AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.51 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12a-il-1000000-n5.txt Download as CSV file: xf-rg12a-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AIRFOIL PROFILE12A 9.00%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5255 0.08873 0.08709 -0.0241 1.0000 0.0027
-9.750 -0.5376 0.08237 0.08076 -0.0269 1.0000 0.0026
-8.750 -0.7114 0.02620 0.02320 -0.0466 0.9957 0.0029
-8.500 -0.6881 0.02264 0.01920 -0.0481 0.9938 0.0030
-8.250 -0.6645 0.02040 0.01664 -0.0486 0.9914 0.0031
-8.000 -0.6389 0.01837 0.01431 -0.0492 0.9891 0.0032
-7.750 -0.6108 0.01692 0.01262 -0.0500 0.9873 0.0033
-7.500 -0.5815 0.01554 0.01102 -0.0509 0.9857 0.0033
-7.250 -0.5506 0.01454 0.00985 -0.0520 0.9844 0.0034
-7.000 -0.5188 0.01369 0.00886 -0.0533 0.9833 0.0036
-6.750 -0.4955 0.01298 0.00804 -0.0525 0.9791 0.0036
-6.500 -0.4664 0.01252 0.00752 -0.0530 0.9763 0.0038
-6.250 -0.4366 0.01179 0.00669 -0.0536 0.9739 0.0039
-6.000 -0.4062 0.01082 0.00558 -0.0545 0.9719 0.0042
-5.750 -0.3766 0.01022 0.00490 -0.0550 0.9692 0.0044
-5.500 -0.3511 0.00978 0.00441 -0.0546 0.9633 0.0047
-5.250 -0.3195 0.00938 0.00397 -0.0555 0.9595 0.0050
-5.000 -0.2885 0.00903 0.00358 -0.0562 0.9548 0.0056
-4.750 -0.2576 0.00870 0.00321 -0.0569 0.9483 0.0061
-4.500 -0.2240 0.00837 0.00283 -0.0582 0.9421 0.0068
-4.250 -0.1914 0.00807 0.00249 -0.0593 0.9327 0.0083
-4.000 -0.1593 0.00785 0.00223 -0.0602 0.9208 0.0103
-3.750 -0.1291 0.00762 0.00197 -0.0607 0.9055 0.0148
-3.500 -0.1009 0.00740 0.00174 -0.0608 0.8878 0.0281
-3.250 -0.0738 0.00725 0.00158 -0.0606 0.8675 0.0428
-2.750 -0.0218 0.00695 0.00130 -0.0598 0.8236 0.0941
-2.500 0.0038 0.00680 0.00118 -0.0594 0.8006 0.1297
-2.250 0.0293 0.00668 0.00108 -0.0590 0.7762 0.1688
-2.000 0.0547 0.00649 0.00099 -0.0586 0.7525 0.2255
-1.750 0.0803 0.00635 0.00092 -0.0582 0.7289 0.2805
-1.500 0.1061 0.00624 0.00085 -0.0579 0.7060 0.3289
-1.250 0.1320 0.00608 0.00080 -0.0576 0.6843 0.3929
-1.000 0.1573 0.00580 0.00075 -0.0573 0.6631 0.4952
-0.750 0.1824 0.00546 0.00073 -0.0569 0.6429 0.6176
-0.500 0.2083 0.00538 0.00076 -0.0565 0.6221 0.6881
-0.250 0.2350 0.00543 0.00079 -0.0563 0.6022 0.7172
0.000 0.2619 0.00549 0.00082 -0.0560 0.5818 0.7351
0.250 0.2887 0.00558 0.00086 -0.0558 0.5618 0.7488
0.500 0.3158 0.00568 0.00089 -0.0556 0.5411 0.7601
0.750 0.3426 0.00578 0.00094 -0.0553 0.5200 0.7704
1.000 0.3694 0.00589 0.00099 -0.0551 0.4973 0.7799
1.250 0.3963 0.00602 0.00105 -0.0549 0.4749 0.7892
1.500 0.4229 0.00614 0.00112 -0.0546 0.4527 0.7997
1.750 0.4493 0.00626 0.00120 -0.0543 0.4305 0.8106
2.000 0.4759 0.00641 0.00128 -0.0541 0.4080 0.8191
2.250 0.5024 0.00657 0.00138 -0.0538 0.3830 0.8249
2.500 0.5289 0.00676 0.00147 -0.0536 0.3571 0.8294
2.750 0.5554 0.00693 0.00157 -0.0534 0.3349 0.8333
3.000 0.5818 0.00712 0.00170 -0.0532 0.3108 0.8378
3.250 0.6079 0.00734 0.00183 -0.0529 0.2841 0.8425
3.500 0.6337 0.00760 0.00198 -0.0526 0.2539 0.8469
3.750 0.6589 0.00789 0.00215 -0.0522 0.2207 0.8521
4.000 0.6830 0.00833 0.00239 -0.0517 0.1718 0.8580
4.250 0.7079 0.00866 0.00260 -0.0512 0.1421 0.8636
4.500 0.7332 0.00893 0.00281 -0.0508 0.1198 0.8699
4.750 0.7583 0.00922 0.00304 -0.0504 0.0997 0.8763
5.000 0.7829 0.00954 0.00329 -0.0499 0.0796 0.8840
5.250 0.8070 0.00988 0.00358 -0.0493 0.0586 0.8926
5.500 0.8309 0.01022 0.00386 -0.0486 0.0431 0.9029
6.000 0.8763 0.01089 0.00449 -0.0467 0.0183 0.9314
6.250 0.8992 0.01115 0.00480 -0.0457 0.0141 0.9561
6.500 0.9296 0.01147 0.00515 -0.0465 0.0124 1.0000
6.750 0.9546 0.01182 0.00553 -0.0461 0.0112 1.0000
7.000 0.9793 0.01221 0.00596 -0.0456 0.0104 1.0000
7.250 1.0035 0.01265 0.00646 -0.0451 0.0098 1.0000
7.500 1.0281 0.01301 0.00687 -0.0447 0.0097 1.0000
7.750 1.0523 0.01341 0.00733 -0.0442 0.0095 1.0000
8.000 1.0763 0.01381 0.00777 -0.0437 0.0092 1.0000
8.250 1.1001 0.01421 0.00822 -0.0431 0.0087 1.0000
8.500 1.1237 0.01462 0.00867 -0.0426 0.0082 1.0000
8.750 1.1469 0.01506 0.00915 -0.0420 0.0077 1.0000
9.000 1.1695 0.01555 0.00968 -0.0413 0.0073 1.0000
9.250 1.1910 0.01614 0.01034 -0.0405 0.0069 1.0000
9.500 1.2096 0.01702 0.01133 -0.0392 0.0063 1.0000
9.750 1.2317 0.01748 0.01183 -0.0385 0.0061 1.0000
10.000 1.2538 0.01792 0.01233 -0.0378 0.0059 1.0000
10.250 1.2752 0.01840 0.01287 -0.0370 0.0056 1.0000
10.500 1.2964 0.01887 0.01339 -0.0362 0.0052 1.0000
10.750 1.3168 0.01939 0.01396 -0.0352 0.0048 1.0000
11.000 1.3370 0.01990 0.01451 -0.0343 0.0045 1.0000
11.250 1.3558 0.02049 0.01516 -0.0332 0.0042 1.0000
11.500 1.3723 0.02126 0.01598 -0.0318 0.0038 1.0000
11.750 1.3886 0.02197 0.01677 -0.0303 0.0036 1.0000
12.000 1.4029 0.02269 0.01758 -0.0286 0.0034 1.0000
12.250 1.4151 0.02340 0.01837 -0.0264 0.0033 1.0000
12.500 1.4258 0.02418 0.01923 -0.0241 0.0030 1.0000
12.750 1.4360 0.02501 0.02013 -0.0219 0.0028 1.0000
13.000 1.4447 0.02593 0.02113 -0.0197 0.0026 1.0000
13.250 1.4533 0.02690 0.02215 -0.0176 0.0024 1.0000
13.500 1.4584 0.02813 0.02349 -0.0153 0.0023 1.0000
13.750 1.4611 0.02960 0.02508 -0.0130 0.0022 1.0000
14.000 1.4606 0.03141 0.02701 -0.0108 0.0021 1.0000
14.250 1.4615 0.03322 0.02894 -0.0092 0.0020 1.0000
14.500 1.4618 0.03523 0.03107 -0.0079 0.0019 1.0000
14.750 1.4591 0.03768 0.03366 -0.0069 0.0019 1.0000
15.000 1.4552 0.04050 0.03661 -0.0064 0.0019 1.0000
15.250 1.4517 0.04352 0.03976 -0.0065 0.0018 1.0000
15.500 1.4451 0.04717 0.04354 -0.0071 0.0018 1.0000
15.750 1.4351 0.05160 0.04812 -0.0084 0.0018 1.0000
16.000 1.4238 0.05655 0.05322 -0.0104 0.0017 1.0000
16.250 1.4110 0.06211 0.05892 -0.0130 0.0017 1.0000
16.500 1.3914 0.06918 0.06616 -0.0166 0.0017 1.0000
16.750 1.3740 0.07628 0.07341 -0.0205 0.0017 1.0000
17.000 1.3509 0.08486 0.08214 -0.0254 0.0017 1.0000
17.250 1.3189 0.09566 0.09312 -0.0316 0.0017 1.0000
17.500 1.2894 0.10638 0.10400 -0.0378 0.0018 1.0000
17.750 1.2528 0.11915 0.11693 -0.0453 0.0018 1.0000
18.000 1.2202 0.13141 0.12933 -0.0524 0.0019 1.0000
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Polar data table (+)
Polar graphs
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