RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 100,000 Max Cl/Cd: 48.59 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14a147-il-100000.txt Download as CSV file: xf-rg14a147-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14A-1.4/7.0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5226 0.09990 0.09497 -0.0101 1.0000 0.0794
-8.500 -0.5352 0.09699 0.09217 -0.0158 1.0000 0.0812
-8.250 -0.5492 0.09370 0.08897 -0.0220 1.0000 0.0816
-8.000 -0.5279 0.08853 0.08381 -0.0159 1.0000 0.0847
-7.750 -0.5235 0.08524 0.08056 -0.0156 1.0000 0.0879
-7.500 -0.5266 0.08152 0.07689 -0.0187 1.0000 0.0912
-7.250 -0.5404 0.07756 0.07278 -0.0290 1.0000 0.0949
-7.000 -0.5295 0.07261 0.06797 -0.0262 1.0000 0.0976
-6.750 -0.5201 0.06950 0.06489 -0.0250 1.0000 0.1022
-6.500 -0.5225 0.06503 0.06016 -0.0307 1.0000 0.1096
-6.250 -0.5086 0.06202 0.05732 -0.0275 1.0000 0.1171
-6.000 -0.5014 0.05839 0.05362 -0.0280 1.0000 0.1275
-5.750 -0.4923 0.05512 0.05029 -0.0279 1.0000 0.1410
-5.500 -0.4817 0.05197 0.04707 -0.0275 1.0000 0.1555
-5.250 -0.4696 0.04887 0.04384 -0.0271 1.0000 0.1715
-4.750 -0.4182 0.03545 0.02836 -0.0296 1.0000 0.0827
-4.500 -0.3951 0.03031 0.02288 -0.0281 1.0000 0.0626
-4.250 -0.3699 0.02722 0.01897 -0.0262 1.0000 0.0544
-4.000 -0.3468 0.02435 0.01574 -0.0250 1.0000 0.0528
-3.750 -0.3224 0.02209 0.01311 -0.0236 1.0000 0.0526
-3.500 -0.2978 0.02059 0.01125 -0.0223 1.0000 0.0560
-3.250 -0.2747 0.01873 0.00944 -0.0213 1.0000 0.0634
-3.000 -0.2510 0.01723 0.00785 -0.0198 1.0000 0.0698
-2.750 -0.2292 0.01589 0.00669 -0.0186 1.0000 0.0894
-2.500 -0.2110 0.01287 0.00522 -0.0170 1.0000 0.3417
-2.250 -0.1124 0.01141 0.00527 -0.0259 1.0000 1.0000
-2.000 -0.1020 0.01128 0.00495 -0.0232 1.0000 1.0000
-1.750 -0.0907 0.01119 0.00468 -0.0205 1.0000 1.0000
-1.500 -0.0784 0.01115 0.00447 -0.0180 1.0000 1.0000
-1.250 -0.0640 0.01116 0.00428 -0.0159 1.0000 1.0000
-1.000 -0.0479 0.01120 0.00417 -0.0142 1.0000 1.0000
-0.750 -0.0307 0.01129 0.00412 -0.0127 1.0000 1.0000
-0.500 -0.0128 0.01141 0.00413 -0.0114 1.0000 1.0000
-0.250 0.0055 0.01157 0.00419 -0.0102 1.0000 1.0000
0.000 0.0240 0.01177 0.00430 -0.0092 1.0000 1.0000
0.250 0.0424 0.01201 0.00445 -0.0082 1.0000 1.0000
0.500 0.0607 0.01230 0.00468 -0.0074 1.0000 1.0000
0.750 0.0788 0.01264 0.00498 -0.0066 1.0000 1.0000
1.000 0.1302 0.01312 0.00546 -0.0123 0.9876 1.0000
1.250 0.1858 0.01350 0.00586 -0.0184 0.9729 1.0000
1.500 0.2412 0.01371 0.00612 -0.0243 0.9577 1.0000
1.750 0.2977 0.01374 0.00626 -0.0300 0.9424 1.0000
2.000 0.3495 0.01362 0.00630 -0.0345 0.9243 1.0000
2.250 0.4034 0.01334 0.00617 -0.0390 0.9059 1.0000
2.500 0.4507 0.01303 0.00601 -0.0418 0.8843 1.0000
2.750 0.4900 0.01275 0.00591 -0.0429 0.8578 1.0000
3.000 0.5216 0.01257 0.00583 -0.0424 0.8258 1.0000
3.250 0.5494 0.01249 0.00579 -0.0410 0.7899 1.0000
3.500 0.5746 0.01252 0.00581 -0.0393 0.7503 1.0000
3.750 0.5970 0.01269 0.00596 -0.0372 0.7051 1.0000
4.000 0.6189 0.01288 0.00613 -0.0351 0.6563 1.0000
4.250 0.6399 0.01318 0.00632 -0.0329 0.6014 1.0000
4.500 0.6599 0.01358 0.00658 -0.0307 0.5385 1.0000
4.750 0.6789 0.01412 0.00690 -0.0286 0.4671 1.0000
5.000 0.6959 0.01485 0.00728 -0.0263 0.3748 1.0000
5.250 0.7107 0.01603 0.00782 -0.0242 0.2520 1.0000
5.500 0.7226 0.01827 0.00920 -0.0220 0.1288 1.0000
5.750 0.7380 0.02057 0.01112 -0.0197 0.0880 1.0000
6.000 0.7591 0.02241 0.01295 -0.0182 0.0731 1.0000
6.250 0.7815 0.02452 0.01496 -0.0172 0.0626 1.0000
6.500 0.8074 0.02664 0.01741 -0.0161 0.0582 1.0000
6.750 0.8320 0.02909 0.02009 -0.0150 0.0541 1.0000
7.000 0.8523 0.03213 0.02341 -0.0140 0.0491 1.0000
7.250 0.8718 0.03544 0.02730 -0.0122 0.0480 1.0000
7.500 0.8876 0.03943 0.03185 -0.0104 0.0483 1.0000
7.750 0.8998 0.04410 0.03698 -0.0087 0.0494 1.0000
8.000 0.9115 0.04968 0.04284 -0.0075 0.0509 1.0000
8.250 0.9192 0.05360 0.04730 -0.0057 0.0511 1.0000
8.500 0.9061 0.06035 0.05493 -0.0031 0.0610 1.0000
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Polar data table (+)
Polar graphs
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