12.25x3.75 (1225x375.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 1.0000 0.7623 0.0000 0.0000 0.5000 0.0000 0.2315 0.0000 0.2315 0.0000 0.1000 0.0000 0.0000 0.1400 0.9648 1.1304 0.0115 -0.4354 0.4944 0.0037 0.2247 0.7467 0.2168 0.2865 0.1028 0.0085 -0.0674 0.2800 0.9428 1.4744 0.0867 -0.8150 0.4916 0.0136 0.2182 2.8217 0.2057 0.2861 0.1100 0.0178 -0.0670 0.4200 0.9337 1.7941 0.2720 -1.0106 0.4912 0.0280 0.2120 5.8846 0.1979 0.2790 0.1195 0.0256 -0.0650 0.5600 0.9370 2.0897 0.5891 -0.9369 0.4930 0.0454 0.2060 9.5054 0.1930 0.2661 0.1309 0.0328 -0.0613 0.7000 0.9511 2.3611 1.0341 -0.5696 0.4968 0.0641 0.2002 13.2306 0.1904 0.2490 0.1441 0.0399 -0.0557 0.8400 0.9728 2.6082 1.5788 0.0588 0.5022 0.0826 0.1947 16.6535 0.1894 0.2291 0.1580 0.0477 -0.0482 0.9800 0.9976 2.8312 2.1753 0.8661 0.5091 0.0993 0.1894 19.4571 0.1890 0.2080 0.1711 0.0568 -0.0388 1.1200 1.0203 3.0300 2.7595 1.7294 0.5172 0.1126 0.1844 21.4118 0.1881 0.1875 0.1819 0.0675 -0.0281 1.2600 1.0353 3.2046 3.2529 2.4907 0.5262 0.1210 0.1796 22.3373 0.1860 0.1697 0.1885 0.0792 -0.0173 1.4000 1.0380 3.3549 3.5621 2.9569 0.5359 0.1229 0.1751 22.0454 0.1818 0.1568 0.1893 0.0905 -0.0083 1.5404 1.0331 3.4814 3.7052 3.1404 0.5463 0.1200 0.1708 20.9483 0.1765 0.1487 0.1858 0.1004 -0.0019 1.6875 1.0314 3.5879 3.8274 3.3041 0.5580 0.1162 0.1666 19.8482 0.1718 0.1420 0.1818 0.1103 0.0030 1.8351 1.0329 3.6678 3.9230 3.4396 0.5703 0.1117 0.1626 18.7904 0.1680 0.1368 0.1773 0.1198 0.0065 1.9826 1.0372 3.7208 3.9918 3.5445 0.5828 0.1065 0.1589 17.7676 0.1648 0.1329 0.1724 0.1286 0.0088 2.1302 1.0436 3.7470 4.0338 3.6174 0.5952 0.1005 0.1555 16.7721 0.1623 0.1301 0.1671 0.1366 0.0099 2.2777 1.0517 3.7500 4.0530 3.6608 0.6073 0.0939 0.1524 15.8122 0.1603 0.1281 0.1614 0.1438 0.0100 2.4253 1.0610 3.7500 4.0694 3.6936 0.6186 0.0868 0.1495 14.9521 0.1587 0.1269 0.1552 0.1501 0.0088 2.5728 1.0710 3.7500 4.0863 3.7190 0.6290 0.0793 0.1469 14.1862 0.1574 0.1263 0.1487 0.1554 0.0065 2.7203 1.0810 3.7500 4.1037 3.7368 0.6382 0.0713 0.1446 13.5004 0.1564 0.1261 0.1418 0.1596 0.0031 2.8679 1.0907 3.7500 4.1215 3.7471 0.6457 0.0629 0.1426 12.8835 0.1555 0.1262 0.1344 0.1626 -0.0011 3.0154 1.0995 3.7500 4.1400 3.7500 0.6514 0.0541 0.1408 12.3260 0.1549 0.1265 0.1266 0.1642 -0.0061 3.1630 1.1069 3.7500 4.1590 3.7500 0.6549 0.0449 0.1393 11.8197 0.1542 0.1267 0.1184 0.1643 -0.0117 3.3105 1.1124 3.7500 4.1775 3.7500 0.6560 0.0355 0.1379 11.3559 0.1534 0.1265 0.1098 0.1629 -0.0178 3.4581 1.1154 3.7500 4.1954 3.7501 0.6542 0.0260 0.1364 10.9288 0.1522 0.1258 0.1008 0.1597 -0.0242 3.6056 1.1155 3.7500 4.2125 3.7501 0.6494 0.0164 0.1349 10.5336 0.1505 0.1244 0.0914 0.1548 -0.0309 3.7531 1.1122 3.7500 4.2288 3.7501 0.6412 0.0066 0.1335 10.1666 0.1485 0.1222 0.0816 0.1480 -0.0377 3.9007 1.1048 3.7500 4.2441 3.7500 0.6293 -0.0032 0.1320 9.8244 0.1459 0.1192 0.0713 0.1393 -0.0448 4.0482 1.0930 3.7500 4.2584 3.7500 0.6134 -0.0130 0.1306 9.5041 0.1427 0.1154 0.0607 0.1286 -0.0519 4.1958 1.0761 3.7500 4.2713 3.7500 0.5932 -0.0228 0.1291 9.2031 0.1389 0.1106 0.0496 0.1158 -0.0591 4.3433 1.0537 3.7500 4.2828 3.7500 0.5685 -0.0326 0.1276 8.9191 0.1345 0.1049 0.0381 0.1008 -0.0663 4.4909 1.0253 3.7500 4.2926 3.7501 0.5388 -0.0424 0.1262 8.6500 0.1294 0.0982 0.0263 0.0835 -0.0736 4.6384 0.9903 3.7500 4.3004 3.7500 0.5040 -0.0521 0.1247 8.3938 0.1235 0.0906 0.0140 0.0639 -0.0808 4.7859 0.9482 3.7500 4.3057 3.7501 0.4637 -0.0617 0.1232 8.1484 0.1169 0.0822 0.0012 0.0419 -0.0879 4.9335 0.8986 3.7500 4.3079 3.7500 0.4176 -0.0713 0.1218 7.9119 0.1094 0.0730 -0.0119 0.0173 -0.0950 5.0810 0.8408 3.7500 4.3061 3.7501 0.3654 -0.0806 0.1203 7.6817 0.1012 0.0633 -0.0254 -0.0098 -0.1019 5.2286 0.7745 3.7500 4.2988 3.7501 0.3068 -0.0899 0.1188 7.4549 0.0920 0.0532 -0.0394 -0.0396 -0.1087 5.3761 0.6990 3.7500 4.2836 3.7501 0.2416 -0.0990 0.1174 7.2273 0.0820 0.0429 -0.0537 -0.0721 -0.1153 5.5237 0.6139 3.7492 4.2955 3.7235 0.1693 -0.1073 0.1159 7.0555 0.0712 0.0329 -0.0685 -0.1074 -0.1219 5.6712 0.5188 3.7080 4.3497 3.6311 0.0897 -0.1143 0.1145 6.9596 0.0594 0.0234 -0.0833 -0.1456 -0.1281 5.8127 0.4177 3.6098 4.4343 3.4954 0.0063 -0.1203 0.1131 6.9227 0.0472 0.0151 -0.0975 -0.1850 -0.1334 5.8497 0.3895 3.5747 4.4582 3.4569 -0.0167 -0.1219 0.1127 6.9160 0.0439 0.0132 -0.1012 -0.1958 -0.1348 5.8806 0.3655 3.5423 4.4767 3.4247 -0.0363 -0.1233 0.1124 6.9082 0.0411 0.0116 -0.1044 -0.2049 -0.1359 5.9116 0.3409 3.5071 4.4925 3.3927 -0.0563 -0.1247 0.1121 6.8964 0.0382 0.0101 -0.1076 -0.2141 -0.1370 5.9425 0.3158 3.4692 4.5026 3.3613 -0.0766 -0.1263 0.1118 6.8761 0.0353 0.0087 -0.1108 -0.2235 -0.1380 5.9734 0.2901 3.4286 4.5046 3.3305 -0.0973 -0.1279 0.1115 6.8439 0.0323 0.0074 -0.1141 -0.2330 -0.1391 6.0044 0.2639 3.3852 4.4925 3.3006 -0.1184 -0.1296 0.1112 6.7908 0.0293 0.0061 -0.1175 -0.2427 -0.1403 6.0353 0.2324 3.3391 4.4591 3.2965 -0.1446 -0.1321 0.1108 6.7066 0.0258 0.0048 -0.1217 -0.2550 -0.1418 6.0662 0.1890 3.2902 4.3920 3.4317 -0.1824 -0.1359 0.1105 6.5732 0.0209 0.0032 -0.1277 -0.2734 -0.1441 6.0972 0.1171 3.2386 4.2693 4.2989 -0.2484 -0.1430 0.1102 6.3590 0.0129 0.0013 -0.1380 -0.3066 -0.1483 6.1250 0.0078 3.1898 3.1900 3.1898 -0.3520 -0.1540 0.1100 4.7384 0.0009 0.0000 -0.1540 0.0000 0.0000 RADIUS: 6.14 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.40 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.098338 TOTAL WEIGHT (Kg) = 0.044598 TOTAL VOLUME (IN**3) = 1.602058 TOTAL PROJECTED AREA (IN**2) = 11.2897 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001815 MOMENT OF INERTIA (Kg-M**2) = 0.000205 STATIC MOMENT, ONE SIDE (IN-LB) = 0.105953 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 = 95.780 INNER LIMIT (NORMALIZED BY RADIUS) = 0.081 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11678.25 BASED ON MODULUS (MILLION) = 2.70 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.