RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 500,000 Max Cl/Cd: 86.7 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12a189-il-500000.txt Download as CSV file: xf-rg12a189-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4906 0.08437 0.08212 -0.0275 1.0000 0.0175
-8.750 -0.4953 0.08008 0.07788 -0.0295 1.0000 0.0178
-8.500 -0.5034 0.07554 0.07338 -0.0317 1.0000 0.0178
-8.250 -0.5200 0.07084 0.06874 -0.0346 1.0000 0.0177
-8.000 -0.5353 0.06579 0.06367 -0.0371 1.0000 0.0176
-7.750 -0.5442 0.06099 0.05880 -0.0382 1.0000 0.0178
-7.500 -0.5504 0.05633 0.05404 -0.0382 1.0000 0.0182
-7.250 -0.5532 0.05183 0.04941 -0.0376 1.0000 0.0187
-7.000 -0.5430 0.04848 0.04574 -0.0362 1.0000 0.0205
-6.750 -0.5408 0.04551 0.04250 -0.0343 1.0000 0.0207
-5.500 -0.4565 0.02093 0.01577 -0.0341 0.9942 0.0145
-5.250 -0.4275 0.01740 0.01190 -0.0347 0.9920 0.0132
-5.000 -0.3949 0.01547 0.00970 -0.0356 0.9895 0.0131
-4.750 -0.3606 0.01414 0.00819 -0.0369 0.9871 0.0135
-4.500 -0.3241 0.01339 0.00733 -0.0387 0.9849 0.0142
-4.250 -0.2892 0.01184 0.00564 -0.0404 0.9833 0.0157
-4.000 -0.2582 0.01137 0.00517 -0.0412 0.9783 0.0187
-3.750 -0.2226 0.01083 0.00457 -0.0428 0.9747 0.0207
-3.500 -0.1856 0.01000 0.00373 -0.0447 0.9722 0.0344
-3.250 -0.1495 0.00932 0.00333 -0.0467 0.9693 0.0976
-3.000 -0.1189 0.00878 0.00306 -0.0476 0.9632 0.1648
-2.750 -0.0832 0.00806 0.00280 -0.0497 0.9598 0.2868
-2.500 -0.0474 0.00702 0.00254 -0.0521 0.9573 0.4973
-2.250 -0.0212 0.00630 0.00247 -0.0517 0.9498 0.6805
-2.000 0.0148 0.00612 0.00238 -0.0531 0.9454 0.7380
-1.750 0.0466 0.00601 0.00227 -0.0537 0.9377 0.7635
-1.500 0.0813 0.00591 0.00217 -0.0548 0.9307 0.7888
-1.250 0.1118 0.00584 0.00211 -0.0549 0.9195 0.8077
-1.000 0.1436 0.00578 0.00203 -0.0555 0.9072 0.8208
-0.750 0.1743 0.00576 0.00195 -0.0557 0.8925 0.8329
-0.500 0.2037 0.00576 0.00189 -0.0557 0.8754 0.8441
-0.250 0.2309 0.00577 0.00187 -0.0552 0.8559 0.8536
0.000 0.2575 0.00582 0.00184 -0.0546 0.8344 0.8628
0.250 0.2835 0.00589 0.00182 -0.0539 0.8118 0.8724
0.500 0.3081 0.00596 0.00182 -0.0529 0.7887 0.8811
0.750 0.3325 0.00604 0.00183 -0.0519 0.7646 0.8905
1.250 0.3792 0.00623 0.00187 -0.0494 0.7175 0.9102
1.500 0.4030 0.00631 0.00189 -0.0484 0.6939 0.9184
1.750 0.4270 0.00641 0.00192 -0.0474 0.6707 0.9260
2.250 0.4751 0.00661 0.00199 -0.0456 0.6235 0.9408
2.500 0.4996 0.00671 0.00203 -0.0448 0.5997 0.9486
2.750 0.5246 0.00684 0.00208 -0.0442 0.5746 0.9579
3.000 0.5530 0.00699 0.00215 -0.0443 0.5476 0.9666
3.250 0.5842 0.00716 0.00226 -0.0451 0.5193 0.9747
3.500 0.6172 0.00736 0.00237 -0.0464 0.4888 0.9835
3.750 0.6523 0.00760 0.00250 -0.0482 0.4553 0.9916
4.000 0.6831 0.00788 0.00265 -0.0492 0.4195 1.0000
4.250 0.7057 0.00814 0.00282 -0.0485 0.3905 1.0000
4.500 0.7298 0.00846 0.00301 -0.0480 0.3539 1.0000
4.750 0.7538 0.00886 0.00323 -0.0475 0.3116 1.0000
5.000 0.7781 0.00926 0.00348 -0.0471 0.2738 1.0000
5.250 0.8016 0.00975 0.00378 -0.0466 0.2293 1.0000
5.500 0.8252 0.01025 0.00411 -0.0461 0.1894 1.0000
5.750 0.8487 0.01077 0.00446 -0.0455 0.1538 1.0000
6.000 0.8722 0.01129 0.00485 -0.0450 0.1212 1.0000
6.250 0.8950 0.01189 0.00530 -0.0443 0.0900 1.0000
6.500 0.9162 0.01266 0.00587 -0.0435 0.0528 1.0000
6.750 0.9365 0.01361 0.00666 -0.0423 0.0283 1.0000
7.000 0.9592 0.01423 0.00732 -0.0415 0.0240 1.0000
7.250 0.9786 0.01525 0.00844 -0.0400 0.0209 1.0000
7.500 1.0007 0.01588 0.00916 -0.0391 0.0201 1.0000
7.750 1.0222 0.01657 0.00996 -0.0381 0.0189 1.0000
8.000 1.0432 0.01728 0.01074 -0.0371 0.0175 1.0000
8.250 1.0627 0.01814 0.01168 -0.0359 0.0165 1.0000
8.500 1.0799 0.01928 0.01290 -0.0343 0.0156 1.0000
8.750 1.0918 0.02120 0.01497 -0.0320 0.0147 1.0000
9.000 1.1077 0.02278 0.01670 -0.0304 0.0140 1.0000
9.250 1.1276 0.02352 0.01756 -0.0293 0.0133 1.0000
9.500 1.1448 0.02473 0.01891 -0.0279 0.0126 1.0000
9.750 1.1610 0.02602 0.02034 -0.0264 0.0119 1.0000
10.000 1.1755 0.02750 0.02198 -0.0248 0.0114 1.0000
10.250 1.1885 0.02897 0.02359 -0.0230 0.0109 1.0000
10.500 1.1990 0.03059 0.02531 -0.0211 0.0104 1.0000
10.750 1.2041 0.03288 0.02778 -0.0186 0.0101 1.0000
11.000 1.1951 0.03730 0.03254 -0.0149 0.0097 1.0000
11.250 1.1852 0.03996 0.03549 -0.0111 0.0094 1.0000
11.500 1.1813 0.04193 0.03765 -0.0083 0.0093 1.0000
11.750 1.1792 0.04356 0.03947 -0.0062 0.0090 1.0000
12.000 1.1749 0.04578 0.04187 -0.0047 0.0086 1.0000
12.250 1.1638 0.04916 0.04546 -0.0037 0.0085 1.0000
12.500 1.1500 0.05320 0.04972 -0.0037 0.0085 1.0000
12.750 1.1330 0.05817 0.05489 -0.0048 0.0085 1.0000
13.000 1.1124 0.06429 0.06123 -0.0073 0.0086 1.0000
13.250 1.0987 0.06988 0.06699 -0.0104 0.0084 1.0000
13.500 1.0746 0.07804 0.07533 -0.0153 0.0087 1.0000
13.750 1.0528 0.08659 0.08404 -0.0210 0.0087 1.0000
14.000 1.0334 0.09543 0.09303 -0.0269 0.0088 1.0000
14.250 1.0059 0.10682 0.10455 -0.0343 0.0091 1.0000
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Polar data table (+)
Polar graphs
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