TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 50,000 Max Cl/Cd: 31.39 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi12-il-50000.txt Download as CSV file: xf-tsagi12-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 12% 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4664 0.13028 0.12305 -0.0092 1.0000 0.2335
-11.000 -0.4490 0.12527 0.11803 -0.0087 1.0000 0.2418
-10.750 -0.4747 0.12483 0.11773 -0.0108 1.0000 0.2497
-10.500 -0.4457 0.11887 0.11171 -0.0094 1.0000 0.2612
-10.250 -0.4416 0.11523 0.10811 -0.0096 1.0000 0.2703
-10.000 -0.4665 0.11439 0.10741 -0.0110 1.0000 0.2802
-9.750 -0.4574 0.11061 0.10365 -0.0103 1.0000 0.2952
-9.500 -0.4512 0.10713 0.10021 -0.0096 1.0000 0.3103
-9.250 -0.4489 0.10396 0.09709 -0.0090 1.0000 0.3256
-9.000 -0.4459 0.10070 0.09388 -0.0082 1.0000 0.3410
-8.750 -0.4462 0.09757 0.09082 -0.0074 1.0000 0.3568
-8.500 -0.4152 0.09272 0.08589 -0.0059 1.0000 0.3772
-8.250 -0.4205 0.09061 0.08385 -0.0042 1.0000 0.4009
-8.000 -0.4010 0.08667 0.07991 -0.0028 1.0000 0.4235
-7.750 -0.4146 0.08501 0.07837 -0.0004 1.0000 0.4484
-7.500 -0.3957 0.08092 0.07427 0.0004 1.0000 0.4661
-7.250 -0.5926 0.06510 0.05844 -0.0207 1.0000 0.1883
-7.000 -0.5939 0.05971 0.05290 -0.0190 1.0000 0.1690
-6.750 -0.6079 0.05540 0.04821 -0.0153 1.0000 0.1563
-6.500 -0.6103 0.05183 0.04441 -0.0119 1.0000 0.1508
-6.250 -0.6226 0.04865 0.04055 -0.0065 1.0000 0.1438
-6.000 -0.6213 0.04592 0.03755 -0.0028 1.0000 0.1434
-5.750 -0.6208 0.04361 0.03485 0.0013 1.0000 0.1440
-5.500 -0.6139 0.04120 0.03238 0.0042 1.0000 0.1474
-5.250 -0.6067 0.03904 0.02993 0.0074 1.0000 0.1490
-5.000 -0.5974 0.03701 0.02757 0.0103 1.0000 0.1510
-4.750 -0.5873 0.03534 0.02551 0.0132 1.0000 0.1564
-4.500 -0.5742 0.03359 0.02348 0.0156 1.0000 0.1623
-4.250 -0.5575 0.03203 0.02171 0.0174 1.0000 0.1689
-4.000 -0.5400 0.03063 0.02008 0.0190 1.0000 0.1787
-3.750 -0.5210 0.02942 0.01873 0.0204 1.0000 0.1926
-3.500 -0.0663 0.02331 0.01479 -0.0418 1.0000 1.0000
-3.250 -0.0713 0.02336 0.01474 -0.0381 1.0000 1.0000
-3.000 -0.0814 0.02363 0.01492 -0.0336 1.0000 1.0000
-2.750 -0.0917 0.02398 0.01518 -0.0291 1.0000 1.0000
-2.500 -0.0995 0.02434 0.01542 -0.0250 1.0000 1.0000
-2.250 -0.1048 0.02471 0.01566 -0.0212 1.0000 1.0000
-2.000 -0.1078 0.02507 0.01590 -0.0178 1.0000 1.0000
-1.750 -0.1089 0.02546 0.01616 -0.0147 1.0000 1.0000
-1.500 -0.1084 0.02586 0.01643 -0.0118 1.0000 1.0000
-1.250 -0.0630 0.02637 0.01670 -0.0172 0.9882 1.0000
-1.000 -0.0049 0.02690 0.01701 -0.0247 0.9722 1.0000
-0.750 0.0514 0.02735 0.01727 -0.0316 0.9564 1.0000
-0.500 0.1049 0.02772 0.01750 -0.0377 0.9408 1.0000
-0.250 0.1563 0.02803 0.01770 -0.0432 0.9253 1.0000
0.000 0.2062 0.02830 0.01788 -0.0482 0.9100 1.0000
0.250 0.2547 0.02852 0.01805 -0.0528 0.8949 1.0000
0.500 0.3027 0.02871 0.01820 -0.0571 0.8800 1.0000
0.750 0.3441 0.02894 0.01841 -0.0601 0.8651 1.0000
1.000 0.3792 0.02925 0.01871 -0.0618 0.8503 1.0000
1.250 0.4096 0.02965 0.01910 -0.0627 0.8356 1.0000
1.500 0.4361 0.03012 0.01958 -0.0628 0.8210 1.0000
1.750 0.4589 0.03069 0.02016 -0.0623 0.8068 1.0000
2.000 0.4780 0.03139 0.02089 -0.0613 0.7931 1.0000
2.250 0.4961 0.03213 0.02165 -0.0600 0.7798 1.0000
2.500 0.5154 0.03287 0.02241 -0.0590 0.7675 1.0000
2.750 0.5458 0.03321 0.02282 -0.0592 0.7565 1.0000
3.000 0.5582 0.03419 0.02383 -0.0571 0.7440 1.0000
3.250 0.5625 0.03549 0.02516 -0.0542 0.7314 1.0000
3.500 0.5708 0.03670 0.02641 -0.0517 0.7198 1.0000
3.750 0.5931 0.03739 0.02716 -0.0508 0.7092 1.0000
4.000 0.6103 0.03828 0.02814 -0.0494 0.6984 1.0000
4.250 0.6066 0.04005 0.02994 -0.0457 0.6863 1.0000
4.500 0.6108 0.04154 0.03147 -0.0430 0.6751 1.0000
4.750 0.6404 0.04198 0.03204 -0.0427 0.6651 1.0000
5.000 0.6447 0.04351 0.03362 -0.0400 0.6536 1.0000
5.250 0.6323 0.04583 0.03597 -0.0358 0.6420 1.0000
5.500 0.6393 0.04735 0.03755 -0.0335 0.6309 1.0000
5.750 0.6735 0.04759 0.03797 -0.0334 0.6199 1.0000
6.000 0.6716 0.04954 0.03996 -0.0303 0.6081 1.0000
6.250 0.6422 0.05261 0.04295 -0.0250 0.5972 1.0000
6.500 0.6488 0.05423 0.04465 -0.0228 0.5855 1.0000
6.750 0.6704 0.05522 0.04581 -0.0217 0.5732 1.0000
7.000 0.7014 0.05565 0.04646 -0.0210 0.5600 1.0000
7.250 0.6994 0.05767 0.04854 -0.0182 0.5472 1.0000
7.500 0.6777 0.06095 0.05178 -0.0149 0.5352 1.0000
7.750 0.7516 0.05828 0.04962 -0.0151 0.5164 1.0000
8.000 0.7501 0.06001 0.05141 -0.0120 0.5001 1.0000
8.250 0.7433 0.06215 0.05360 -0.0089 0.4830 1.0000
8.500 1.0120 0.03224 0.02449 -0.0063 0.3664 1.0000
8.750 0.9982 0.03197 0.02408 0.0015 0.3068 1.0000
9.000 0.9767 0.03319 0.02466 0.0092 0.2432 1.0000
9.250 0.9567 0.03539 0.02617 0.0157 0.1990 1.0000
9.500 0.9448 0.03758 0.02795 0.0209 0.1710 1.0000
9.750 0.9474 0.03987 0.02995 0.0242 0.1483 1.0000
10.000 0.9608 0.04206 0.03201 0.0262 0.1302 1.0000
10.250 1.0169 0.04537 0.03501 0.0234 0.1123 1.0000
10.500 1.0283 0.04789 0.03796 0.0255 0.1070 1.0000
10.750 1.0611 0.05137 0.04137 0.0247 0.0990 1.0000
11.000 1.0600 0.05408 0.04452 0.0278 0.0974 1.0000
11.250 1.0581 0.05720 0.04801 0.0307 0.0964 1.0000
11.500 1.0488 0.06029 0.05141 0.0342 0.0959 1.0000
11.750 1.0355 0.06339 0.05477 0.0375 0.0958 1.0000
12.000 1.0183 0.06673 0.05836 0.0402 0.0960 1.0000
12.250 0.9984 0.07047 0.06232 0.0421 0.0963 1.0000
12.500 0.9754 0.07477 0.06681 0.0430 0.0967 1.0000
12.750 0.9518 0.07955 0.07176 0.0428 0.0973 1.0000
13.000 0.9286 0.08496 0.07729 0.0418 0.0980 1.0000
13.250 0.9094 0.09083 0.08326 0.0404 0.0989 1.0000
13.500 0.7909 0.11150 0.10402 0.0251 0.1104 1.0000
13.750 0.7748 0.11988 0.11236 0.0217 0.1118 1.0000
|
Polar data table (+)
Polar graphs
<< Back to TSAGI 12% AIRFOIL (tsagi12-il)