8x4 (8x4.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 0.8000 1.1656 0.0000 0.0000 0.4000 0.0000 0.4097 0.0000 0.3277 0.0000 0.1300 0.0000 0.0000 0.1160 0.7658 1.4849 0.0095 -0.3625 0.3948 0.0036 0.3807 0.7458 0.2916 0.2129 0.1315 0.0105 -0.0313 0.2320 0.7341 1.7850 0.0733 -0.6970 0.3906 0.0133 0.3536 2.8774 0.2596 0.2067 0.1356 0.0227 -0.0308 0.3480 0.7071 2.0662 0.2365 -0.9147 0.3875 0.0275 0.3282 6.1724 0.2321 0.1961 0.1409 0.0357 -0.0294 0.4640 0.6872 2.3282 0.5305 -0.9292 0.3855 0.0445 0.3046 10.3126 0.2093 0.1810 0.1468 0.0491 -0.0270 0.5800 0.6760 2.5712 0.9674 -0.6882 0.3845 0.0630 0.2827 14.8672 0.1911 0.1635 0.1532 0.0622 -0.0232 0.6960 0.6734 2.7951 1.5337 -0.1816 0.3844 0.0813 0.2626 19.3268 0.1769 0.1452 0.1598 0.0745 -0.0181 0.8120 0.6779 2.9999 2.1848 0.5473 0.3854 0.0980 0.2443 23.1820 0.1656 0.1276 0.1660 0.0855 -0.0117 0.9280 0.6869 3.1857 2.8431 1.3947 0.3873 0.1115 0.2278 25.9941 0.1565 0.1117 0.1708 0.0945 -0.0043 1.0440 0.6973 3.3524 3.4023 2.1990 0.3901 0.1204 0.2130 27.4143 0.1485 0.0985 0.1731 0.1008 0.0033 1.1600 0.7064 3.5000 3.7380 2.7555 0.3937 0.1231 0.2000 27.1516 0.1413 0.0888 0.1717 0.1026 0.0098 1.2745 0.7134 3.6270 3.8758 3.0533 0.3979 0.1212 0.1889 25.8270 0.1348 0.0820 0.1674 0.1013 0.0142 1.3630 0.7175 3.7125 3.9679 3.2599 0.4012 0.1190 0.1815 24.8589 0.1302 0.0773 0.1637 0.1010 0.0168 1.4501 0.7203 3.7857 4.0476 3.4418 0.4045 0.1162 0.1752 23.9531 0.1262 0.0731 0.1597 0.1013 0.0186 1.5371 0.7219 3.8482 4.1168 3.6005 0.4076 0.1129 0.1699 23.0868 0.1227 0.0695 0.1554 0.1021 0.0198 1.6241 0.7223 3.8999 4.1760 3.7345 0.4106 0.1089 0.1656 22.2553 0.1196 0.0664 0.1509 0.1033 0.0203 1.7112 0.7215 3.9409 4.2254 3.8423 0.4132 0.1043 0.1623 21.4547 0.1171 0.0638 0.1460 0.1050 0.0202 1.7982 0.7195 3.9711 4.2653 3.9227 0.4155 0.0992 0.1600 20.6820 0.1151 0.0617 0.1409 0.1069 0.0194 1.8852 0.7162 3.9907 4.2951 3.9750 0.4173 0.0936 0.1582 19.9304 0.1133 0.0600 0.1355 0.1091 0.0181 1.9723 0.7116 3.9995 4.3137 3.9986 0.4187 0.0878 0.1565 19.1928 0.1113 0.0584 0.1298 0.1115 0.0165 2.0593 0.7057 4.0000 4.3236 4.0000 0.4194 0.0819 0.1547 18.4772 0.1092 0.0567 0.1239 0.1139 0.0146 2.1463 0.6985 4.0000 4.3326 4.0000 0.4194 0.0760 0.1529 17.8107 0.1068 0.0549 0.1178 0.1164 0.0124 2.2334 0.6899 4.0000 4.3412 4.0001 0.4186 0.0699 0.1511 17.1900 0.1043 0.0530 0.1115 0.1187 0.0099 2.3204 0.6800 4.0000 4.3493 4.0001 0.4170 0.0638 0.1493 16.6105 0.1016 0.0509 0.1049 0.1208 0.0072 2.4074 0.6686 4.0000 4.3569 4.0001 0.4144 0.0576 0.1476 16.0681 0.0987 0.0486 0.0981 0.1227 0.0043 2.4945 0.6559 4.0000 4.3640 4.0001 0.4108 0.0514 0.1458 15.5590 0.0956 0.0462 0.0912 0.1242 0.0012 2.5815 0.6417 4.0000 4.3705 4.0001 0.4060 0.0451 0.1440 15.0800 0.0924 0.0437 0.0840 0.1252 -0.0021 2.6686 0.6260 4.0000 4.3763 4.0001 0.4001 0.0387 0.1422 14.6284 0.0890 0.0411 0.0767 0.1258 -0.0055 2.7556 0.6089 4.0000 4.3816 4.0001 0.3929 0.0324 0.1404 14.2015 0.0855 0.0384 0.0692 0.1257 -0.0091 2.8426 0.5902 4.0000 4.3860 4.0001 0.3843 0.0260 0.1387 13.7970 0.0818 0.0357 0.0616 0.1250 -0.0128 2.9297 0.5700 4.0000 4.3897 4.0001 0.3743 0.0195 0.1369 13.4128 0.0780 0.0329 0.0538 0.1235 -0.0166 3.0167 0.5483 4.0000 4.3924 4.0001 0.3627 0.0131 0.1351 13.0470 0.0741 0.0300 0.0459 0.1211 -0.0205 3.1037 0.5249 4.0000 4.3940 4.0001 0.3496 0.0066 0.1333 12.6978 0.0700 0.0272 0.0379 0.1179 -0.0246 3.1908 0.5000 4.0000 4.3945 4.0001 0.3347 0.0001 0.1315 12.3635 0.0658 0.0244 0.0297 0.1137 -0.0287 3.2778 0.4734 4.0000 4.3939 3.9989 0.3180 -0.0064 0.1298 12.0434 0.0614 0.0216 0.0214 0.1084 -0.0328 3.3648 0.4453 4.0000 4.4009 3.9821 0.2995 -0.0127 0.1280 11.7587 0.0570 0.0189 0.0130 0.1020 -0.0372 3.4519 0.4155 4.0000 4.4249 3.9520 0.2791 -0.0187 0.1262 11.5311 0.0524 0.0162 0.0046 0.0944 -0.0416 3.5389 0.3841 4.0000 4.4740 3.9171 0.2565 -0.0243 0.1244 11.3766 0.0478 0.0137 -0.0037 0.0855 -0.0460 3.6259 0.3510 4.0000 4.5558 3.8861 0.2319 -0.0295 0.1226 11.3082 0.0431 0.0113 -0.0119 0.0753 -0.0503 3.7130 0.3163 4.0000 4.6793 3.8667 0.2051 -0.0345 0.1209 11.3418 0.0382 0.0091 -0.0198 0.0636 -0.0544 3.7965 0.2812 4.0000 4.8376 3.8691 0.1772 -0.0392 0.1192 11.4641 0.0335 0.0071 -0.0273 0.0509 -0.0583 3.8202 0.2710 4.0000 4.8901 3.8744 0.1689 -0.0405 0.1187 11.5151 0.0322 0.0065 -0.0294 0.0471 -0.0594 3.8404 0.2622 4.0000 4.9374 3.8808 0.1617 -0.0416 0.1183 11.5641 0.0310 0.0061 -0.0312 0.0437 -0.0603 3.8606 0.2530 4.0000 4.9870 3.8890 0.1541 -0.0428 0.1179 11.6177 0.0298 0.0057 -0.0330 0.0402 -0.0613 3.8808 0.2416 4.0000 5.0392 3.8994 0.1443 -0.0445 0.1174 11.6764 0.0284 0.0052 -0.0354 0.0353 -0.0625 3.9010 0.2269 4.0000 5.0937 3.9226 0.1312 -0.0468 0.1170 11.7399 0.0266 0.0045 -0.0385 0.0287 -0.0641 3.9212 0.2080 4.0000 5.1504 3.9666 0.1140 -0.0500 0.1166 11.8073 0.0243 0.0038 -0.0426 0.0198 -0.0663 3.9414 0.1831 4.0000 5.2088 4.0427 0.0909 -0.0545 0.1162 11.8779 0.0213 0.0030 -0.0482 0.0077 -0.0692 3.9616 0.1470 4.0000 5.2686 4.2057 0.0568 -0.0614 0.1158 11.9510 0.0170 0.0019 -0.0564 -0.0104 -0.0735 3.9818 0.0799 4.0000 5.3306 4.9205 -0.0076 -0.0747 0.1154 12.0280 0.0092 0.0006 -0.0722 -0.0451 -0.0817 4.0000 0.0093 4.0000 4.0000 4.0000 -0.0754 -0.0896 0.1150 9.0431 0.0011 0.0000 -0.0896 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.16 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.037259 TOTAL WEIGHT (Kg) = 0.016897 TOTAL VOLUME (IN**3) = 0.606991 TOTAL PROJECTED AREA (IN**2) = 4.6579 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000209 MOMENT OF INERTIA (Kg-M**2) = 0.000024 STATIC MOMENT, ONE SIDE (IN-LB) = 0.021141 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 = 88.487 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 30611.99 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.