RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 50,000 Max Cl/Cd: 33.99 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg12a189-il-50000.txt Download as CSV file: xf-rg12a189-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4615 0.10399 0.09706 -0.0110 1.0000 0.2515
-8.500 -0.4651 0.10124 0.09441 -0.0111 1.0000 0.2636
-8.250 -0.4797 0.09980 0.09309 -0.0114 1.0000 0.2753
-8.000 -0.4517 0.09469 0.08795 -0.0087 1.0000 0.2970
-7.750 -0.4514 0.09193 0.08527 -0.0076 1.0000 0.3142
-7.500 -0.4624 0.09000 0.08347 -0.0065 1.0000 0.3316
-7.250 -0.4518 0.08625 0.07976 -0.0048 1.0000 0.3495
-7.000 -0.4424 0.08289 0.07641 -0.0030 1.0000 0.3682
-6.750 -0.4675 0.08214 0.07585 0.0001 1.0000 0.3896
-6.500 -0.4400 0.07732 0.07101 0.0014 1.0000 0.4087
-5.750 -0.4914 0.05069 0.04327 -0.0352 1.0000 0.1313
-5.500 -0.4764 0.04574 0.03763 -0.0355 1.0000 0.1186
-5.250 -0.4592 0.04187 0.03352 -0.0347 1.0000 0.1150
-5.000 -0.4394 0.03785 0.02885 -0.0341 1.0000 0.1094
-4.750 -0.4166 0.03461 0.02478 -0.0331 1.0000 0.1068
-4.500 -0.3946 0.03184 0.02186 -0.0321 1.0000 0.1100
-4.250 -0.3710 0.02972 0.01924 -0.0310 1.0000 0.1185
-4.000 -0.3470 0.02741 0.01681 -0.0299 1.0000 0.1272
-3.750 -0.3227 0.02550 0.01473 -0.0286 1.0000 0.1447
-3.500 -0.2985 0.02361 0.01287 -0.0270 1.0000 0.1769
-3.250 -0.2765 0.02157 0.01134 -0.0255 1.0000 0.2509
-3.000 -0.1106 0.01899 0.01072 -0.0364 1.0000 1.0000
-2.750 -0.1062 0.01861 0.01013 -0.0337 1.0000 1.0000
-2.500 -0.1020 0.01830 0.00964 -0.0308 1.0000 1.0000
-2.250 -0.0985 0.01806 0.00924 -0.0276 1.0000 1.0000
-2.000 -0.0957 0.01785 0.00887 -0.0243 1.0000 1.0000
-1.750 -0.0931 0.01769 0.00857 -0.0209 1.0000 1.0000
-1.500 -0.0898 0.01758 0.00832 -0.0176 1.0000 1.0000
-1.250 -0.0835 0.01753 0.00812 -0.0148 1.0000 1.0000
-1.000 -0.0727 0.01757 0.00798 -0.0129 1.0000 1.0000
-0.750 -0.0588 0.01768 0.00792 -0.0115 1.0000 1.0000
-0.500 -0.0430 0.01786 0.00792 -0.0105 1.0000 1.0000
-0.250 -0.0262 0.01810 0.00801 -0.0098 1.0000 1.0000
0.000 -0.0088 0.01841 0.00819 -0.0092 1.0000 1.0000
0.250 0.0087 0.01878 0.00844 -0.0087 1.0000 1.0000
0.500 0.0263 0.01920 0.00877 -0.0083 1.0000 1.0000
0.750 0.0437 0.01969 0.00916 -0.0081 1.0000 1.0000
1.000 0.0609 0.02025 0.00965 -0.0079 1.0000 1.0000
1.250 0.0779 0.02088 0.01022 -0.0078 1.0000 1.0000
1.500 0.0945 0.02157 0.01087 -0.0078 1.0000 1.0000
1.750 0.1323 0.02268 0.01196 -0.0119 0.9898 1.0000
2.000 0.1925 0.02402 0.01333 -0.0197 0.9688 1.0000
2.250 0.2473 0.02500 0.01437 -0.0261 0.9462 1.0000
2.500 0.2991 0.02578 0.01526 -0.0315 0.9230 1.0000
2.750 0.3568 0.02639 0.01600 -0.0375 0.9009 1.0000
3.000 0.4050 0.02677 0.01653 -0.0414 0.8764 1.0000
3.250 0.4535 0.02699 0.01697 -0.0449 0.8518 1.0000
3.500 0.5120 0.02680 0.01702 -0.0493 0.8282 1.0000
3.750 0.5703 0.02627 0.01681 -0.0528 0.8039 1.0000
4.000 0.6158 0.02585 0.01663 -0.0540 0.7769 1.0000
4.250 0.6598 0.02529 0.01630 -0.0545 0.7484 1.0000
4.500 0.7018 0.02467 0.01592 -0.0542 0.7181 1.0000
4.750 0.7300 0.02461 0.01599 -0.0523 0.6834 1.0000
5.000 0.7633 0.02428 0.01574 -0.0506 0.6476 1.0000
5.250 0.7878 0.02439 0.01591 -0.0482 0.6081 1.0000
5.500 0.8120 0.02453 0.01609 -0.0457 0.5662 1.0000
5.750 0.8350 0.02475 0.01624 -0.0430 0.5214 1.0000
6.000 0.8550 0.02517 0.01658 -0.0402 0.4732 1.0000
6.250 0.8741 0.02572 0.01694 -0.0374 0.4216 1.0000
6.500 0.8900 0.02654 0.01755 -0.0344 0.3665 1.0000
6.750 0.9047 0.02769 0.01846 -0.0314 0.3100 1.0000
7.000 0.9178 0.02918 0.01964 -0.0286 0.2545 1.0000
7.250 0.9298 0.03095 0.02114 -0.0258 0.2042 1.0000
7.500 0.9450 0.03319 0.02313 -0.0237 0.1646 1.0000
7.750 0.9634 0.03571 0.02558 -0.0222 0.1377 1.0000
8.000 0.9852 0.03889 0.02898 -0.0209 0.1231 1.0000
8.250 1.0072 0.04225 0.03241 -0.0201 0.1135 1.0000
8.500 1.0191 0.04534 0.03613 -0.0179 0.1064 1.0000
8.750 1.0373 0.04908 0.03995 -0.0171 0.1007 1.0000
9.000 1.0425 0.05320 0.04471 -0.0148 0.0997 1.0000
9.250 1.0436 0.05767 0.04971 -0.0127 0.0994 1.0000
9.500 1.0416 0.06231 0.05478 -0.0107 0.0996 1.0000
9.750 1.0365 0.06713 0.05994 -0.0091 0.1001 1.0000
10.000 1.0300 0.07208 0.06514 -0.0078 0.1007 1.0000
10.250 0.9844 0.07641 0.06994 -0.0056 0.1038 1.0000
10.500 0.9357 0.08269 0.07639 -0.0069 0.1071 1.0000
10.750 0.9029 0.09032 0.08400 -0.0113 0.1101 1.0000
11.000 0.8856 0.09795 0.09161 -0.0155 0.1125 1.0000
11.250 0.8884 0.10376 0.09743 -0.0165 0.1142 1.0000
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Polar data table (+)
Polar graphs
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