14x8 (14x8.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 0.5000 0.0000 0.0000 0.5750 0.0000 0.4696 0.0000 0.5400 0.0000 0.2500 0.0000 0.0000 0.1500 1.1031 1.3730 0.0161 -0.4766 0.5692 0.0090 0.4662 0.9808 0.5143 0.5045 0.2557 0.0170 -0.0163 0.3000 1.0552 2.1920 0.1249 -0.9170 0.5665 0.0335 0.4562 3.7906 0.4814 0.4958 0.2711 0.0395 -0.0112 0.4500 1.0123 2.9570 0.4054 -1.2025 0.5665 0.0693 0.4394 8.1590 0.4448 0.4798 0.2936 0.0651 -0.0012 0.6000 0.9800 3.6680 0.9191 -1.2170 0.5688 0.1127 0.4172 13.7016 0.4089 0.4562 0.3204 0.0924 0.0129 0.7500 0.9625 4.3250 1.7016 -0.8787 0.5731 0.1599 0.3954 19.8544 0.3806 0.4275 0.3491 0.1203 0.0298 0.9000 0.9601 4.9280 2.7484 -0.1539 0.5789 0.2073 0.3744 25.9211 0.3595 0.3963 0.3770 0.1473 0.0483 1.0500 0.9689 5.4770 3.9981 0.9203 0.5859 0.2511 0.3544 31.2165 0.3434 0.3645 0.4016 0.1724 0.0670 1.2000 0.9822 5.9720 5.3169 2.2117 0.5937 0.2877 0.3354 35.1906 0.3294 0.3336 0.4204 0.1942 0.0848 1.3500 0.9921 6.4130 6.4939 3.4796 0.6019 0.3133 0.3172 37.4369 0.3147 0.3046 0.4309 0.2117 0.1004 1.5000 0.9917 6.8000 7.2567 4.3862 0.6101 0.3242 0.3000 37.5946 0.2975 0.2781 0.4306 0.2240 0.1124 1.6512 0.9847 7.1354 7.6241 4.9041 0.6188 0.3240 0.2836 36.3114 0.2792 0.2543 0.4225 0.2327 0.1208 1.8224 0.9813 7.4491 7.9647 5.4477 0.6298 0.3213 0.2661 34.8213 0.2612 0.2318 0.4122 0.2418 0.1272 1.9948 0.9824 7.6938 8.2309 5.9417 0.6421 0.3161 0.2498 33.2925 0.2454 0.2130 0.4007 0.2501 0.1307 2.1672 0.9874 7.8671 8.4206 6.3709 0.6552 0.3089 0.2347 31.7319 0.2317 0.1974 0.3881 0.2575 0.1318 2.3397 0.9957 7.9691 8.5347 6.7257 0.6688 0.2996 0.2208 30.1382 0.2198 0.1844 0.3745 0.2640 0.1307 2.5121 1.0067 8.0000 8.5741 6.9979 0.6825 0.2884 0.2081 28.5118 0.2095 0.1735 0.3600 0.2694 0.1278 2.6845 1.0198 8.0000 8.5806 7.2170 0.6962 0.2757 0.1967 26.9632 0.2006 0.1644 0.3444 0.2741 0.1229 2.8569 1.0343 8.0000 8.5861 7.4090 0.7095 0.2617 0.1865 25.5629 0.1929 0.1570 0.3281 0.2782 0.1158 3.0293 1.0497 8.0000 8.5916 7.5740 0.7221 0.2465 0.1775 24.2938 0.1863 0.1510 0.3108 0.2815 0.1067 3.2017 1.0652 8.0000 8.5978 7.7120 0.7336 0.2300 0.1698 23.1414 0.1809 0.1462 0.2928 0.2841 0.0958 3.3741 1.0804 8.0000 8.6056 7.8231 0.7439 0.2123 0.1633 22.0932 0.1764 0.1427 0.2741 0.2858 0.0833 3.5466 1.0945 8.0000 8.6158 7.9073 0.7525 0.1934 0.1580 21.1386 0.1729 0.1401 0.2547 0.2866 0.0694 3.7190 1.1070 8.0000 8.6291 7.9645 0.7592 0.1734 0.1539 20.2685 0.1704 0.1386 0.2346 0.2864 0.0542 3.8914 1.1171 8.0000 8.6462 7.9948 0.7638 0.1523 0.1511 19.4749 0.1688 0.1380 0.2140 0.2852 0.0378 4.0638 1.1244 8.0000 8.6676 8.0000 0.7658 0.1301 0.1494 18.7502 0.1680 0.1381 0.1928 0.2829 0.0204 4.2362 1.1281 8.0000 8.6894 8.0000 0.7650 0.1076 0.1480 18.0799 0.1670 0.1376 0.1711 0.2795 0.0027 4.4086 1.1275 8.0000 8.7106 8.0001 0.7610 0.0849 0.1466 17.4563 0.1653 0.1361 0.1490 0.2749 -0.0152 4.5810 1.1222 8.0000 8.7310 8.0001 0.7537 0.0622 0.1451 16.8743 0.1629 0.1335 0.1265 0.2691 -0.0330 4.7534 1.1113 8.0000 8.7506 8.0001 0.7427 0.0396 0.1437 16.3298 0.1597 0.1296 0.1037 0.2620 -0.0506 4.9259 1.0943 8.0000 8.7691 8.0000 0.7277 0.0172 0.1423 15.8191 0.1557 0.1244 0.0806 0.2537 -0.0680 5.0983 1.0706 8.0000 8.7866 8.0000 0.7084 -0.0050 0.1408 15.3387 0.1508 0.1179 0.0573 0.2440 -0.0850 5.2707 1.0395 8.0000 8.8028 8.0000 0.6845 -0.0269 0.1394 14.8856 0.1449 0.1101 0.0338 0.2330 -0.1015 5.4431 1.0003 8.0000 8.8174 8.0000 0.6557 -0.0484 0.1379 14.4571 0.1380 0.1009 0.0101 0.2207 -0.1175 5.6155 0.9525 8.0000 8.8302 8.0000 0.6218 -0.0693 0.1365 14.0505 0.1300 0.0906 -0.0136 0.2070 -0.1327 5.7879 0.8954 8.0000 8.8406 8.0000 0.5824 -0.0898 0.1351 13.6633 0.1209 0.0793 -0.0374 0.1919 -0.1473 5.9603 0.8283 8.0000 8.8478 8.0000 0.5372 -0.1096 0.1336 13.2928 0.1107 0.0672 -0.0611 0.1754 -0.1609 6.1328 0.7506 7.9789 8.8295 7.9789 0.4859 -0.1287 0.1322 12.9059 0.0992 0.0546 -0.0848 0.1574 -0.1735 6.3052 0.6617 7.8882 8.7425 7.8833 0.4283 -0.1471 0.1308 12.4444 0.0865 0.0421 -0.1083 0.1379 -0.1849 6.4776 0.5613 7.7263 8.7110 7.6611 0.3641 -0.1628 0.1293 12.0807 0.0726 0.0300 -0.1311 0.1170 -0.1951 6.6429 0.4537 7.5041 8.8184 7.3715 0.2960 -0.1755 0.1279 11.9299 0.0580 0.0194 -0.1520 0.0955 -0.2035 6.6854 0.4241 7.4363 8.8725 7.2932 0.2774 -0.1785 0.1276 11.9269 0.0541 0.0169 -0.1572 0.0898 -0.2054 6.7207 0.3988 7.3767 8.9260 7.2285 0.2616 -0.1810 0.1273 11.9354 0.0508 0.0150 -0.1615 0.0850 -0.2070 6.7561 0.3730 7.3140 8.9866 7.1649 0.2455 -0.1835 0.1270 11.9531 0.0474 0.0131 -0.1659 0.0801 -0.2085 6.7914 0.3466 7.2484 9.0630 7.1018 0.2291 -0.1860 0.1267 11.9908 0.0439 0.0113 -0.1701 0.0751 -0.2099 6.8268 0.3196 7.1797 9.1369 7.0423 0.2124 -0.1885 0.1264 12.0250 0.0404 0.0096 -0.1745 0.0701 -0.2114 6.8621 0.2920 7.1081 9.2138 6.9858 0.1954 -0.1912 0.1261 12.0626 0.0368 0.0080 -0.1789 0.0651 -0.2128 6.8975 0.2589 7.0334 9.2913 6.9338 0.1733 -0.1950 0.1258 12.1006 0.0326 0.0063 -0.1845 0.0574 -0.2148 6.9328 0.2129 6.9558 9.3637 6.9680 0.1389 -0.2016 0.1255 12.1317 0.0267 0.0043 -0.1933 0.0430 -0.2185 6.9682 0.1378 6.8751 9.4209 7.3585 0.0763 -0.2143 0.1252 12.1435 0.0173 0.0018 -0.2092 0.0134 -0.2258 7.0000 0.0088 6.8000 6.8001 6.8000 -0.0396 -0.2393 0.1250 8.7889 0.0011 0.0000 -0.2393 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 1.50 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.162027 TOTAL WEIGHT (Kg) = 0.073482 TOTAL VOLUME (IN**3) = 2.639633 TOTAL PROJECTED AREA (IN**2) = 12.4014 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003295 MOMENT OF INERTIA (Kg-M**2) = 0.000372 STATIC MOMENT, ONE SIDE (IN-LB) = 0.176532 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 = 87.762 INNER LIMIT (NORMALIZED BY RADIUS) = 0.082 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14090.30 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.