10x10M-JK (10x10M-JK.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 1.2200 0.8248 0.0000 0.0000 0.6100 0.0000 0.3260 0.0000 0.3978 0.0000 0.3000 0.0000 0.0000 0.0700 1.2325 1.2149 0.0795 -0.1740 0.6069 0.1076 0.3184 10.2450 0.3924 0.6563 0.3015 -0.0002 -0.0239 0.1400 1.2561 1.6184 0.2916 -0.2269 0.5985 0.1901 0.3109 18.3405 0.3905 0.6471 0.3049 0.0034 -0.0277 0.2100 1.2757 2.0331 0.6073 -0.1745 0.5862 0.2507 0.3036 24.7149 0.3873 0.6168 0.3080 0.0113 -0.0325 0.2800 1.2831 2.4571 1.0090 -0.0225 0.5711 0.2927 0.2965 29.8365 0.3804 0.5682 0.3141 0.0238 -0.0377 0.3500 1.2735 2.8884 1.4912 0.2255 0.5544 0.3193 0.2895 34.1416 0.3686 0.5070 0.3299 0.0416 -0.0425 0.4200 1.2443 3.3250 2.0660 0.5753 0.5374 0.3337 0.2827 38.0574 0.3517 0.4378 0.3429 0.0655 -0.0455 0.4900 1.1926 3.7648 2.7842 1.0789 0.5212 0.3390 0.2760 42.1242 0.3292 0.3642 0.3491 0.0979 -0.0439 0.5600 1.1323 4.2059 3.6762 1.8195 0.5071 0.3384 0.2695 46.2552 0.3051 0.2970 0.3508 0.1325 -0.0364 0.6300 1.0985 4.6461 4.5118 2.6215 0.4963 0.3352 0.2631 48.7379 0.2891 0.2550 0.3513 0.1504 -0.0292 0.7000 1.0947 5.0837 5.0824 3.1906 0.4900 0.3326 0.2570 49.1276 0.2813 0.2379 0.3511 0.1493 -0.0257 0.7734 1.1027 5.5373 5.5373 3.6557 0.4869 0.3316 0.2507 48.7302 0.2764 0.2314 0.3503 0.1409 -0.0228 0.9053 1.1182 6.3316 6.3316 4.5165 0.4819 0.3293 0.2398 48.0651 0.2681 0.2208 0.3484 0.1263 -0.0197 1.0406 1.1352 7.1070 7.1070 5.4056 0.4776 0.3262 0.2292 47.3879 0.2602 0.2115 0.3457 0.1114 -0.0186 1.1758 1.1512 7.8279 7.8279 6.2604 0.4736 0.3224 0.2192 46.6564 0.2524 0.2032 0.3424 0.0968 -0.0187 1.3111 1.1651 8.4800 8.4800 7.0364 0.4699 0.3179 0.2099 45.8297 0.2445 0.1962 0.3384 0.0827 -0.0196 1.4464 1.1771 9.0487 9.0487 7.6924 0.4662 0.3126 0.2011 44.8763 0.2367 0.1911 0.3337 0.0686 -0.0211 1.5817 1.1872 9.5195 9.5195 8.2059 0.4623 0.3065 0.1929 43.7682 0.2291 0.1875 0.3283 0.0545 -0.0226 1.7169 1.1953 9.8778 9.8778 8.6176 0.4578 0.2996 0.1854 42.4788 0.2216 0.1836 0.3222 0.0396 -0.0229 1.8522 1.2014 10.1093 10.1093 8.9153 0.4526 0.2919 0.1784 40.9796 0.2144 0.1793 0.3154 0.0236 -0.0219 1.9875 1.2056 10.1993 10.1993 9.0793 0.4464 0.2834 0.1721 39.2402 0.2075 0.1747 0.3080 0.0062 -0.0189 2.1228 1.2079 10.2000 10.2000 9.1521 0.4391 0.2743 0.1663 37.4070 0.2009 0.1703 0.3000 -0.0118 -0.0150 2.2580 1.2081 10.2000 10.2000 9.2146 0.4303 0.2647 0.1612 35.7137 0.1947 0.1661 0.2916 -0.0296 -0.0117 2.3933 1.2065 10.2000 10.2000 9.2690 0.4198 0.2546 0.1566 34.1490 0.1890 0.1618 0.2827 -0.0473 -0.0092 2.5286 1.2028 10.2000 10.2000 9.3152 0.4074 0.2441 0.1527 32.7009 0.1836 0.1576 0.2732 -0.0652 -0.0075 2.6639 1.1973 10.2000 10.2000 9.3527 0.3928 0.2332 0.1493 31.3585 0.1788 0.1534 0.2631 -0.0837 -0.0066 2.7991 1.1897 10.2000 10.2000 9.3810 0.3759 0.2217 0.1466 30.1119 0.1744 0.1492 0.2525 -0.1031 -0.0064 2.9344 1.1802 10.2000 10.2000 9.3999 0.3563 0.2098 0.1444 28.9523 0.1705 0.1451 0.2414 -0.1237 -0.0071 3.0697 1.1688 10.2000 10.2000 9.4173 0.3338 0.1973 0.1424 27.8718 0.1665 0.1407 0.2296 -0.1458 -0.0088 3.2050 1.1554 10.2000 10.2000 9.4366 0.3082 0.1843 0.1405 26.8631 0.1623 0.1360 0.2173 -0.1697 -0.0113 3.3402 1.1400 10.2000 10.2000 9.4581 0.2793 0.1709 0.1385 25.9201 0.1579 0.1310 0.2045 -0.1957 -0.0146 3.4755 1.1227 10.2000 10.2000 9.4819 0.2468 0.1570 0.1365 25.0368 0.1532 0.1256 0.1911 -0.2242 -0.0187 3.6108 1.1034 10.2000 10.2000 9.5083 0.2105 0.1427 0.1345 24.2083 0.1484 0.1200 0.1771 -0.2553 -0.0235 3.7461 1.0822 10.2000 10.2000 9.5375 0.1701 0.1281 0.1325 23.4298 0.1434 0.1141 0.1626 -0.2893 -0.0290 3.8813 1.0590 10.2000 10.2000 9.5695 0.1254 0.1130 0.1305 22.6972 0.1382 0.1081 0.1475 -0.3266 -0.0352 4.0166 1.0339 10.2000 10.2000 9.6046 0.0761 0.0974 0.1285 22.0069 0.1329 0.1018 0.1319 -0.3673 -0.0422 4.1519 1.0068 10.2000 10.2000 9.6431 0.0221 0.0815 0.1265 21.3554 0.1274 0.0955 0.1157 -0.4118 -0.0498 4.2872 0.9778 10.2000 10.2000 9.6826 -0.0369 0.0651 0.1245 20.7397 0.1218 0.0890 0.0989 -0.4601 -0.0581 4.4224 0.9467 10.2000 10.2000 9.7033 -0.1012 0.0483 0.1225 20.1570 0.1160 0.0824 0.0816 -0.5122 -0.0668 4.5577 0.9054 10.1973 10.1990 9.5949 -0.1741 0.0302 0.1206 19.6031 0.1092 0.0742 0.0615 -0.5677 -0.0777 4.6872 0.8315 10.1720 10.1837 9.0891 -0.2569 0.0103 0.1191 19.0747 0.0990 0.0618 0.0363 -0.6184 -0.0905 4.7179 0.7996 10.1620 10.1822 8.9058 -0.2835 0.0035 0.1191 18.9568 0.0952 0.0571 0.0276 -0.6311 -0.0943 4.7429 0.7671 10.1528 10.1832 8.7488 -0.3085 -0.0031 0.1192 18.8660 0.0914 0.0525 0.0193 -0.6418 -0.0978 4.7678 0.7283 10.1426 10.1871 8.5818 -0.3364 -0.0105 0.1194 18.7809 0.0870 0.0473 0.0100 -0.6528 -0.1015 4.7928 0.6837 10.1314 10.1946 8.4034 -0.3668 -0.0186 0.1198 18.7026 0.0819 0.0418 -0.0001 -0.6638 -0.1051 4.8177 0.6341 10.1192 10.2063 8.2142 -0.3989 -0.0272 0.1203 18.6324 0.0763 0.0360 -0.0107 -0.6742 -0.1086 4.8427 0.5797 10.1060 10.2240 8.0166 -0.4324 -0.0362 0.1210 18.5729 0.0702 0.0302 -0.0217 -0.6840 -0.1117 4.8676 0.5184 10.0919 10.2527 7.8191 -0.4686 -0.0458 0.1219 18.5325 0.0632 0.0242 -0.0335 -0.6936 -0.1147 4.8926 0.4433 10.0767 10.3078 7.6503 -0.5112 -0.0574 0.1230 18.5369 0.0545 0.0178 -0.0474 -0.7035 -0.1176 4.9175 0.3326 10.0605 10.4602 7.6443 -0.5716 -0.0744 0.1243 18.7031 0.0413 0.0101 -0.0674 -0.7161 -0.1212 4.9400 0.0533 10.0451 11.7057 11.7057 -0.7180 -0.1208 0.1256 20.6630 0.0067 0.0000 -0.1208 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.61 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.115733 TOTAL WEIGHT (Kg) = 0.052486 TOTAL VOLUME (IN**3) = 1.885432 TOTAL PROJECTED AREA (IN**2) = 9.0795 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001375 MOMENT OF INERTIA (Kg-M**2) = 0.000155 STATIC MOMENT, ONE SIDE (IN-LB) = 0.095666 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 = 155.720 INNER LIMIT (NORMALIZED BY RADIUS) = 0.122 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 20303.06 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.50, APC12 (Transition Start, Airfoil 1) AIRFOIL2: 4.90, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412