9x4 (9x4.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 1.0372 0.0000 0.0000 0.4000 0.0000 0.4625 0.0000 0.3700 0.0000 0.0300 0.0000 0.0000 0.1100 0.7673 1.3541 0.0092 -0.5876 0.3958 -0.0008 0.4610 0.7602 0.3538 0.2375 0.0323 0.0066 -0.1399 0.2200 0.7366 1.6532 0.0707 -1.1302 0.3939 -0.0027 0.4566 2.9281 0.3363 0.2334 0.0385 0.0210 -0.1404 0.3300 0.7100 1.9343 0.2285 -1.5022 0.3941 -0.0053 0.4493 6.2879 0.3190 0.2258 0.0476 0.0368 -0.1390 0.4400 0.6902 2.1974 0.5134 -1.5799 0.3963 -0.0080 0.4390 10.5201 0.3030 0.2136 0.0586 0.0533 -0.1354 0.5500 0.6786 2.4427 0.9381 -1.2947 0.4001 -0.0104 0.4258 15.1882 0.2890 0.1986 0.0702 0.0698 -0.1298 0.6600 0.6753 2.6700 1.4910 -0.6429 0.4054 -0.0120 0.4097 19.7761 0.2767 0.1824 0.0814 0.0860 -0.1229 0.7700 0.6786 2.8794 2.1305 0.2983 0.4118 -0.0123 0.3907 23.7672 0.2651 0.1663 0.0910 0.1012 -0.1150 0.8800 0.6856 3.0709 2.7825 1.3592 0.4193 -0.0108 0.3687 26.7132 0.2528 0.1514 0.0979 0.1151 -0.1068 0.9900 0.6931 3.2444 3.3425 2.2806 0.4275 -0.0072 0.3438 28.2512 0.2383 0.1384 0.1012 0.1273 -0.0988 1.1000 0.6982 3.4000 3.6850 2.7336 0.4362 -0.0009 0.3159 28.0650 0.2206 0.1282 0.1001 0.1374 -0.0919 1.2098 0.7017 3.5375 3.8313 2.7734 0.4452 0.0065 0.2875 26.7497 0.2017 0.1191 0.0953 0.1459 -0.0865 1.3157 0.7064 3.6531 3.9502 2.8595 0.4542 0.0122 0.2631 25.5403 0.1859 0.1091 0.0888 0.1536 -0.0822 1.4214 0.7120 3.7520 4.0498 2.9875 0.4634 0.0164 0.2419 24.3927 0.1722 0.0986 0.0817 0.1605 -0.0786 1.5271 0.7183 3.8343 4.1319 3.1363 0.4724 0.0192 0.2237 23.2984 0.1607 0.0892 0.0753 0.1666 -0.0753 1.6328 0.7252 3.9001 4.1977 3.2908 0.4813 0.0205 0.2086 22.2533 0.1513 0.0821 0.0705 0.1716 -0.0721 1.7384 0.7324 3.9493 4.2488 3.4262 0.4899 0.0204 0.1966 21.2548 0.1440 0.0777 0.0676 0.1757 -0.0688 1.8441 0.7396 3.9820 4.2863 3.5396 0.4979 0.0189 0.1876 20.3007 0.1388 0.0757 0.0660 0.1790 -0.0657 1.9498 0.7466 3.9981 4.3117 3.6439 0.5053 0.0159 0.1817 19.3893 0.1357 0.0748 0.0644 0.1818 -0.0634 2.0555 0.7531 4.0000 4.3276 3.7397 0.5118 0.0115 0.1785 18.5247 0.1344 0.0748 0.0626 0.1840 -0.0620 2.1612 0.7588 4.0000 4.3418 3.8331 0.5174 0.0070 0.1756 17.7309 0.1332 0.0748 0.0606 0.1857 -0.0611 2.2669 0.7635 4.0000 4.3554 3.9137 0.5219 0.0025 0.1727 17.0030 0.1318 0.0746 0.0582 0.1870 -0.0608 2.3726 0.7670 4.0000 4.3685 3.9723 0.5251 -0.0020 0.1698 16.3328 0.1302 0.0741 0.0550 0.1878 -0.0612 2.4783 0.7689 4.0000 4.3809 3.9994 0.5268 -0.0065 0.1668 15.7136 0.1283 0.0731 0.0510 0.1882 -0.0623 2.5840 0.7690 4.0000 4.3926 4.0001 0.5270 -0.0110 0.1639 15.1393 0.1261 0.0719 0.0462 0.1880 -0.0641 2.6897 0.7671 4.0000 4.4036 4.0001 0.5254 -0.0155 0.1610 14.6049 0.1235 0.0702 0.0411 0.1871 -0.0660 2.7953 0.7628 4.0000 4.4137 4.0001 0.5220 -0.0201 0.1581 14.1061 0.1206 0.0682 0.0357 0.1853 -0.0681 2.9010 0.7559 4.0000 4.4229 4.0001 0.5165 -0.0248 0.1552 13.6390 0.1173 0.0657 0.0300 0.1826 -0.0703 3.0067 0.7462 4.0000 4.4312 4.0001 0.5087 -0.0296 0.1523 13.2004 0.1137 0.0628 0.0239 0.1790 -0.0726 3.1124 0.7333 4.0000 4.4384 4.0001 0.4987 -0.0345 0.1494 12.7872 0.1096 0.0595 0.0174 0.1744 -0.0751 3.2181 0.7170 4.0000 4.4445 4.0001 0.4861 -0.0396 0.1465 12.3968 0.1050 0.0558 0.0106 0.1688 -0.0777 3.3238 0.6971 4.0000 4.4493 4.0001 0.4708 -0.0448 0.1436 12.0270 0.1001 0.0517 0.0033 0.1622 -0.0805 3.4295 0.6732 4.0000 4.4527 4.0001 0.4527 -0.0502 0.1407 11.6754 0.0947 0.0473 -0.0045 0.1545 -0.0835 3.5352 0.6452 4.0000 4.4546 4.0001 0.4317 -0.0558 0.1378 11.3401 0.0889 0.0425 -0.0127 0.1456 -0.0867 3.6409 0.6127 4.0000 4.4545 4.0001 0.4074 -0.0617 0.1349 11.0190 0.0826 0.0376 -0.0215 0.1355 -0.0901 3.7466 0.5754 4.0000 4.4523 4.0001 0.3800 -0.0678 0.1320 10.7100 0.0759 0.0325 -0.0308 0.1242 -0.0938 3.8522 0.5332 3.9888 4.4467 3.9743 0.3490 -0.0741 0.1291 10.4099 0.0688 0.0273 -0.0407 0.1117 -0.0977 3.9579 0.4859 3.9539 4.4461 3.9036 0.3145 -0.0802 0.1262 10.1366 0.0613 0.0222 -0.0511 0.0978 -0.1019 4.0636 0.4331 3.8951 4.4634 3.8035 0.2762 -0.0862 0.1233 9.9158 0.0534 0.0173 -0.0618 0.0826 -0.1062 4.1693 0.3746 3.8124 4.5082 3.6899 0.2340 -0.0923 0.1203 9.7644 0.0451 0.0126 -0.0729 0.0660 -0.1107 4.2707 0.3127 3.7107 4.5845 3.5810 0.1897 -0.0985 0.1176 9.6954 0.0368 0.0086 -0.0839 0.0488 -0.1152 4.2977 0.2953 3.6799 4.6084 3.5541 0.1772 -0.1003 0.1168 9.6848 0.0345 0.0077 -0.0869 0.0440 -0.1165 4.3205 0.2802 3.6528 4.6292 3.5324 0.1665 -0.1019 0.1162 9.6774 0.0326 0.0069 -0.0895 0.0399 -0.1176 4.3432 0.2649 3.6246 4.6503 3.5117 0.1557 -0.1035 0.1156 9.6708 0.0306 0.0061 -0.0922 0.0357 -0.1187 4.3659 0.2493 3.5952 4.6711 3.4921 0.1446 -0.1052 0.1149 9.6636 0.0286 0.0054 -0.0949 0.0314 -0.1198 4.3886 0.2331 3.5648 4.6909 3.4735 0.1331 -0.1071 0.1143 9.6545 0.0266 0.0047 -0.0977 0.0270 -0.1210 4.4114 0.2133 3.5333 4.7087 3.4605 0.1181 -0.1096 0.1137 9.6415 0.0243 0.0039 -0.1012 0.0208 -0.1226 4.4341 0.1876 3.5007 4.7232 3.4830 0.0974 -0.1131 0.1131 9.6220 0.0212 0.0031 -0.1060 0.0114 -0.1249 4.4568 0.1522 3.4669 4.7319 3.5802 0.0673 -0.1183 0.1124 9.5911 0.0171 0.0020 -0.1127 -0.0031 -0.1281 4.4795 0.0895 3.4321 4.7314 4.1340 0.0103 -0.1280 0.1118 9.5423 0.0100 0.0007 -0.1248 -0.0320 -0.1340 4.5000 0.0075 3.3998 3.3999 3.3998 -0.0660 -0.1413 0.1112 6.8566 0.0008 0.0000 -0.1413 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.050934 TOTAL WEIGHT (Kg) = 0.023099 TOTAL VOLUME (IN**3) = 0.829776 TOTAL PROJECTED AREA (IN**2) = 5.6880 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000416 MOMENT OF INERTIA (Kg-M**2) = 0.000047 STATIC MOMENT, ONE SIDE (IN-LB) = 0.035368 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 = 91.954 INNER LIMIT (NORMALIZED BY RADIUS) = 0.089 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19074.46 BASED ON MODULUS (MILLION) = 1.60 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.