RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.05 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14a147-il-1000000.txt Download as CSV file: xf-rg14a147-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5322 0.09229 0.09066 -0.0108 1.0000 0.0067
-9.000 -0.5350 0.08774 0.08613 -0.0129 1.0000 0.0068
-8.750 -0.5355 0.08368 0.08209 -0.0149 1.0000 0.0069
-8.500 -0.5382 0.07942 0.07786 -0.0172 1.0000 0.0069
-8.250 -0.5433 0.07517 0.07363 -0.0198 1.0000 0.0070
-8.000 -0.5516 0.07034 0.06882 -0.0240 1.0000 0.0070
-7.750 -0.5527 0.06502 0.06347 -0.0280 1.0000 0.0070
-7.500 -0.5516 0.05999 0.05838 -0.0306 1.0000 0.0071
-7.250 -0.5484 0.05542 0.05374 -0.0320 1.0000 0.0072
-7.000 -0.5436 0.05116 0.04938 -0.0325 1.0000 0.0073
-6.750 -0.5373 0.04680 0.04489 -0.0325 1.0000 0.0073
-6.500 -0.5291 0.04310 0.04105 -0.0319 1.0000 0.0075
-6.250 -0.5197 0.03945 0.03725 -0.0308 1.0000 0.0077
-4.750 -0.3953 0.01524 0.01082 -0.0275 0.9952 0.0070
-4.500 -0.3616 0.01381 0.00923 -0.0286 0.9938 0.0061
-4.250 -0.3315 0.01170 0.00684 -0.0289 0.9915 0.0060
-4.000 -0.2987 0.01072 0.00571 -0.0298 0.9890 0.0063
-3.750 -0.2669 0.00907 0.00389 -0.0308 0.9865 0.0080
-3.500 -0.2317 0.00864 0.00342 -0.0324 0.9845 0.0091
-3.250 -0.1955 0.00823 0.00297 -0.0342 0.9828 0.0104
-3.000 -0.1641 0.00796 0.00269 -0.0350 0.9786 0.0115
-2.750 -0.1311 0.00728 0.00186 -0.0359 0.9745 0.0188
-2.500 -0.0967 0.00674 0.00155 -0.0375 0.9711 0.0748
-2.250 -0.0664 0.00627 0.00136 -0.0382 0.9648 0.1558
-2.000 -0.0359 0.00573 0.00119 -0.0390 0.9574 0.2665
-1.750 -0.0069 0.00521 0.00104 -0.0395 0.9468 0.3909
-1.500 0.0217 0.00468 0.00091 -0.0399 0.9335 0.5264
-1.250 0.0452 0.00393 0.00086 -0.0390 0.9162 0.7472
-1.000 0.0710 0.00382 0.00084 -0.0383 0.8966 0.8058
-0.750 0.0968 0.00381 0.00081 -0.0375 0.8751 0.8354
-0.500 0.1216 0.00381 0.00080 -0.0366 0.8519 0.8648
-0.250 0.1467 0.00386 0.00079 -0.0357 0.8273 0.8845
0.250 0.1962 0.00400 0.00079 -0.0339 0.7726 0.9151
0.500 0.2206 0.00409 0.00080 -0.0330 0.7504 0.9296
0.750 0.2454 0.00416 0.00083 -0.0321 0.7298 0.9431
1.000 0.2708 0.00424 0.00085 -0.0314 0.7061 0.9562
1.250 0.2979 0.00435 0.00086 -0.0311 0.6727 0.9690
1.500 0.3294 0.00451 0.00089 -0.0318 0.6371 0.9775
1.750 0.3621 0.00469 0.00095 -0.0329 0.6008 0.9849
2.000 0.3978 0.00488 0.00100 -0.0348 0.5616 0.9900
2.250 0.4329 0.00510 0.00106 -0.0365 0.5207 0.9948
2.500 0.4691 0.00534 0.00114 -0.0385 0.4712 0.9986
2.750 0.4957 0.00563 0.00124 -0.0385 0.4181 1.0000
3.000 0.5162 0.00594 0.00135 -0.0372 0.3650 1.0000
3.250 0.5382 0.00624 0.00148 -0.0361 0.3208 1.0000
3.500 0.5604 0.00659 0.00163 -0.0351 0.2705 1.0000
3.750 0.5836 0.00692 0.00181 -0.0344 0.2282 1.0000
4.000 0.6068 0.00734 0.00203 -0.0336 0.1784 1.0000
4.250 0.6302 0.00780 0.00228 -0.0329 0.1298 1.0000
4.500 0.6542 0.00823 0.00254 -0.0323 0.0915 1.0000
4.750 0.6778 0.00875 0.00287 -0.0317 0.0503 1.0000
5.000 0.7015 0.00932 0.00328 -0.0310 0.0229 1.0000
5.250 0.7261 0.00980 0.00385 -0.0303 0.0174 1.0000
5.500 0.7518 0.01007 0.00416 -0.0300 0.0163 1.0000
5.750 0.7771 0.01039 0.00451 -0.0296 0.0141 1.0000
6.000 0.8014 0.01093 0.00510 -0.0290 0.0119 1.0000
6.250 0.8231 0.01190 0.00623 -0.0278 0.0099 1.0000
6.500 0.8488 0.01216 0.00653 -0.0275 0.0090 1.0000
6.750 0.8736 0.01259 0.00698 -0.0271 0.0075 1.0000
7.000 0.8965 0.01331 0.00778 -0.0263 0.0062 1.0000
7.250 0.9142 0.01499 0.00967 -0.0246 0.0053 1.0000
7.500 0.9391 0.01534 0.01007 -0.0242 0.0049 1.0000
7.750 0.9604 0.01640 0.01127 -0.0232 0.0046 1.0000
8.000 0.9816 0.01747 0.01247 -0.0222 0.0044 1.0000
8.250 1.0018 0.01877 0.01393 -0.0211 0.0041 1.0000
8.500 1.0231 0.01973 0.01501 -0.0202 0.0039 1.0000
8.750 1.0448 0.02048 0.01585 -0.0195 0.0036 1.0000
9.000 1.0648 0.02151 0.01700 -0.0186 0.0034 1.0000
9.250 1.0808 0.02317 0.01884 -0.0173 0.0031 1.0000
9.500 1.0380 0.01855 0.01523 -0.0113 0.0027 1.0000
9.750 1.0404 0.02155 0.01855 -0.0090 0.0027 1.0000
10.000 1.0319 0.02538 0.02270 -0.0059 0.0027 1.0000
10.250 1.0124 0.02859 0.02616 -0.0015 0.0026 1.0000
10.500 0.9892 0.03188 0.02964 0.0014 0.0026 1.0000
10.750 0.9617 0.03638 0.03432 0.0020 0.0027 1.0000
11.000 0.9394 0.04171 0.03978 0.0002 0.0027 1.0000
11.250 0.9095 0.05016 0.04838 -0.0044 0.0027 1.0000
11.500 0.8856 0.05977 0.05812 -0.0103 0.0028 1.0000
12.750 0.8748 0.11705 0.11562 -0.0380 0.0031 1.0000
13.000 0.8056 0.14541 0.14386 -0.0496 0.0049 1.0000
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Polar data table (+)
Polar graphs
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