6x4 (6x4.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 -1.5097 0.0000 0.0000 0.2500 0.0000 0.3000 0.0000 0.1500 0.0000 0.0500 0.0000 0.0000 0.0726 0.4798 -0.9828 0.0064 -0.1804 0.2465 0.0033 0.2994 0.8026 0.1437 0.0620 0.0533 0.0052 -0.0213 0.1452 0.4633 -0.4823 0.0494 -0.3390 0.2432 0.0122 0.2976 3.0983 0.1379 0.0629 0.0624 0.0109 -0.0179 0.2178 0.4517 -0.0083 0.1592 -0.4153 0.2403 0.0255 0.2945 6.6357 0.1330 0.0628 0.0757 0.0159 -0.0118 0.2904 0.4459 0.4392 0.3562 -0.3611 0.2378 0.0419 0.2903 11.0476 0.1294 0.0617 0.0919 0.0201 -0.0036 0.3630 0.4466 0.8602 0.6482 -0.1500 0.2358 0.0602 0.2848 15.8642 0.1272 0.0601 0.1099 0.0237 0.0061 0.4356 0.4534 1.2547 1.0277 0.2193 0.2343 0.0791 0.2781 20.5810 0.1261 0.0580 0.1283 0.0264 0.0168 0.5082 0.4649 1.6228 1.4720 0.7206 0.2334 0.0973 0.2702 24.7500 0.1256 0.0556 0.1457 0.0283 0.0277 0.5808 0.4789 1.9644 1.9433 1.3004 0.2333 0.1136 0.2611 28.0362 0.1250 0.0530 0.1607 0.0295 0.0380 0.6534 0.4930 2.2795 2.3909 1.8810 0.2338 0.1268 0.2508 30.2151 0.1236 0.0504 0.1720 0.0297 0.0468 0.7260 0.5046 2.5681 2.7546 2.3655 0.2352 0.1356 0.2392 31.1268 0.1207 0.0478 0.1782 0.0288 0.0527 0.7985 0.5135 2.8299 3.0282 2.7280 0.2368 0.1402 0.2265 31.1138 0.1163 0.0453 0.1796 0.0270 0.0557 0.8693 0.5209 3.0602 3.2662 3.0289 0.2379 0.1424 0.2128 30.8781 0.1109 0.0428 0.1783 0.0251 0.0562 0.9401 0.5272 3.2650 3.4752 3.2645 0.2384 0.1422 0.1981 30.4702 0.1044 0.0404 0.1746 0.0234 0.0544 1.0108 0.5323 3.4447 3.6570 3.4447 0.2385 0.1393 0.1843 29.9334 0.0981 0.0383 0.1684 0.0215 0.0502 1.0816 0.5362 3.5992 3.8143 3.5993 0.2380 0.1346 0.1735 29.3050 0.0930 0.0366 0.1614 0.0193 0.0455 1.1523 0.5389 3.7286 3.9480 3.7287 0.2371 0.1290 0.1657 28.6036 0.0893 0.0353 0.1542 0.0167 0.0407 1.2230 0.5404 3.8328 4.0590 3.8330 0.2357 0.1224 0.1610 27.8433 0.0870 0.0344 0.1470 0.0139 0.0360 1.2938 0.5407 3.9119 4.1474 3.9121 0.2337 0.1151 0.1587 27.0306 0.0858 0.0339 0.1397 0.0108 0.0314 1.3645 0.5398 3.9659 4.2104 3.9661 0.2314 0.1075 0.1566 26.1555 0.0845 0.0334 0.1323 0.0078 0.0270 1.4352 0.5377 3.9947 4.2477 3.9949 0.2285 0.0999 0.1545 25.2219 0.0831 0.0327 0.1248 0.0047 0.0229 1.5060 0.5345 4.0000 4.2610 4.0002 0.2253 0.0921 0.1525 24.2425 0.0815 0.0318 0.1172 0.0016 0.0191 1.5767 0.5300 4.0000 4.2687 4.0001 0.2215 0.0844 0.1504 23.3106 0.0797 0.0309 0.1094 -0.0012 0.0152 1.6475 0.5244 4.0000 4.2762 4.0001 0.2174 0.0766 0.1483 22.4460 0.0778 0.0298 0.1016 -0.0039 0.0111 1.7182 0.5176 4.0000 4.2834 4.0001 0.2128 0.0689 0.1462 21.6417 0.0757 0.0286 0.0937 -0.0064 0.0069 1.7889 0.5096 4.0000 4.2903 4.0001 0.2077 0.0611 0.1442 20.8917 0.0735 0.0273 0.0856 -0.0087 0.0026 1.8597 0.5004 4.0000 4.2970 4.0001 0.2023 0.0533 0.1421 20.1908 0.0711 0.0260 0.0774 -0.0108 -0.0018 1.9304 0.4901 4.0000 4.3033 4.0001 0.1965 0.0455 0.1400 19.5343 0.0686 0.0246 0.0692 -0.0127 -0.0064 2.0011 0.4785 4.0000 4.3093 4.0000 0.1903 0.0377 0.1379 18.9180 0.0660 0.0231 0.0608 -0.0145 -0.0111 2.0719 0.4658 4.0000 4.3150 4.0000 0.1837 0.0299 0.1358 18.3385 0.0633 0.0215 0.0523 -0.0160 -0.0159 2.1426 0.4519 4.0000 4.3203 4.0000 0.1767 0.0221 0.1338 17.7923 0.0605 0.0199 0.0437 -0.0174 -0.0209 2.2134 0.4368 4.0000 4.3253 4.0000 0.1693 0.0142 0.1317 17.2766 0.0575 0.0184 0.0350 -0.0186 -0.0259 2.2841 0.4206 4.0000 4.3299 4.0000 0.1616 0.0063 0.1296 16.7888 0.0545 0.0167 0.0262 -0.0196 -0.0311 2.3548 0.4032 4.0000 4.3341 4.0000 0.1535 -0.0017 0.1275 16.3266 0.0514 0.0151 0.0173 -0.0204 -0.0364 2.4256 0.3845 4.0000 4.3379 4.0000 0.1450 -0.0097 0.1255 15.8880 0.0482 0.0136 0.0083 -0.0210 -0.0417 2.4963 0.3647 4.0000 4.3412 4.0000 0.1363 -0.0177 0.1234 15.4709 0.0450 0.0120 -0.0008 -0.0214 -0.0472 2.5670 0.3438 4.0000 4.3441 4.0000 0.1272 -0.0258 0.1213 15.0737 0.0417 0.0105 -0.0100 -0.0216 -0.0528 2.6378 0.3216 4.0000 4.3464 4.0000 0.1177 -0.0340 0.1192 14.6948 0.0383 0.0090 -0.0194 -0.0216 -0.0586 2.7085 0.2983 4.0000 4.3482 4.0000 0.1080 -0.0422 0.1172 14.3326 0.0349 0.0076 -0.0288 -0.0214 -0.0644 2.7793 0.2738 3.9849 4.3341 3.9849 0.0980 -0.0505 0.1151 13.9388 0.0315 0.0063 -0.0383 -0.0210 -0.0703 2.8471 0.2492 3.9055 4.2548 3.9055 0.0880 -0.0587 0.1131 13.3790 0.0282 0.0051 -0.0476 -0.0204 -0.0758 2.8652 0.2418 3.8729 4.2223 3.8731 0.0847 -0.0610 0.1126 13.1996 0.0272 0.0048 -0.0503 -0.0206 -0.0773 2.8803 0.2337 3.8419 4.1916 3.8426 0.0801 -0.0634 0.1121 13.0404 0.0262 0.0045 -0.0530 -0.0217 -0.0789 2.8955 0.2238 3.8074 4.1577 3.8090 0.0738 -0.0661 0.1117 12.8733 0.0250 0.0041 -0.0562 -0.0237 -0.0808 2.9106 0.2117 3.7696 4.1207 3.7742 0.0654 -0.0694 0.1112 12.6981 0.0235 0.0037 -0.0599 -0.0270 -0.0830 2.9258 0.1970 3.7284 4.0804 3.7375 0.0544 -0.0731 0.1108 12.5147 0.0218 0.0031 -0.0643 -0.0316 -0.0855 2.9409 0.1788 3.6838 4.0367 3.6993 0.0402 -0.0775 0.1103 12.3232 0.0197 0.0026 -0.0694 -0.0380 -0.0885 2.9561 0.1556 3.6357 3.9897 3.6616 0.0209 -0.0829 0.1099 12.1234 0.0171 0.0020 -0.0758 -0.0472 -0.0923 2.9712 0.1223 3.5843 3.9396 3.6325 -0.0081 -0.0902 0.1094 11.9162 0.0134 0.0012 -0.0846 -0.0618 -0.0974 2.9864 0.0647 3.5295 3.8883 3.6715 -0.0610 -0.1022 0.1090 11.7074 0.0070 0.0003 -0.0993 -0.0897 -0.1060 3.0000 0.0095 3.4773 3.4773 3.4773 -0.1119 -0.1134 0.1086 10.4523 0.0010 0.0000 -0.1134 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.73 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.011927 TOTAL WEIGHT (Kg) = 0.005409 TOTAL VOLUME (IN**3) = 0.194303 TOTAL PROJECTED AREA (IN**2) = 2.5038 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000049 MOMENT OF INERTIA (Kg-M**2) = 0.000005 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006074 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 = 94.568 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 31055.96 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.