RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.92 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14-il-1000000.txt Download as CSV file: xf-rg14-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4184 0.13835 0.13673 -0.0064 1.0000 0.0078
-12.750 -0.4154 0.13491 0.13329 -0.0078 1.0000 0.0080
-6.750 -0.5806 0.02653 0.02349 -0.0325 0.9978 0.0082
-6.500 -0.5539 0.02204 0.01848 -0.0339 0.9955 0.0083
-6.250 -0.5236 0.01922 0.01528 -0.0352 0.9940 0.0084
-6.000 -0.4965 0.01662 0.01232 -0.0355 0.9914 0.0082
-5.750 -0.4657 0.01511 0.01058 -0.0364 0.9890 0.0084
-5.500 -0.4338 0.01371 0.00898 -0.0374 0.9869 0.0085
-5.250 -0.4016 0.01225 0.00734 -0.0384 0.9851 0.0085
-5.000 -0.3682 0.01106 0.00600 -0.0397 0.9836 0.0084
-4.750 -0.3341 0.01016 0.00498 -0.0411 0.9822 0.0087
-4.500 -0.3064 0.00952 0.00425 -0.0410 0.9771 0.0088
-4.250 -0.2731 0.00892 0.00356 -0.0421 0.9741 0.0095
-4.000 -0.2382 0.00831 0.00285 -0.0436 0.9718 0.0121
-3.750 -0.2027 0.00799 0.00250 -0.0453 0.9697 0.0144
-3.500 -0.1756 0.00753 0.00215 -0.0450 0.9624 0.0382
-3.250 -0.1434 0.00718 0.00192 -0.0460 0.9575 0.0656
-3.000 -0.1142 0.00688 0.00173 -0.0464 0.9492 0.0981
-2.750 -0.0828 0.00657 0.00155 -0.0472 0.9414 0.1375
-2.500 -0.0540 0.00623 0.00137 -0.0475 0.9298 0.1950
-2.250 -0.0270 0.00580 0.00122 -0.0474 0.9158 0.2848
-2.000 -0.0011 0.00543 0.00111 -0.0471 0.9001 0.3781
-1.750 0.0240 0.00507 0.00101 -0.0467 0.8833 0.4774
-1.500 0.0488 0.00475 0.00092 -0.0461 0.8657 0.5730
-1.250 0.0716 0.00433 0.00088 -0.0450 0.8474 0.7096
-1.000 0.0961 0.00421 0.00091 -0.0440 0.8288 0.7807
-0.750 0.1218 0.00422 0.00091 -0.0433 0.8092 0.8126
-0.500 0.1477 0.00427 0.00090 -0.0427 0.7895 0.8332
-0.250 0.1734 0.00431 0.00091 -0.0421 0.7686 0.8515
0.000 0.1992 0.00438 0.00092 -0.0415 0.7474 0.8658
0.250 0.2250 0.00445 0.00093 -0.0409 0.7251 0.8779
0.500 0.2508 0.00453 0.00095 -0.0403 0.7029 0.8894
0.750 0.2762 0.00462 0.00097 -0.0396 0.6799 0.9011
1.000 0.3013 0.00471 0.00100 -0.0389 0.6558 0.9112
1.250 0.3265 0.00480 0.00103 -0.0382 0.6315 0.9204
1.500 0.3514 0.00491 0.00107 -0.0374 0.6070 0.9307
2.000 0.4001 0.00515 0.00117 -0.0356 0.5560 0.9528
2.250 0.4262 0.00529 0.00123 -0.0352 0.5287 0.9630
2.500 0.4548 0.00545 0.00131 -0.0353 0.5011 0.9729
2.750 0.4853 0.00563 0.00139 -0.0359 0.4723 0.9823
3.000 0.5211 0.00584 0.00148 -0.0378 0.4374 0.9865
3.250 0.5559 0.00607 0.00159 -0.0395 0.4058 0.9903
3.500 0.5889 0.00630 0.00172 -0.0408 0.3719 0.9941
3.750 0.6228 0.00656 0.00184 -0.0423 0.3372 0.9969
4.000 0.6561 0.00684 0.00199 -0.0438 0.3017 0.9998
4.250 0.6763 0.00706 0.00212 -0.0424 0.2763 1.0000
4.500 0.6964 0.00737 0.00229 -0.0410 0.2426 1.0000
4.750 0.7178 0.00771 0.00250 -0.0398 0.2083 1.0000
5.000 0.7404 0.00807 0.00272 -0.0389 0.1766 1.0000
5.250 0.7638 0.00840 0.00295 -0.0382 0.1505 1.0000
5.500 0.7875 0.00877 0.00321 -0.0375 0.1248 1.0000
5.750 0.8109 0.00919 0.00349 -0.0369 0.0974 1.0000
6.000 0.8342 0.00964 0.00381 -0.0362 0.0716 1.0000
6.250 0.8581 0.01005 0.00415 -0.0356 0.0539 1.0000
6.500 0.8822 0.01044 0.00448 -0.0350 0.0407 1.0000
6.750 0.9062 0.01085 0.00484 -0.0345 0.0296 1.0000
7.000 0.9299 0.01130 0.00525 -0.0339 0.0198 1.0000
7.250 0.9524 0.01189 0.00578 -0.0330 0.0112 1.0000
7.500 0.9752 0.01249 0.00641 -0.0322 0.0075 1.0000
7.750 0.9949 0.01350 0.00756 -0.0307 0.0056 1.0000
8.000 1.0170 0.01415 0.00832 -0.0298 0.0053 1.0000
8.250 1.0393 0.01474 0.00899 -0.0290 0.0051 1.0000
8.500 1.0612 0.01535 0.00968 -0.0281 0.0048 1.0000
8.750 1.0818 0.01610 0.01052 -0.0270 0.0046 1.0000
9.000 1.1009 0.01702 0.01156 -0.0257 0.0045 1.0000
9.250 1.1193 0.01798 0.01264 -0.0243 0.0043 1.0000
9.500 1.1379 0.01887 0.01363 -0.0230 0.0042 1.0000
9.750 1.1534 0.02012 0.01503 -0.0212 0.0041 1.0000
10.000 1.1699 0.02118 0.01621 -0.0197 0.0040 1.0000
10.250 1.1840 0.02247 0.01766 -0.0179 0.0039 1.0000
10.500 1.1986 0.02359 0.01890 -0.0162 0.0037 1.0000
10.750 1.2102 0.02496 0.02042 -0.0142 0.0036 1.0000
11.000 1.2211 0.02621 0.02180 -0.0122 0.0034 1.0000
11.250 1.2262 0.02764 0.02338 -0.0092 0.0033 1.0000
11.500 1.2252 0.02940 0.02531 -0.0056 0.0033 1.0000
11.750 1.2257 0.03088 0.02691 -0.0027 0.0031 1.0000
12.000 1.2204 0.03299 0.02918 0.0004 0.0031 1.0000
12.250 1.2085 0.03585 0.03225 0.0032 0.0030 1.0000
12.500 1.1949 0.03917 0.03577 0.0051 0.0029 1.0000
12.750 1.1807 0.04293 0.03973 0.0058 0.0029 1.0000
13.000 1.1665 0.04719 0.04418 0.0054 0.0029 1.0000
13.250 1.1437 0.05325 0.05045 0.0034 0.0028 1.0000
13.500 1.1238 0.05975 0.05714 0.0001 0.0028 1.0000
13.750 1.1262 0.06311 0.06057 -0.0019 0.0029 1.0000
14.000 1.1044 0.07116 0.06880 -0.0069 0.0029 1.0000
14.250 1.0867 0.07910 0.07688 -0.0119 0.0029 1.0000
14.500 1.0781 0.08558 0.08347 -0.0160 0.0030 1.0000
14.750 1.0580 0.09492 0.09294 -0.0217 0.0031 1.0000
15.000 1.0383 0.10454 0.10267 -0.0275 0.0031 1.0000
15.250 1.0116 0.11639 0.11465 -0.0343 0.0031 1.0000
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Polar data table (+)
Polar graphs
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