13x13N (13x13N.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 1.1500 0.2845 0.0000 0.0000 0.5750 0.0000 0.4050 0.0000 0.4657 0.0000 0.0400 0.0000 0.0000 0.1625 1.0968 1.4378 0.0176 -0.8003 0.5666 0.0071 0.3856 0.9850 0.4230 0.4499 0.0481 0.0103 -0.1797 0.3250 1.0386 2.5363 0.1377 -1.5600 0.5580 0.0264 0.3672 3.8579 0.3813 0.4398 0.0700 0.0325 -0.1697 0.4875 0.9827 3.5800 0.4560 -2.1183 0.5497 0.0545 0.3495 8.4676 0.3435 0.4208 0.1015 0.0579 -0.1540 0.6500 0.9371 4.5688 1.0586 -2.3062 0.5423 0.0882 0.3328 14.5313 0.3118 0.3930 0.1393 0.0852 -0.1337 0.8125 0.9080 5.5029 2.0123 -1.9806 0.5362 0.1246 0.3168 21.5132 0.2877 0.3602 0.1802 0.1129 -0.1107 0.9750 0.8979 6.3821 3.3434 -1.0474 0.5318 0.1605 0.3018 28.6241 0.2710 0.3259 0.2204 0.1395 -0.0863 1.1375 0.9040 7.2065 5.0043 0.4891 0.5298 0.1930 0.2876 34.9993 0.2600 0.2929 0.2565 0.1640 -0.0626 1.3000 0.9192 7.9761 6.8347 2.4632 0.5305 0.2191 0.2742 39.9209 0.2520 0.2632 0.2848 0.1850 -0.0415 1.4625 0.9345 8.6908 8.5376 4.4955 0.5344 0.2356 0.2617 42.8951 0.2445 0.2383 0.3016 0.2014 -0.0255 1.6250 0.9419 9.3508 9.7059 6.0072 0.5420 0.2397 0.2500 43.5495 0.2355 0.2189 0.3033 0.2122 -0.0171 1.7869 0.9426 9.9538 10.3423 6.9126 0.5524 0.2344 0.2392 42.6500 0.2255 0.2034 0.2943 0.2192 -0.0151 1.9388 0.9437 10.4700 10.8834 7.7375 0.5629 0.2284 0.2299 41.7781 0.2169 0.1902 0.2851 0.2261 -0.0145 2.0901 0.9450 10.9366 11.3730 8.5294 0.5738 0.2213 0.2213 40.8933 0.2091 0.1783 0.2753 0.2330 -0.0151 2.2414 0.9464 11.3557 11.8134 9.2809 0.5850 0.2132 0.2134 39.9912 0.2020 0.1681 0.2648 0.2393 -0.0172 2.3927 0.9476 11.7272 12.2049 9.9823 0.5963 0.2042 0.2063 39.0711 0.1955 0.1593 0.2538 0.2449 -0.0205 2.5440 0.9485 12.0513 12.5478 10.6250 0.6074 0.1942 0.2000 38.1324 0.1897 0.1515 0.2420 0.2502 -0.0247 2.6953 0.9488 12.3278 12.8425 11.2012 0.6181 0.1832 0.1943 37.1748 0.1844 0.1444 0.2297 0.2553 -0.0297 2.8466 0.9483 12.5568 13.0886 11.7042 0.6281 0.1714 0.1895 36.1967 0.1797 0.1376 0.2167 0.2607 -0.0351 2.9978 0.9469 12.7383 13.2876 12.1282 0.6374 0.1585 0.1853 35.2005 0.1755 0.1313 0.2031 0.2663 -0.0411 3.1491 0.9443 12.8722 13.4402 12.4684 0.6456 0.1447 0.1819 34.1865 0.1717 0.1255 0.1888 0.2719 -0.0476 3.3004 0.9403 12.9587 13.5460 12.7211 0.6525 0.1299 0.1792 33.1535 0.1685 0.1206 0.1739 0.2768 -0.0547 3.4517 0.9347 12.9976 13.6034 12.8836 0.6580 0.1144 0.1766 32.0974 0.1651 0.1160 0.1584 0.2812 -0.0623 3.6030 0.9273 13.0000 13.6227 12.9650 0.6617 0.0983 0.1740 31.0374 0.1614 0.1116 0.1422 0.2848 -0.0704 3.7543 0.9179 13.0000 13.6382 12.9988 0.6636 0.0818 0.1715 30.0348 0.1574 0.1073 0.1254 0.2879 -0.0793 3.9056 0.9063 13.0000 13.6524 13.0002 0.6633 0.0648 0.1689 29.0890 0.1531 0.1030 0.1079 0.2901 -0.0890 4.0569 0.8923 13.0000 13.6651 13.0005 0.6606 0.0473 0.1664 28.1954 0.1484 0.0982 0.0897 0.2912 -0.0992 4.2082 0.8755 13.0000 13.6762 13.0008 0.6553 0.0294 0.1638 27.3496 0.1434 0.0931 0.0709 0.2910 -0.1099 4.3595 0.8560 13.0000 13.6853 13.0008 0.6473 0.0110 0.1612 26.5477 0.1380 0.0876 0.0515 0.2894 -0.1210 4.5108 0.8333 13.0000 13.6925 13.0007 0.6362 -0.0079 0.1587 25.7859 0.1322 0.0817 0.0315 0.2863 -0.1325 4.6621 0.8074 13.0000 13.6973 13.0007 0.6219 -0.0272 0.1561 25.0608 0.1261 0.0755 0.0108 0.2814 -0.1444 4.8134 0.7780 13.0000 13.6993 13.0006 0.6041 -0.0469 0.1536 24.3692 0.1195 0.0690 -0.0105 0.2747 -0.1567 4.9647 0.7449 13.0000 13.6982 13.0006 0.5827 -0.0671 0.1510 23.7077 0.1125 0.0623 -0.0324 0.2660 -0.1694 5.1159 0.7078 13.0000 13.6931 13.0005 0.5573 -0.0877 0.1484 23.0734 0.1051 0.0554 -0.0551 0.2552 -0.1824 5.2672 0.6666 13.0000 13.6832 13.0004 0.5279 -0.1088 0.1459 22.4628 0.0972 0.0484 -0.0783 0.2421 -0.1958 5.4185 0.6211 13.0000 13.6672 13.0004 0.4941 -0.1303 0.1433 21.8724 0.0890 0.0414 -0.1022 0.2267 -0.2095 5.5698 0.5710 12.9612 13.6041 12.9615 0.4557 -0.1524 0.1408 21.2426 0.0804 0.0344 -0.1268 0.2086 -0.2233 5.7211 0.5161 12.8462 13.4533 12.8464 0.4126 -0.1749 0.1382 20.5186 0.0713 0.0278 -0.1520 0.1878 -0.2372 5.8724 0.4563 12.6551 13.2098 12.6553 0.3645 -0.1981 0.1356 19.6980 0.0619 0.0214 -0.1778 0.1642 -0.2512 6.0237 0.3912 12.3879 12.8641 12.3880 0.3112 -0.2217 0.1331 18.7723 0.0521 0.0156 -0.2043 0.1376 -0.2654 6.1688 0.3237 12.0600 12.4188 12.0601 0.2550 -0.2447 0.1306 17.7656 0.0423 0.0106 -0.2303 0.1094 -0.2795 6.2078 0.3047 11.9599 12.2759 11.9600 0.2390 -0.2510 0.1300 17.4701 0.0396 0.0094 -0.2374 0.1013 -0.2833 6.2407 0.2884 11.8718 12.1464 11.8719 0.2253 -0.2563 0.1294 17.2114 0.0373 0.0084 -0.2434 0.0944 -0.2866 6.2735 0.2719 11.7801 12.0076 11.7801 0.2112 -0.2616 0.1289 16.9421 0.0350 0.0075 -0.2494 0.0873 -0.2898 6.3063 0.2550 11.6848 11.8580 11.6848 0.1970 -0.2669 0.1283 16.6607 0.0327 0.0066 -0.2555 0.0801 -0.2932 6.3391 0.2379 11.5859 11.6962 11.5859 0.1824 -0.2723 0.1277 16.3650 0.0304 0.0058 -0.2616 0.0727 -0.2965 6.3720 0.2205 11.4834 11.5197 11.4834 0.1675 -0.2776 0.1272 16.0522 0.0280 0.0050 -0.2677 0.0652 -0.2999 6.4048 0.2010 11.3773 11.3255 11.3773 0.1506 -0.2835 0.1266 15.7182 0.0255 0.0041 -0.2745 0.0567 -0.3036 6.4376 0.1707 11.2677 11.1087 11.3317 0.1233 -0.2922 0.1261 15.3568 0.0215 0.0030 -0.2845 0.0427 -0.3091 6.4705 0.1165 11.1545 10.8622 11.7084 0.0728 -0.3068 0.1255 14.9588 0.0146 0.0014 -0.3015 0.0164 -0.3185 6.5000 0.0075 11.0495 11.0495 11.0495 -0.0310 -0.3345 0.1250 15.1390 0.0009 0.0000 -0.3345 0.0000 0.0000 RADIUS: 6.50 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 1.62 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.127475 TOTAL WEIGHT (Kg) = 0.057812 TOTAL VOLUME (IN**3) = 2.076738 TOTAL PROJECTED AREA (IN**2) = 9.2288 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001880 MOMENT OF INERTIA (Kg-M**2) = 0.000212 STATIC MOMENT, ONE SIDE (IN-LB) = 0.117823 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 = 71.414 INNER LIMIT (NORMALIZED BY RADIUS) = 0.088 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 18170.66 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.