13x9 (13x9.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 1.0840 1.0969 0.0000 0.0000 0.5420 0.0000 0.4493 0.0000 0.4870 0.0000 0.0400 0.0000 0.0000 0.1625 1.0347 1.9970 0.0182 -0.8499 0.5345 0.0043 0.4476 1.0193 0.4631 0.4247 0.0469 0.0098 -0.1815 0.3250 0.9870 2.8426 0.1413 -1.6440 0.5284 0.0160 0.4427 3.9573 0.4369 0.4209 0.0656 0.0291 -0.1763 0.4875 0.9466 3.6339 0.4607 -2.2041 0.5238 0.0332 0.4345 8.5534 0.4113 0.4135 0.0928 0.0493 -0.1665 0.6500 0.9194 4.3708 1.0469 -2.3610 0.5208 0.0538 0.4230 14.3780 0.3889 0.4010 0.1253 0.0696 -0.1531 0.8125 0.9090 5.0532 1.9377 -1.9972 0.5195 0.0762 0.4083 20.7853 0.3711 0.3847 0.1599 0.0893 -0.1374 0.9750 0.9152 5.6813 3.1216 -1.0701 0.5200 0.0985 0.3902 27.0014 0.3571 0.3659 0.1934 0.1077 -0.1207 1.1375 0.9337 6.2550 4.5199 0.3555 0.5224 0.1189 0.3689 32.3095 0.3445 0.3456 0.2226 0.1244 -0.1043 1.3000 0.9572 6.7743 5.9746 2.0787 0.5268 0.1356 0.3449 36.1837 0.3301 0.3245 0.2444 0.1385 -0.0894 1.4625 0.9778 7.2392 7.2510 3.7556 0.5333 0.1468 0.3217 38.2764 0.3146 0.3028 0.2559 0.1497 -0.0773 1.6250 0.9884 7.6496 8.0638 4.9300 0.5420 0.1506 0.3000 38.3010 0.2965 0.2800 0.2542 0.1578 -0.0692 1.7869 0.9922 8.0045 8.4476 5.5733 0.5524 0.1486 0.2798 36.9585 0.2776 0.2574 0.2435 0.1640 -0.0647 1.9380 0.9977 8.2870 8.7487 6.1353 0.5628 0.1453 0.2623 35.6964 0.2616 0.2386 0.2329 0.1694 -0.0622 2.0884 1.0047 8.5216 8.9972 6.6537 0.5737 0.1408 0.2460 34.4365 0.2472 0.2220 0.2220 0.1745 -0.0611 2.2389 1.0129 8.7095 9.1950 7.1228 0.5848 0.1350 0.2311 33.1699 0.2341 0.2072 0.2106 0.1792 -0.0611 2.3894 1.0220 8.8508 9.3428 7.5356 0.5960 0.1281 0.2174 31.8946 0.2222 0.1939 0.1989 0.1834 -0.0622 2.5399 1.0316 8.9455 9.4414 7.8860 0.6071 0.1200 0.2049 30.6095 0.2114 0.1820 0.1867 0.1870 -0.0641 2.6903 1.0414 8.9935 9.4916 8.1690 0.6177 0.1109 0.1938 29.3142 0.2018 0.1714 0.1740 0.1901 -0.0669 2.8408 1.0509 9.0000 9.4994 8.3850 0.6278 0.1007 0.1838 28.0217 0.1932 0.1621 0.1610 0.1927 -0.0704 2.9913 1.0599 9.0000 9.5009 8.5642 0.6370 0.0895 0.1751 26.8167 0.1856 0.1540 0.1475 0.1949 -0.0751 3.1418 1.0679 9.0000 9.5034 8.7127 0.6452 0.0775 0.1677 25.7072 0.1791 0.1472 0.1335 0.1968 -0.0810 3.2922 1.0746 9.0000 9.5079 8.8304 0.6522 0.0646 0.1615 24.6851 0.1736 0.1415 0.1191 0.1983 -0.0880 3.4427 1.0797 9.0000 9.5149 8.9172 0.6577 0.0507 0.1566 23.7433 0.1691 0.1370 0.1043 0.1994 -0.0961 3.5932 1.0827 9.0000 9.5253 8.9733 0.6616 0.0359 0.1529 22.8753 0.1656 0.1335 0.0891 0.2000 -0.1052 3.7437 1.0833 9.0000 9.5396 8.9985 0.6635 0.0201 0.1505 22.0755 0.1630 0.1311 0.0734 0.2000 -0.1152 3.8941 1.0811 9.0000 9.5573 9.0000 0.6634 0.0034 0.1490 21.3361 0.1611 0.1292 0.0573 0.1994 -0.1260 4.0446 1.0758 9.0000 9.5746 9.0002 0.6609 -0.0134 0.1477 20.6443 0.1589 0.1266 0.0407 0.1979 -0.1371 4.1951 1.0669 9.0000 9.5911 9.0003 0.6559 -0.0305 0.1463 19.9951 0.1561 0.1233 0.0237 0.1956 -0.1484 4.3456 1.0542 9.0000 9.6069 9.0003 0.6481 -0.0477 0.1449 19.3844 0.1527 0.1192 0.0062 0.1923 -0.1598 4.4960 1.0371 9.0000 9.6216 9.0003 0.6374 -0.0650 0.1435 18.8086 0.1488 0.1143 -0.0116 0.1880 -0.1713 4.6465 1.0154 9.0000 9.6353 9.0003 0.6235 -0.0825 0.1421 18.2646 0.1443 0.1085 -0.0299 0.1827 -0.1829 4.7970 0.9886 9.0000 9.6476 9.0002 0.6062 -0.1001 0.1407 17.7494 0.1391 0.1019 -0.0487 0.1762 -0.1944 4.9475 0.9565 9.0000 9.6584 9.0002 0.5853 -0.1178 0.1393 17.2601 0.1333 0.0944 -0.0679 0.1685 -0.2060 5.0979 0.9185 9.0000 9.6674 9.0002 0.5606 -0.1356 0.1379 16.7943 0.1267 0.0862 -0.0875 0.1595 -0.2175 5.2484 0.8743 9.0000 9.6740 9.0002 0.5318 -0.1534 0.1365 16.3495 0.1194 0.0774 -0.1076 0.1493 -0.2290 5.3989 0.8236 9.0000 9.6777 9.0002 0.4987 -0.1713 0.1352 15.9230 0.1113 0.0681 -0.1281 0.1377 -0.2403 5.5494 0.7660 8.9798 9.6574 8.9800 0.4612 -0.1893 0.1338 15.4813 0.1025 0.0584 -0.1491 0.1246 -0.2515 5.6998 0.7010 8.9079 9.5799 8.9080 0.4190 -0.2075 0.1324 14.9759 0.0928 0.0485 -0.1705 0.1100 -0.2622 5.8503 0.6285 8.7839 9.4798 8.7607 0.3719 -0.2251 0.1310 14.4612 0.0823 0.0386 -0.1921 0.0939 -0.2726 6.0008 0.5483 8.6077 9.4488 8.5219 0.3197 -0.2410 0.1296 14.0689 0.0711 0.0292 -0.2136 0.0762 -0.2829 6.1451 0.4637 8.3898 9.5189 8.2522 0.2645 -0.2552 0.1283 13.8492 0.0595 0.0207 -0.2338 0.0577 -0.2923 6.1840 0.4396 8.3230 9.5569 8.1785 0.2489 -0.2589 0.1279 13.8184 0.0562 0.0186 -0.2393 0.0524 -0.2947 6.2167 0.4188 8.2640 9.5952 8.1174 0.2353 -0.2621 0.1276 13.8014 0.0534 0.0168 -0.2439 0.0480 -0.2968 6.2494 0.3976 8.2026 9.6390 8.0575 0.2216 -0.2652 0.1273 13.7922 0.0506 0.0151 -0.2485 0.0434 -0.2988 6.2821 0.3759 8.1387 9.6876 7.9994 0.2075 -0.2684 0.1270 13.7897 0.0477 0.0135 -0.2531 0.0388 -0.3009 6.3148 0.3522 8.0723 9.7405 7.9436 0.1917 -0.2721 0.1267 13.7931 0.0446 0.0119 -0.2582 0.0332 -0.3032 6.3475 0.3221 8.0035 9.7968 7.8971 0.1697 -0.2773 0.1264 13.8010 0.0407 0.0099 -0.2650 0.0245 -0.3064 6.3802 0.2830 7.9322 9.8664 7.9175 0.1393 -0.2845 0.1261 13.8269 0.0357 0.0077 -0.2741 0.0111 -0.3108 6.4129 0.2291 7.8585 9.9234 8.0646 0.0947 -0.2954 0.1258 13.8355 0.0288 0.0050 -0.2873 -0.0098 -0.3173 6.4456 0.1325 7.7823 9.9752 8.9946 0.0088 -0.3165 0.1255 13.8370 0.0166 0.0017 -0.3120 -0.0530 -0.3298 6.4750 0.0118 7.7116 7.7116 7.7115 -0.1010 -0.3443 0.1252 10.7332 0.0015 0.0000 -0.3443 0.0000 0.0000 RADIUS: 6.47 PROPELLER RADIUS (IN) HUBRAD: 0.54 HUB RADIUS (IN) HUBTRA: 1.62 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.148065 TOTAL WEIGHT (Kg) = 0.067150 TOTAL VOLUME (IN**3) = 2.412173 TOTAL PROJECTED AREA (IN**2) = 10.9501 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002533 MOMENT OF INERTIA (Kg-M**2) = 0.000286 STATIC MOMENT, ONE SIDE (IN-LB) = 0.150588 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 = 91.782 INNER LIMIT (NORMALIZED BY RADIUS) = 0.084 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 17800.46 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.