RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 500,000 Max Cl/Cd: 73.97 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14-il-500000-n5.txt Download as CSV file: xf-rg14-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4438 0.08201 0.07984 -0.0238 1.0000 0.0059
-9.750 -0.4604 0.07395 0.07182 -0.0263 1.0000 0.0056
-9.500 -0.4704 0.06814 0.06603 -0.0283 1.0000 0.0057
-9.250 -0.4922 0.05974 0.05768 -0.0315 1.0000 0.0055
-8.750 -0.5845 0.06312 0.06099 -0.0355 1.0000 0.0052
-8.500 -0.6051 0.05495 0.05272 -0.0391 1.0000 0.0051
-8.250 -0.6277 0.04512 0.04268 -0.0397 1.0000 0.0051
-8.000 -0.6466 0.03653 0.03364 -0.0378 1.0000 0.0051
-7.750 -0.6489 0.03177 0.02844 -0.0354 1.0000 0.0051
-7.500 -0.6409 0.02894 0.02528 -0.0334 1.0000 0.0052
-7.250 -0.6382 0.02428 0.02002 -0.0308 0.9999 0.0054
-7.000 -0.6123 0.02131 0.01659 -0.0320 0.9974 0.0059
-6.750 -0.5828 0.01961 0.01463 -0.0331 0.9951 0.0061
-6.500 -0.5534 0.01815 0.01292 -0.0340 0.9928 0.0063
-6.250 -0.5248 0.01653 0.01103 -0.0345 0.9898 0.0064
-6.000 -0.4946 0.01526 0.00956 -0.0353 0.9869 0.0065
-5.750 -0.4631 0.01416 0.00828 -0.0363 0.9843 0.0066
-5.500 -0.4309 0.01326 0.00723 -0.0374 0.9820 0.0069
-5.250 -0.4034 0.01251 0.00637 -0.0375 0.9770 0.0072
-5.000 -0.3723 0.01184 0.00560 -0.0383 0.9732 0.0076
-4.750 -0.3392 0.01127 0.00495 -0.0395 0.9702 0.0085
-4.500 -0.3104 0.01081 0.00441 -0.0397 0.9646 0.0089
-4.250 -0.2793 0.01033 0.00384 -0.0404 0.9596 0.0100
-4.000 -0.2460 0.00991 0.00339 -0.0416 0.9556 0.0128
-3.750 -0.2168 0.00953 0.00303 -0.0419 0.9477 0.0207
-3.500 -0.1833 0.00917 0.00271 -0.0432 0.9417 0.0365
-3.250 -0.1521 0.00887 0.00246 -0.0439 0.9326 0.0539
-3.000 -0.1202 0.00855 0.00223 -0.0449 0.9230 0.0794
-2.750 -0.0893 0.00819 0.00201 -0.0456 0.9117 0.1245
-2.500 -0.0600 0.00784 0.00181 -0.0461 0.8985 0.1772
-2.250 -0.0320 0.00754 0.00165 -0.0462 0.8833 0.2338
-2.000 -0.0049 0.00728 0.00151 -0.0461 0.8666 0.2895
-1.750 0.0210 0.00695 0.00139 -0.0457 0.8486 0.3721
-1.500 0.0460 0.00661 0.00127 -0.0452 0.8295 0.4629
-1.250 0.0704 0.00631 0.00119 -0.0446 0.8095 0.5539
-1.000 0.0940 0.00600 0.00114 -0.0436 0.7900 0.6511
-0.750 0.1167 0.00578 0.00119 -0.0423 0.7696 0.7519
-0.500 0.1413 0.00578 0.00120 -0.0413 0.7489 0.7976
-0.250 0.1666 0.00582 0.00121 -0.0405 0.7275 0.8234
0.000 0.1918 0.00589 0.00122 -0.0398 0.7058 0.8442
0.250 0.2168 0.00597 0.00124 -0.0389 0.6833 0.8617
0.500 0.2420 0.00605 0.00126 -0.0382 0.6607 0.8759
0.750 0.2670 0.00615 0.00128 -0.0374 0.6378 0.8889
1.000 0.2919 0.00625 0.00131 -0.0366 0.6141 0.9022
1.250 0.3165 0.00636 0.00135 -0.0358 0.5901 0.9155
1.500 0.3413 0.00648 0.00141 -0.0349 0.5656 0.9284
1.750 0.3668 0.00661 0.00146 -0.0343 0.5405 0.9414
2.000 0.3945 0.00676 0.00153 -0.0342 0.5143 0.9544
2.250 0.4253 0.00694 0.00160 -0.0348 0.4862 0.9645
2.500 0.4567 0.00713 0.00170 -0.0357 0.4568 0.9727
2.750 0.4884 0.00733 0.00180 -0.0366 0.4269 0.9793
3.000 0.5196 0.00756 0.00191 -0.0375 0.3962 0.9845
3.250 0.5515 0.00780 0.00203 -0.0386 0.3651 0.9892
3.500 0.5824 0.00806 0.00220 -0.0395 0.3330 0.9943
3.750 0.6140 0.00834 0.00236 -0.0406 0.3011 0.9994
4.000 0.6364 0.00861 0.00253 -0.0397 0.2736 1.0000
4.250 0.6583 0.00890 0.00271 -0.0386 0.2453 1.0000
4.500 0.6809 0.00923 0.00293 -0.0377 0.2163 1.0000
4.750 0.7042 0.00953 0.00318 -0.0370 0.1924 1.0000
5.000 0.7276 0.00989 0.00343 -0.0363 0.1654 1.0000
5.250 0.7509 0.01029 0.00372 -0.0356 0.1382 1.0000
5.500 0.7740 0.01074 0.00404 -0.0349 0.1101 1.0000
5.750 0.7976 0.01114 0.00437 -0.0342 0.0902 1.0000
6.000 0.8216 0.01152 0.00471 -0.0336 0.0752 1.0000
6.250 0.8454 0.01192 0.00510 -0.0331 0.0613 1.0000
6.500 0.8682 0.01246 0.00553 -0.0323 0.0432 1.0000
6.750 0.8912 0.01296 0.00597 -0.0317 0.0296 1.0000
7.000 0.9141 0.01348 0.00645 -0.0310 0.0198 1.0000
7.250 0.9370 0.01400 0.00696 -0.0303 0.0141 1.0000
7.500 0.9599 0.01452 0.00751 -0.0296 0.0107 1.0000
7.750 0.9824 0.01508 0.00812 -0.0288 0.0081 1.0000
8.000 1.0045 0.01569 0.00882 -0.0279 0.0065 1.0000
8.250 1.0249 0.01651 0.00974 -0.0268 0.0053 1.0000
8.500 1.0461 0.01720 0.01053 -0.0259 0.0050 1.0000
8.750 1.0664 0.01797 0.01143 -0.0248 0.0047 1.0000
9.000 1.0857 0.01883 0.01240 -0.0236 0.0044 1.0000
9.250 1.1037 0.01979 0.01349 -0.0222 0.0042 1.0000
9.500 1.1213 0.02075 0.01458 -0.0208 0.0041 1.0000
9.750 1.1375 0.02182 0.01579 -0.0193 0.0039 1.0000
10.000 1.1545 0.02274 0.01682 -0.0179 0.0037 1.0000
10.250 1.1698 0.02377 0.01800 -0.0164 0.0035 1.0000
10.500 1.1849 0.02474 0.01907 -0.0149 0.0032 1.0000
10.750 1.1960 0.02601 0.02049 -0.0129 0.0031 1.0000
11.000 1.2021 0.02749 0.02213 -0.0102 0.0030 1.0000
11.250 1.2046 0.02903 0.02384 -0.0071 0.0029 1.0000
11.500 1.2037 0.03087 0.02586 -0.0039 0.0028 1.0000
11.750 1.2002 0.03297 0.02816 -0.0010 0.0028 1.0000
12.000 1.1944 0.03538 0.03078 0.0015 0.0027 1.0000
12.250 1.1843 0.03840 0.03403 0.0034 0.0027 1.0000
12.500 1.1704 0.04214 0.03800 0.0045 0.0026 1.0000
12.750 1.1556 0.04641 0.04250 0.0045 0.0026 1.0000
13.000 1.1444 0.05075 0.04702 0.0034 0.0026 1.0000
13.250 1.1374 0.05492 0.05136 0.0016 0.0026 1.0000
13.500 1.1281 0.05990 0.05650 -0.0009 0.0025 1.0000
13.750 1.1036 0.06796 0.06477 -0.0055 0.0026 1.0000
14.000 1.0883 0.07514 0.07211 -0.0100 0.0026 1.0000
14.250 1.0707 0.08319 0.08032 -0.0150 0.0026 1.0000
14.750 1.0455 0.09818 0.09553 -0.0240 0.0027 1.0000
15.000 1.0311 0.10649 0.10394 -0.0288 0.0027 1.0000
15.250 1.0092 0.11690 0.11447 -0.0347 0.0027 1.0000
15.500 1.0022 0.12385 0.12148 -0.0385 0.0028 1.0000
15.750 0.9841 0.13397 0.13170 -0.0440 0.0029 1.0000
16.000 0.9585 0.14683 0.14465 -0.0507 0.0030 1.0000
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Polar data table (+)
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