14x4.7SF (14x47SF.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 0.5000 0.2552 0.0000 0.0000 0.2500 0.0000 0.1076 0.0000 0.0538 0.0000 0.0400 0.0000 0.0000 0.1166 0.4759 0.6116 0.0132 -0.5324 0.2535 0.0051 0.1026 1.0319 0.0488 0.0882 0.0442 0.0129 -0.0604 0.2332 0.4725 0.9531 0.0996 -0.9912 0.2734 0.0190 0.0977 3.8888 0.0462 0.0899 0.0555 0.0351 -0.0535 0.3498 0.4886 1.2797 0.3054 -1.1935 0.3064 0.0396 0.0931 7.9106 0.0455 0.0912 0.0707 0.0624 -0.0425 0.4664 0.5227 1.5914 0.6357 -1.0351 0.3493 0.0649 0.0886 12.2403 0.0463 0.0905 0.0893 0.0930 -0.0284 0.5830 0.5722 1.8882 1.0623 -0.5399 0.3989 0.0928 0.0844 16.1722 0.0483 0.0877 0.1116 0.1255 -0.0120 0.6996 0.6332 2.1701 1.5410 0.1933 0.4520 0.1214 0.0804 19.3188 0.0509 0.0828 0.1361 0.1585 0.0057 0.8162 0.7013 2.4372 2.0264 1.0391 0.5056 0.1487 0.0766 21.5606 0.0537 0.0762 0.1608 0.1907 0.0239 0.9328 0.7721 2.6893 2.4783 1.8742 0.5565 0.1728 0.0731 22.9214 0.0564 0.0691 0.1835 0.2208 0.0417 1.0494 0.8412 2.9266 2.8626 2.5153 0.6015 0.1916 0.0697 23.4680 0.0586 0.0635 0.2019 0.2459 0.0571 1.1660 0.9047 3.1489 3.1483 2.9173 0.6376 0.2033 0.0665 23.2551 0.0602 0.0623 0.2138 0.2600 0.0669 1.2862 0.9641 3.3625 3.3625 3.1749 0.6672 0.2096 0.0635 22.5917 0.0612 0.0651 0.2210 0.2636 0.0714 1.4677 1.0492 3.6552 3.6552 3.5276 0.7090 0.2172 0.0593 21.6216 0.0623 0.0680 0.2301 0.2678 0.0779 1.6528 1.1302 3.9164 3.9164 3.8392 0.7480 0.2228 0.0556 20.6632 0.0629 0.0698 0.2372 0.2707 0.0839 1.8378 1.2052 4.1401 4.1401 4.1001 0.7833 0.2263 0.0525 19.7242 0.0632 0.0704 0.2422 0.2722 0.0894 2.0229 1.2743 4.3263 4.3263 4.3142 0.8151 0.2278 0.0498 18.7973 0.0635 0.0705 0.2453 0.2727 0.0943 2.2080 1.3373 4.4750 4.4750 4.4842 0.8432 0.2274 0.0477 17.8777 0.0638 0.0703 0.2465 0.2723 0.0985 2.3931 1.3942 4.5862 4.5862 4.6078 0.8677 0.2250 0.0461 16.9621 0.0643 0.0703 0.2460 0.2714 0.1020 2.5782 1.4447 4.6598 4.6598 4.6884 0.8885 0.2209 0.0451 16.0484 0.0651 0.0708 0.2439 0.2699 0.1047 2.7633 1.4889 4.6960 4.6960 4.7283 0.9058 0.2149 0.0446 15.1348 0.0663 0.0721 0.2403 0.2682 0.1066 2.9483 1.5267 4.7000 4.7000 4.7328 0.9194 0.2073 0.0445 14.2362 0.0679 0.0743 0.2353 0.2660 0.1074 3.1334 1.5579 4.7000 4.7000 4.7309 0.9294 0.1985 0.0445 13.4267 0.0693 0.0770 0.2291 0.2629 0.1064 3.3185 1.5825 4.7000 4.7000 4.7288 0.9357 0.1886 0.0445 12.7028 0.0704 0.0792 0.2218 0.2590 0.1040 3.5036 1.6004 4.7000 4.7000 4.7270 0.9385 0.1779 0.0445 12.0519 0.0712 0.0809 0.2134 0.2543 0.1003 3.6887 1.6115 4.7000 4.7000 4.7255 0.9376 0.1665 0.0445 11.4636 0.0717 0.0818 0.2041 0.2488 0.0956 3.8738 1.6157 4.7000 4.7000 4.7243 0.9330 0.1544 0.0445 10.9294 0.0719 0.0822 0.1939 0.2426 0.0900 4.0588 1.6129 4.7000 4.7000 4.7234 0.9249 0.1420 0.0445 10.4422 0.0718 0.0818 0.1832 0.2356 0.0835 4.2439 1.6030 4.7000 4.7000 4.7230 0.9131 0.1291 0.0445 9.9962 0.0713 0.0808 0.1718 0.2279 0.0765 4.4290 1.5860 4.7000 4.7000 4.7229 0.8977 0.1162 0.0445 9.5864 0.0706 0.0790 0.1600 0.2196 0.0689 4.6141 1.5617 4.7000 4.7000 4.7234 0.8787 0.1032 0.0445 9.2086 0.0695 0.0766 0.1478 0.2105 0.0610 4.7992 1.5300 4.7000 4.7000 4.7244 0.8560 0.0903 0.0445 8.8592 0.0681 0.0736 0.1355 0.2008 0.0529 4.9843 1.4909 4.7000 4.7000 4.7262 0.8297 0.0776 0.0445 8.5351 0.0663 0.0700 0.1230 0.1905 0.0447 5.1693 1.4443 4.7000 4.7000 4.7290 0.7998 0.0653 0.0445 8.2338 0.0643 0.0658 0.1105 0.1796 0.0365 5.3544 1.3900 4.7000 4.7000 4.7328 0.7662 0.0535 0.0445 7.9529 0.0619 0.0611 0.0982 0.1681 0.0285 5.5395 1.3281 4.7000 4.7000 4.7382 0.7291 0.0423 0.0445 7.6904 0.0591 0.0559 0.0861 0.1561 0.0209 5.7246 1.2583 4.7000 4.7000 4.7457 0.6883 0.0319 0.0445 7.4446 0.0560 0.0504 0.0744 0.1437 0.0137 5.9097 1.1806 4.7000 4.7000 4.7549 0.6439 0.0223 0.0445 7.2140 0.0525 0.0446 0.0631 0.1308 0.0070 6.0948 1.0950 4.7000 4.7000 4.7668 0.5958 0.0138 0.0445 6.9971 0.0487 0.0386 0.0524 0.1175 0.0011 6.2798 1.0013 4.7000 4.7000 4.7834 0.5441 0.0064 0.0445 6.7928 0.0446 0.0326 0.0424 0.1038 -0.0040 6.4649 0.8994 4.7000 4.7000 4.8071 0.4888 0.0003 0.0445 6.6001 0.0400 0.0266 0.0333 0.0899 -0.0082 6.6422 0.7861 4.7000 4.7000 4.8370 0.4245 -0.0051 0.0445 6.4254 0.0350 0.0206 0.0242 0.0721 -0.0119 6.6854 0.7486 4.7000 4.7000 4.8465 0.3996 -0.0072 0.0445 6.3843 0.0333 0.0188 0.0208 0.0630 -0.0136 6.7207 0.7134 4.7000 4.7000 4.8550 0.3750 -0.0093 0.0445 6.3510 0.0317 0.0171 0.0175 0.0533 -0.0153 6.7561 0.6736 4.7000 4.7000 4.8702 0.3459 -0.0118 0.0445 6.3180 0.0300 0.0153 0.0136 0.0411 -0.0174 6.7914 0.6280 4.7000 4.7000 4.8932 0.3113 -0.0148 0.0445 6.2854 0.0279 0.0134 0.0089 0.0257 -0.0201 6.8268 0.5748 4.7000 4.7000 4.9247 0.2693 -0.0185 0.0445 6.2531 0.0256 0.0113 0.0033 0.0064 -0.0234 6.8621 0.5110 4.7000 4.7000 4.9719 0.2169 -0.0232 0.0445 6.2212 0.0227 0.0090 -0.0038 -0.0186 -0.0277 6.8975 0.4285 4.7000 4.7000 5.0548 0.1461 -0.0299 0.0445 6.1895 0.0191 0.0064 -0.0135 -0.0536 -0.0338 6.9328 0.3023 4.7000 4.7000 5.2099 0.0320 -0.0407 0.0445 6.1582 0.0135 0.0036 -0.0293 -0.1163 -0.0451 6.9682 0.1579 4.7000 4.7000 5.7512 -0.1000 -0.0521 0.0445 6.1272 0.0070 0.0010 -0.0465 -0.1853 -0.0564 7.0000 0.0279 4.7000 4.7024 4.7024 -0.2187 -0.0630 0.0445 6.1026 0.0012 0.0000 -0.0630 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 1.17 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.056576 TOTAL WEIGHT (Kg) = 0.025658 TOTAL VOLUME (IN**3) = 0.921702 TOTAL PROJECTED AREA (IN**2) = 16.2529 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001863 MOMENT OF INERTIA (Kg-M**2) = 0.000210 STATIC MOMENT, ONE SIDE (IN-LB) = 0.086599 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 = 129.519 INNER LIMIT (NORMALIZED BY RADIUS) = 0.036 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 2706.17 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 6.90, E63 (Transition Start, Airfoil 1) AIRFOIL2: 7.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412