RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.19 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12a189-il-1000000.txt Download as CSV file: xf-rg12a189-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RG 12A-1.8/9.0 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 -0.4981 0.08256 0.08096 -0.0277 1.0000 0.0096
-9.000 -0.5032 0.07765 0.07607 -0.0300 1.0000 0.0096
-8.750 -0.5110 0.07241 0.07086 -0.0328 1.0000 0.0096
-8.500 -0.5253 0.06689 0.06538 -0.0371 1.0000 0.0096
-8.250 -0.5446 0.06163 0.06008 -0.0386 1.0000 0.0096
-8.000 -0.5570 0.05577 0.05413 -0.0391 1.0000 0.0096
-7.750 -0.5685 0.05019 0.04839 -0.0382 1.0000 0.0096
-7.500 -0.5777 0.04544 0.04346 -0.0363 1.0000 0.0096
-7.250 -0.5697 0.03990 0.03759 -0.0378 0.9986 0.0097
-6.000 -0.4497 0.01575 0.01125 -0.0462 0.9865 0.0083
-5.750 -0.4185 0.01335 0.00850 -0.0470 0.9852 0.0077
-5.500 -0.3850 0.01205 0.00704 -0.0483 0.9841 0.0077
-5.250 -0.3535 0.01118 0.00607 -0.0492 0.9821 0.0079
-5.000 -0.3250 0.01051 0.00533 -0.0494 0.9782 0.0085
-4.750 -0.2922 0.00996 0.00472 -0.0505 0.9756 0.0092
-4.500 -0.2578 0.00943 0.00412 -0.0519 0.9736 0.0099
-4.250 -0.2228 0.00874 0.00336 -0.0536 0.9719 0.0114
-4.000 -0.1865 0.00839 0.00300 -0.0555 0.9706 0.0134
-3.750 -0.1595 0.00799 0.00256 -0.0551 0.9646 0.0174
-3.500 -0.1267 0.00747 0.00218 -0.0563 0.9609 0.0481
-3.250 -0.0926 0.00711 0.00194 -0.0577 0.9577 0.0797
-3.000 -0.0646 0.00676 0.00174 -0.0578 0.9497 0.1227
-2.750 -0.0312 0.00629 0.00153 -0.0593 0.9438 0.1963
-2.250 0.0275 0.00523 0.00118 -0.0605 0.9210 0.4235
-2.000 0.0556 0.00474 0.00104 -0.0607 0.9061 0.5470
-1.750 0.0821 0.00436 0.00099 -0.0604 0.8888 0.6720
-1.500 0.1093 0.00433 0.00097 -0.0601 0.8694 0.7131
-1.250 0.1361 0.00435 0.00095 -0.0597 0.8480 0.7378
-1.000 0.1625 0.00441 0.00095 -0.0592 0.8256 0.7605
-0.750 0.1889 0.00449 0.00094 -0.0587 0.8019 0.7732
-0.500 0.2150 0.00457 0.00094 -0.0582 0.7774 0.7837
-0.250 0.2412 0.00466 0.00095 -0.0577 0.7531 0.7936
0.000 0.2675 0.00477 0.00096 -0.0573 0.7293 0.8028
0.250 0.2935 0.00487 0.00099 -0.0568 0.7056 0.8111
0.500 0.3200 0.00497 0.00102 -0.0564 0.6828 0.8188
0.750 0.3462 0.00508 0.00106 -0.0559 0.6604 0.8266
1.000 0.3726 0.00518 0.00109 -0.0556 0.6371 0.8341
1.250 0.3989 0.00530 0.00115 -0.0552 0.6145 0.8418
1.500 0.4249 0.00541 0.00120 -0.0547 0.5916 0.8499
1.750 0.4512 0.00553 0.00126 -0.0543 0.5681 0.8590
2.000 0.4768 0.00565 0.00133 -0.0538 0.5447 0.8667
2.500 0.5290 0.00593 0.00148 -0.0531 0.4934 0.8786
2.750 0.5553 0.00609 0.00156 -0.0528 0.4677 0.8843
3.000 0.5812 0.00625 0.00165 -0.0524 0.4416 0.8899
3.250 0.6067 0.00642 0.00177 -0.0520 0.4139 0.8963
3.500 0.6319 0.00665 0.00189 -0.0515 0.3807 0.9031
3.750 0.6570 0.00683 0.00202 -0.0510 0.3546 0.9107
4.000 0.6808 0.00712 0.00217 -0.0502 0.3153 0.9196
4.250 0.7039 0.00741 0.00235 -0.0493 0.2777 0.9309
4.500 0.7262 0.00767 0.00252 -0.0482 0.2441 0.9454
4.750 0.7501 0.00792 0.00269 -0.0475 0.2146 0.9653
5.000 0.7816 0.00833 0.00293 -0.0486 0.1748 0.9882
5.250 0.8089 0.00877 0.00321 -0.0488 0.1407 1.0000
5.500 0.8339 0.00918 0.00349 -0.0486 0.1128 1.0000
5.750 0.8584 0.00962 0.00380 -0.0482 0.0856 1.0000
6.000 0.8825 0.01011 0.00415 -0.0477 0.0600 1.0000
6.250 0.9051 0.01076 0.00463 -0.0470 0.0304 1.0000
6.500 0.9289 0.01129 0.00510 -0.0463 0.0191 1.0000
6.750 0.9531 0.01174 0.00556 -0.0458 0.0164 1.0000
7.000 0.9762 0.01236 0.00628 -0.0449 0.0144 1.0000
7.250 1.0007 0.01274 0.00670 -0.0445 0.0139 1.0000
7.500 1.0248 0.01318 0.00719 -0.0439 0.0132 1.0000
7.750 1.0480 0.01368 0.00777 -0.0432 0.0124 1.0000
8.000 1.0707 0.01424 0.00839 -0.0425 0.0117 1.0000
8.250 1.0927 0.01484 0.00904 -0.0416 0.0109 1.0000
8.500 1.1101 0.01596 0.01027 -0.0400 0.0099 1.0000
8.750 1.1267 0.01712 0.01156 -0.0383 0.0094 1.0000
9.000 1.1491 0.01760 0.01210 -0.0376 0.0091 1.0000
9.250 1.1701 0.01823 0.01282 -0.0366 0.0087 1.0000
9.500 1.1901 0.01892 0.01358 -0.0356 0.0082 1.0000
9.750 1.2102 0.01955 0.01428 -0.0346 0.0077 1.0000
10.000 1.2307 0.02009 0.01484 -0.0337 0.0072 1.0000
10.250 1.2480 0.02091 0.01571 -0.0324 0.0068 1.0000
10.500 1.2468 0.02367 0.01871 -0.0285 0.0061 1.0000
10.750 1.2650 0.02422 0.01933 -0.0273 0.0060 1.0000
11.000 1.2813 0.02483 0.02004 -0.0258 0.0057 1.0000
11.250 1.2928 0.02563 0.02093 -0.0235 0.0055 1.0000
11.500 1.2994 0.02680 0.02224 -0.0207 0.0053 1.0000
11.750 1.3080 0.02775 0.02328 -0.0184 0.0050 1.0000
12.000 1.3156 0.02877 0.02440 -0.0161 0.0048 1.0000
12.250 1.3215 0.02995 0.02568 -0.0138 0.0047 1.0000
12.500 1.3267 0.03121 0.02702 -0.0118 0.0045 1.0000
12.750 1.3288 0.03281 0.02873 -0.0098 0.0044 1.0000
13.000 1.3270 0.03488 0.03092 -0.0079 0.0043 1.0000
13.250 1.3322 0.03634 0.03244 -0.0069 0.0042 1.0000
13.500 1.3230 0.03951 0.03579 -0.0057 0.0042 1.0000
13.750 1.3124 0.04313 0.03956 -0.0053 0.0040 1.0000
14.000 1.2983 0.04758 0.04417 -0.0059 0.0039 1.0000
14.250 1.2838 0.05259 0.04936 -0.0073 0.0039 1.0000
14.500 1.2632 0.05900 0.05597 -0.0099 0.0039 1.0000
14.750 1.2272 0.06863 0.06587 -0.0148 0.0038 1.0000
15.000 1.2276 0.07263 0.06994 -0.0171 0.0039 1.0000
15.250 1.2112 0.07992 0.07738 -0.0213 0.0039 1.0000
15.500 1.1930 0.08794 0.08554 -0.0261 0.0039 1.0000
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Polar data table (+)
Polar graphs
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