 0.3123 -0.0934 0.1380 15.9402 0.0607 0.0197 -0.0694 0.1207 -0.1293 3.7350 0.4175 6.0000 6.5089 6.0001 0.2994 -0.1001 0.1351 15.5014 0.0564 0.0174 -0.0777 0.1173 -0.1332 3.8448 0.3935 6.0000 6.5107 6.0001 0.2854 -0.1065 0.1321 15.0833 0.0520 0.0151 -0.0858 0.1136 -0.1368 3.9546 0.3675 5.9847 6.4958 5.9847 0.2702 -0.1128 0.1292 14.6508 0.0475 0.0129 -0.0938 0.1095 -0.1403 4.0644 0.3394 5.9329 6.4429 5.9330 0.2537 -0.1190 0.1262 14.1598 0.0428 0.0107 -0.1017 0.1050 -0.1434 4.1742 0.3091 5.8447 6.3515 5.8447 0.2358 -0.1250 0.1233 13.6134 0.0381 0.0087 -0.1095 0.1002 -0.1463 4.2840 0.2766 5.7199 6.2211 5.7199 0.2167 -0.1309 0.1204 13.0138 0.0333 0.0068 -0.1171 0.0950 -0.1490 4.3892 0.2433 5.5660 6.0586 5.5660 0.1970 -0.1364 0.1175 12.3904 0.0286 0.0052 -0.1244 0.0897 -0.1514 4.4171 0.2341 5.5196 6.0093 5.5196 0.1915 -0.1378 0.1168 12.2174 0.0273 0.0047 -0.1263 0.0883 -0.1520 4.4405 0.2263 5.4789 5.9660 5.4789 0.1869 -0.1390 0.1162 12.0699 0.0263 0.0044 -0.1279 0.0870 -0.1525 4.4638 0.2183 5.4366 5.9206 5.4366 0.1822 -0.1402 0.1155 11.9200 0.0252 0.0041 -0.1294 0.0858 -0.1530 4.4872 0.2103 5.3926 5.8734 5.3926 0.1775 -0.1413 0.1149 11.7676 0.0242 0.0038 -0.1310 0.0845 -0.1535 4.5105 0.2016 5.3470 5.8242 5.3471 0.1721 -0.1426 0.1143 11.6131 0.0230 0.0034 -0.1327 0.0829 -0.1541 4.5339 0.1887 5.2997 5.7738 5.3007 0.1627 -0.1446 0.1137 11.4575 0.0215 0.0030 -0.1354 0.0791 -0.1553 4.5573 0.1700 5.2507 5.7219 5.2649 0.1476 -0.1478 0.1130 11.3005 0.0192 0.0024 -0.1395 0.0722 -0.1572 4.5806 0.1422 5.2001 5.6682 5.2457 0.1237 -0.1526 0.1124 11.1415 0.0160 0.0017 -0.1456 0.0604 -0.1604 4.6040 0.0910 5.1479 5.6132 5.3154 0.0767 -0.1617 0.1118 10.9814 0.0102 0.0007 -0.1573 0.0359 -0.1667 4.6250 0.0080 5.0994 5.0994 5.0994 -0.0017 -0.1767 0.1112 9.9530 0.0009 0.0000 -0.1768 0.0000 0.0000 RADIUS: 4.62 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.036665 TOTAL WEIGHT (Kg) = 0.016628 TOTAL VOLUME (IN**3) = 0.597322 TOTAL PROJECTED AREA (IN**2) = 4.5261 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000246 MOMENT OF INERTIA (Kg-M**2) = 0.000028 STATIC MOMENT, ONE SIDE (IN-LB) = 0.022191 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 = 65.108 INNER LIMIT (NORMALIZED BY RADIUS) = 0.086 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 21135.12 BASED ON MODULUS (MILLION) = 2.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.