16x13 (16x13.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 1.2500 -2.0480 0.0000 0.0000 0.6250 0.0000 0.4913 0.0000 0.6142 0.0000 0.1600 0.0000 0.0000 0.1920 1.1912 -0.1835 0.0246 -1.0346 0.6184 0.0074 0.4591 1.1702 0.5469 0.6887 0.1656 0.0174 -0.1652 0.3840 1.1342 1.5577 0.1922 -1.9947 0.6174 0.0273 0.4284 4.5553 0.4859 0.6660 0.1808 0.0468 -0.1617 0.5760 1.0872 3.1757 0.6293 -2.6520 0.6211 0.0565 0.3993 9.8637 0.4341 0.6331 0.2026 0.0811 -0.1543 0.7680 1.0591 4.6704 1.4380 -2.8009 0.6289 0.0919 0.3717 16.5946 0.3937 0.5928 0.2288 0.1181 -0.1437 0.9600 1.0554 6.0418 2.6797 -2.2884 0.6399 0.1306 0.3457 23.9536 0.3648 0.5489 0.2570 0.1559 -0.1310 1.1520 1.0754 7.2899 4.3492 -1.0494 0.6536 0.1694 0.3212 31.0001 0.3454 0.5045 0.2849 0.1926 -0.1170 1.3440 1.1127 8.4148 6.3463 0.8463 0.6690 0.2055 0.2982 36.9259 0.3318 0.4619 0.3098 0.2263 -0.1026 1.5360 1.1562 9.4164 8.4543 3.1516 0.6855 0.2356 0.2769 41.2187 0.3201 0.4228 0.3293 0.2552 -0.0890 1.7280 1.1943 10.2947 10.3421 5.4296 0.7024 0.2569 0.2570 43.6076 0.3070 0.3881 0.3408 0.2775 -0.0773 1.9200 1.2171 11.0498 11.6060 7.0982 0.7189 0.2663 0.2387 43.8923 0.2906 0.3580 0.3415 0.2918 -0.0686 2.1119 1.2280 11.6811 12.2679 8.1068 0.7350 0.2666 0.2220 42.7547 0.2726 0.3310 0.3344 0.3002 -0.0625 2.3012 1.2389 12.1836 12.7884 9.0227 0.7511 0.2650 0.2070 41.4911 0.2565 0.3062 0.3268 0.3075 -0.0571 2.4905 1.2500 12.5659 13.1819 9.8423 0.7673 0.2619 0.1936 40.1105 0.2419 0.2834 0.3185 0.3138 -0.0521 2.6797 1.2607 12.8285 13.4503 10.5465 0.7832 0.2571 0.1816 38.6194 0.2289 0.2624 0.3096 0.3190 -0.0473 2.8690 1.2710 12.9713 13.5952 11.1185 0.7987 0.2508 0.1711 37.0232 0.2175 0.2435 0.3000 0.3232 -0.0427 3.0582 1.2805 13.0000 13.6240 11.5490 0.8136 0.2429 0.1622 35.3373 0.2077 0.2266 0.2899 0.3264 -0.0383 3.2474 1.2889 13.0000 13.6251 11.9050 0.8275 0.2338 0.1547 33.7333 0.1994 0.2121 0.2791 0.3295 -0.0352 3.4367 1.2958 13.0000 13.6291 12.2110 0.8403 0.2235 0.1488 32.2590 0.1928 0.1999 0.2678 0.3326 -0.0338 3.6259 1.3012 13.0000 13.6372 12.4670 0.8518 0.2120 0.1443 30.9040 0.1878 0.1902 0.2558 0.3357 -0.0340 3.8152 1.3045 13.0000 13.6503 12.6730 0.8617 0.1991 0.1414 29.6590 0.1845 0.1829 0.2431 0.3386 -0.0359 4.0044 1.3057 13.0000 13.6696 12.8290 0.8697 0.1849 0.1400 28.5151 0.1828 0.1781 0.2298 0.3411 -0.0392 4.1937 1.3043 13.0000 13.6921 12.9348 0.8758 0.1698 0.1393 27.4580 0.1817 0.1746 0.2159 0.3434 -0.0439 4.3829 1.3001 13.0000 13.7146 12.9906 0.8795 0.1542 0.1386 26.4740 0.1801 0.1715 0.2014 0.3452 -0.0496 4.5721 1.2928 13.0000 13.7370 13.0000 0.8808 0.1382 0.1379 25.5562 0.1782 0.1685 0.1862 0.3464 -0.0563 4.7614 1.2821 13.0000 13.7591 13.0001 0.8793 0.1217 0.1371 24.6985 0.1758 0.1648 0.1704 0.3467 -0.0635 4.9506 1.2676 13.0000 13.7810 13.0002 0.8748 0.1047 0.1364 23.8952 0.1729 0.1602 0.1539 0.3459 -0.0713 5.1399 1.2491 13.0000 13.8026 13.0003 0.8672 0.0874 0.1357 23.1416 0.1695 0.1547 0.1368 0.3438 -0.0796 5.3291 1.2262 13.0000 13.8237 13.0003 0.8561 0.0696 0.1350 22.4333 0.1656 0.1483 0.1190 0.3404 -0.0883 5.5183 1.1987 13.0000 13.8444 13.0002 0.8414 0.0515 0.1343 21.7661 0.1610 0.1410 0.1006 0.3356 -0.0973 5.7076 1.1662 13.0000 13.8643 13.0002 0.8228 0.0331 0.1336 21.1367 0.1558 0.1328 0.0816 0.3292 -0.1066 5.8968 1.1284 13.0000 13.8835 13.0002 0.8001 0.0143 0.1329 20.5417 0.1499 0.1237 0.0619 0.3211 -0.1163 6.0861 1.0850 13.0000 13.9016 13.0001 0.7731 -0.0049 0.1322 19.9781 0.1434 0.1138 0.0416 0.3112 -0.1262 6.2753 1.0358 13.0000 13.9186 13.0001 0.7415 -0.0243 0.1315 19.4432 0.1362 0.1031 0.0206 0.2994 -0.1364 6.4646 0.9803 13.0000 13.9340 13.0001 0.7051 -0.0440 0.1308 18.9345 0.1282 0.0919 -0.0010 0.2856 -0.1467 6.6538 0.9183 13.0000 13.9473 13.0001 0.6636 -0.0640 0.1300 18.4493 0.1194 0.0803 -0.0233 0.2698 -0.1572 6.8430 0.8495 13.0000 13.9580 13.0001 0.6169 -0.0842 0.1293 17.9852 0.1099 0.0684 -0.0462 0.2517 -0.1679 7.0323 0.7736 12.9852 13.9500 12.9853 0.5648 -0.1047 0.1286 17.5218 0.0995 0.0565 -0.0697 0.2312 -0.1786 7.2215 0.6902 12.8625 13.8280 12.8626 0.5069 -0.1256 0.1279 16.9489 0.0883 0.0448 -0.0939 0.2082 -0.1889 7.4108 0.5990 12.6155 13.5727 12.6155 0.4430 -0.1468 0.1272 16.2509 0.0762 0.0336 -0.1187 0.1826 -0.1991 7.5922 0.5041 12.2619 13.1973 12.2619 0.3760 -0.1674 0.1265 15.4643 0.0638 0.0238 -0.1431 0.1557 -0.2088 7.6404 0.4776 12.1489 13.0750 12.1489 0.3572 -0.1728 0.1263 15.2356 0.0603 0.0213 -0.1497 0.1481 -0.2114 7.6808 0.4549 12.0478 12.9647 12.0479 0.3412 -0.1774 0.1262 15.0370 0.0574 0.0194 -0.1553 0.1416 -0.2136 7.7212 0.4319 11.9411 12.8470 11.9412 0.3248 -0.1821 0.1260 14.8321 0.0544 0.0175 -0.1609 0.1351 -0.2158 7.7616 0.4085 11.8288 12.7216 11.8288 0.3081 -0.1867 0.1259 14.6204 0.0514 0.0156 -0.1665 0.1283 -0.2181 7.8020 0.3846 11.7108 12.5881 11.7108 0.2911 -0.1913 0.1257 14.4017 0.0484 0.0139 -0.1721 0.1215 -0.2203 7.8424 0.3553 11.5871 12.4470 11.5881 0.2688 -0.1971 0.1256 14.1764 0.0446 0.0118 -0.1793 0.1118 -0.2235 7.8828 0.3156 11.4577 12.2978 11.4723 0.2366 -0.2053 0.1254 13.9441 0.0396 0.0093 -0.1894 0.0967 -0.2283 7.9232 0.2594 11.3227 12.1390 11.4041 0.1885 -0.2172 0.1253 13.7035 0.0325 0.0063 -0.2040 0.0729 -0.2358 7.9636 0.1585 11.1820 11.9708 11.5784 0.0968 -0.2391 0.1251 13.4545 0.0198 0.0024 -0.2310 0.0253 -0.2505 8.0000 0.0131 11.0506 11.0507 11.0505 -0.0389 -0.2709 0.1250 12.3990 0.0016 0.0000 -0.2709 0.0000 0.0000 RADIUS: 8.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 1.92 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.242944 TOTAL WEIGHT (Kg) = 0.110179 TOTAL VOLUME (IN**3) = 3.957866 TOTAL PROJECTED AREA (IN**2) = 15.4440 MOMENT OF INERTIA (SNAIL-IN**2) = 0.005822 MOMENT OF INERTIA (Kg-M**2) = 0.000658 STATIC MOMENT, ONE SIDE (IN-LB) = 0.285908 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 = 84.494 INNER LIMIT (NORMALIZED BY RADIUS) = 0.078 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 13096.70 BASED ON MODULUS (MILLION) = 2.80 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.