RG-12 (rg12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-12 (rg12-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.18 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12-il-1000000-n5.txt Download as CSV file: xf-rg12-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG-12
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7924 0.04242 0.04051 -0.0521 1.0000 0.0033
-10.500 -0.7926 0.04161 0.03967 -0.0497 1.0000 0.0035
-10.250 -0.8300 0.03556 0.03324 -0.0457 1.0000 0.0034
-10.000 -0.8437 0.03139 0.02873 -0.0424 1.0000 0.0034
-9.750 -0.8413 0.02896 0.02605 -0.0399 1.0000 0.0035
-9.500 -0.8374 0.02643 0.02326 -0.0374 1.0000 0.0035
-9.250 -0.8227 0.02445 0.02104 -0.0364 0.9995 0.0036
-9.000 -0.7982 0.02246 0.01879 -0.0373 0.9980 0.0037
-8.750 -0.7728 0.02053 0.01659 -0.0382 0.9964 0.0038
-8.500 -0.7450 0.01908 0.01493 -0.0391 0.9950 0.0039
-8.250 -0.7175 0.01769 0.01333 -0.0399 0.9935 0.0040
-8.000 -0.6904 0.01677 0.01226 -0.0403 0.9914 0.0041
-7.750 -0.6626 0.01575 0.01108 -0.0408 0.9893 0.0043
-7.500 -0.6334 0.01490 0.01011 -0.0416 0.9873 0.0044
-7.250 -0.6032 0.01413 0.00923 -0.0425 0.9856 0.0045
-7.000 -0.5724 0.01326 0.00824 -0.0435 0.9840 0.0046
-6.750 -0.5407 0.01252 0.00739 -0.0447 0.9828 0.0046
-6.500 -0.5159 0.01194 0.00672 -0.0442 0.9783 0.0047
-6.250 -0.4868 0.01140 0.00611 -0.0447 0.9749 0.0048
-6.000 -0.4572 0.01042 0.00498 -0.0453 0.9721 0.0053
-5.750 -0.4249 0.00993 0.00445 -0.0464 0.9700 0.0058
-5.500 -0.3993 0.00958 0.00405 -0.0460 0.9636 0.0062
-5.250 -0.3681 0.00925 0.00369 -0.0469 0.9591 0.0067
-5.000 -0.3366 0.00893 0.00332 -0.0477 0.9538 0.0071
-4.750 -0.3049 0.00866 0.00300 -0.0486 0.9466 0.0075
-4.500 -0.2723 0.00840 0.00271 -0.0497 0.9384 0.0080
-4.250 -0.2403 0.00814 0.00241 -0.0506 0.9281 0.0103
-4.000 -0.2108 0.00786 0.00215 -0.0510 0.9146 0.0196
-3.750 -0.1829 0.00763 0.00193 -0.0510 0.8990 0.0334
-3.500 -0.1557 0.00747 0.00176 -0.0509 0.8819 0.0444
-3.250 -0.1293 0.00730 0.00160 -0.0506 0.8641 0.0648
-2.750 -0.0771 0.00700 0.00134 -0.0499 0.8271 0.1117
-2.500 -0.0518 0.00675 0.00120 -0.0495 0.8078 0.1642
-2.250 -0.0261 0.00660 0.00110 -0.0491 0.7884 0.2047
-2.000 -0.0002 0.00646 0.00101 -0.0488 0.7686 0.2452
-1.500 0.0509 0.00605 0.00085 -0.0481 0.7287 0.3722
-1.250 0.0765 0.00587 0.00080 -0.0477 0.7078 0.4361
-1.000 0.1021 0.00568 0.00075 -0.0474 0.6870 0.5048
-0.750 0.1275 0.00549 0.00071 -0.0470 0.6654 0.5805
-0.500 0.1528 0.00532 0.00072 -0.0466 0.6438 0.6628
-0.250 0.1790 0.00534 0.00075 -0.0462 0.6219 0.7012
0.000 0.2058 0.00540 0.00078 -0.0459 0.6000 0.7220
0.250 0.2325 0.00548 0.00081 -0.0457 0.5775 0.7372
0.500 0.2594 0.00558 0.00084 -0.0454 0.5550 0.7501
0.750 0.2863 0.00568 0.00088 -0.0452 0.5323 0.7617
1.000 0.3130 0.00579 0.00093 -0.0450 0.5087 0.7711
1.250 0.3398 0.00591 0.00099 -0.0447 0.4845 0.7792
1.500 0.3665 0.00605 0.00105 -0.0445 0.4592 0.7886
1.750 0.3930 0.00618 0.00112 -0.0442 0.4350 0.7978
2.000 0.4195 0.00633 0.00120 -0.0440 0.4111 0.8064
2.250 0.4460 0.00648 0.00130 -0.0437 0.3864 0.8155
2.500 0.4724 0.00663 0.00139 -0.0434 0.3629 0.8238
3.000 0.5248 0.00701 0.00161 -0.0429 0.3088 0.8363
3.250 0.5510 0.00722 0.00175 -0.0426 0.2827 0.8415
3.500 0.5771 0.00744 0.00188 -0.0424 0.2569 0.8464
3.750 0.6027 0.00768 0.00203 -0.0420 0.2294 0.8518
4.000 0.6288 0.00789 0.00219 -0.0417 0.2079 0.8577
4.250 0.6544 0.00812 0.00236 -0.0414 0.1853 0.8634
4.500 0.6795 0.00842 0.00258 -0.0410 0.1574 0.8700
4.750 0.7037 0.00880 0.00282 -0.0404 0.1244 0.8771
5.000 0.7284 0.00911 0.00305 -0.0399 0.1006 0.8852
5.250 0.7530 0.00938 0.00329 -0.0393 0.0839 0.8936
5.500 0.7776 0.00964 0.00353 -0.0388 0.0699 0.9031
6.000 0.8248 0.01016 0.00406 -0.0372 0.0476 0.9302
6.250 0.8478 0.01046 0.00434 -0.0363 0.0358 0.9514
6.500 0.8765 0.01085 0.00469 -0.0367 0.0235 0.9773
6.750 0.9051 0.01124 0.00505 -0.0372 0.0166 1.0000
7.000 0.9295 0.01162 0.00541 -0.0367 0.0129 1.0000
7.250 0.9544 0.01194 0.00577 -0.0363 0.0111 1.0000
7.500 0.9788 0.01231 0.00614 -0.0359 0.0093 1.0000
7.750 1.0029 0.01271 0.00655 -0.0354 0.0077 1.0000
8.000 1.0272 0.01306 0.00695 -0.0349 0.0066 1.0000
8.250 1.0507 0.01349 0.00739 -0.0343 0.0053 1.0000
8.500 1.0738 0.01398 0.00791 -0.0336 0.0043 1.0000
8.750 1.0970 0.01443 0.00841 -0.0330 0.0040 1.0000
9.000 1.1196 0.01492 0.00897 -0.0323 0.0035 1.0000
9.250 1.1418 0.01545 0.00955 -0.0315 0.0032 1.0000
9.500 1.1633 0.01603 0.01019 -0.0306 0.0029 1.0000
9.750 1.1840 0.01667 0.01090 -0.0296 0.0027 1.0000
10.000 1.2032 0.01745 0.01178 -0.0284 0.0025 1.0000
10.250 1.2194 0.01850 0.01296 -0.0268 0.0022 1.0000
10.500 1.2387 0.01916 0.01369 -0.0257 0.0022 1.0000
10.750 1.2569 0.01988 0.01450 -0.0244 0.0022 1.0000
11.000 1.2742 0.02065 0.01538 -0.0231 0.0021 1.0000
11.250 1.2895 0.02153 0.01636 -0.0214 0.0021 1.0000
11.500 1.3033 0.02247 0.01742 -0.0196 0.0020 1.0000
11.750 1.3147 0.02340 0.01846 -0.0174 0.0020 1.0000
12.000 1.3220 0.02442 0.01959 -0.0146 0.0020 1.0000
12.250 1.3289 0.02544 0.02072 -0.0119 0.0019 1.0000
12.500 1.3339 0.02661 0.02201 -0.0092 0.0019 1.0000
12.750 1.3378 0.02789 0.02341 -0.0066 0.0019 1.0000
13.000 1.3400 0.02935 0.02499 -0.0041 0.0019 1.0000
13.250 1.3369 0.03130 0.02710 -0.0016 0.0019 1.0000
13.500 1.3373 0.03310 0.02903 0.0002 0.0018 1.0000
13.750 1.3303 0.03573 0.03182 0.0018 0.0018 1.0000
14.000 1.3295 0.03801 0.03421 0.0026 0.0018 1.0000
14.250 1.3236 0.04105 0.03739 0.0030 0.0018 1.0000
14.500 1.3164 0.04455 0.04104 0.0026 0.0018 1.0000
14.750 1.3076 0.04861 0.04526 0.0016 0.0018 1.0000
15.000 1.2965 0.05340 0.05020 -0.0002 0.0017 1.0000
15.250 1.2813 0.05926 0.05622 -0.0030 0.0017 1.0000
15.500 1.2608 0.06653 0.06367 -0.0070 0.0018 1.0000
15.750 1.2405 0.07429 0.07159 -0.0114 0.0018 1.0000
16.000 1.2205 0.08246 0.07990 -0.0162 0.0018 1.0000
16.250 1.1916 0.09284 0.09043 -0.0223 0.0018 1.0000
16.500 1.1671 0.10275 0.10047 -0.0281 0.0018 1.0000
16.750 1.1379 0.11404 0.11191 -0.0346 0.0018 1.0000
17.000 1.1155 0.12418 0.12215 -0.0403 0.0018 1.0000
17.250 1.0853 0.13651 0.13460 -0.0474 0.0019 1.0000
17.500 1.0603 0.14808 0.14628 -0.0540 0.0019 1.0000
17.750 1.0318 0.16119 0.15949 -0.0614 0.0019 1.0000
18.000 0.9980 0.17688 0.17530 -0.0700 0.0020 1.0000
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Polar data table (+)
Polar graphs
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