RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.76 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf26-il-1000000-n5.txt Download as CSV file: xf-raf26-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 26 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5125 0.08550 0.08394 -0.0179 1.0000 0.0028
-8.250 -0.5167 0.08171 0.08018 -0.0190 1.0000 0.0028
-8.000 -0.5259 0.07813 0.07664 -0.0194 1.0000 0.0027
-7.750 -0.5326 0.07409 0.07263 -0.0212 1.0000 0.0027
-6.750 -0.5051 0.01737 0.01369 -0.0571 0.9886 0.0022
-6.500 -0.4768 0.01536 0.01132 -0.0579 0.9873 0.0024
-6.250 -0.4539 0.01372 0.00938 -0.0571 0.9838 0.0025
-6.000 -0.4265 0.01255 0.00799 -0.0573 0.9810 0.0027
-5.750 -0.3971 0.01165 0.00691 -0.0578 0.9789 0.0030
-5.500 -0.3724 0.01107 0.00621 -0.0572 0.9744 0.0032
-5.250 -0.3462 0.01016 0.00511 -0.0570 0.9693 0.0034
-4.750 -0.2951 0.00930 0.00416 -0.0561 0.9484 0.0043
-4.500 -0.2607 0.00881 0.00360 -0.0576 0.9409 0.0049
-4.250 -0.2214 0.00835 0.00304 -0.0602 0.9340 0.0054
-3.750 -0.1318 0.00750 0.00201 -0.0681 0.9200 0.0085
-3.500 -0.0925 0.00722 0.00165 -0.0708 0.9096 0.0126
-3.250 -0.0583 0.00704 0.00141 -0.0723 0.8922 0.0228
-3.000 -0.0300 0.00695 0.00125 -0.0724 0.8704 0.0348
-2.750 -0.0040 0.00684 0.00112 -0.0720 0.8553 0.0491
-2.500 0.0216 0.00668 0.00100 -0.0715 0.8422 0.0757
-2.250 0.0470 0.00654 0.00089 -0.0710 0.8293 0.1038
-2.000 0.0721 0.00640 0.00080 -0.0704 0.8143 0.1366
-1.750 0.0967 0.00628 0.00072 -0.0697 0.7948 0.1755
-1.500 0.1209 0.00620 0.00064 -0.0689 0.7718 0.2140
-1.250 0.1449 0.00606 0.00058 -0.0682 0.7499 0.2680
-1.000 0.1687 0.00594 0.00056 -0.0673 0.7262 0.3311
-0.750 0.1917 0.00586 0.00054 -0.0664 0.6947 0.3986
-0.500 0.2153 0.00591 0.00054 -0.0655 0.6616 0.4313
-0.250 0.2396 0.00596 0.00055 -0.0647 0.6317 0.4592
0.000 0.2634 0.00595 0.00057 -0.0639 0.6016 0.5086
0.250 0.2855 0.00589 0.00062 -0.0628 0.5594 0.5947
0.500 0.3033 0.00606 0.00071 -0.0608 0.4594 0.6928
0.750 0.3237 0.00614 0.00081 -0.0592 0.4097 0.7634
1.000 0.3448 0.00604 0.00089 -0.0577 0.3866 0.8468
1.250 0.4234 0.00666 0.00115 -0.0699 0.2266 0.9901
1.500 0.4563 0.00706 0.00131 -0.0714 0.1666 1.0000
1.750 0.4795 0.00732 0.00143 -0.0704 0.1298 1.0000
2.000 0.5020 0.00764 0.00158 -0.0694 0.0860 1.0000
2.250 0.5266 0.00777 0.00170 -0.0687 0.0807 1.0000
2.500 0.5513 0.00790 0.00184 -0.0680 0.0780 1.0000
2.750 0.5757 0.00808 0.00199 -0.0673 0.0730 1.0000
3.000 0.6003 0.00822 0.00214 -0.0666 0.0689 1.0000
3.250 0.6253 0.00834 0.00228 -0.0660 0.0653 1.0000
3.500 0.6495 0.00854 0.00245 -0.0652 0.0559 1.0000
3.750 0.6732 0.00877 0.00260 -0.0644 0.0381 1.0000
4.000 0.6951 0.00921 0.00289 -0.0632 0.0127 1.0000
4.250 0.7187 0.00949 0.00318 -0.0623 0.0082 1.0000
4.500 0.7424 0.00975 0.00350 -0.0614 0.0069 1.0000
4.750 0.7654 0.01008 0.00386 -0.0605 0.0058 1.0000
5.000 0.7880 0.01048 0.00430 -0.0594 0.0048 1.0000
5.250 0.8113 0.01079 0.00465 -0.0584 0.0042 1.0000
5.500 0.8341 0.01116 0.00506 -0.0574 0.0038 1.0000
5.750 0.8562 0.01162 0.00555 -0.0563 0.0033 1.0000
6.000 0.8765 0.01230 0.00635 -0.0548 0.0031 1.0000
6.250 0.8985 0.01279 0.00691 -0.0537 0.0029 1.0000
6.500 0.9196 0.01340 0.00762 -0.0523 0.0026 1.0000
6.750 0.9400 0.01414 0.00846 -0.0509 0.0025 1.0000
7.000 0.9600 0.01495 0.00938 -0.0494 0.0023 1.0000
7.250 0.9796 0.01588 0.01043 -0.0479 0.0022 1.0000
7.500 1.0011 0.01646 0.01108 -0.0468 0.0021 1.0000
7.750 1.0232 0.01692 0.01158 -0.0460 0.0019 1.0000
8.000 1.0415 0.01805 0.01285 -0.0444 0.0018 1.0000
8.250 1.0566 0.01982 0.01487 -0.0422 0.0017 1.0000
8.500 1.0743 0.02114 0.01642 -0.0406 0.0016 1.0000
8.750 1.0905 0.02269 0.01822 -0.0387 0.0016 1.0000
9.000 1.1042 0.02464 0.02045 -0.0365 0.0015 1.0000
9.250 1.1148 0.02702 0.02316 -0.0339 0.0015 1.0000
9.500 1.1202 0.03010 0.02661 -0.0308 0.0014 1.0000
9.750 1.1030 0.03671 0.03388 -0.0250 0.0014 1.0000
10.000 1.0421 0.05056 0.04845 -0.0159 0.0014 1.0000
10.250 1.0079 0.05655 0.05466 -0.0106 0.0014 1.0000
10.500 0.9774 0.06217 0.06041 -0.0084 0.0013 1.0000
10.750 0.9562 0.06718 0.06553 -0.0092 0.0014 1.0000
11.000 0.9349 0.07368 0.07215 -0.0128 0.0014 1.0000
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Polar data table (+)
Polar graphs
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